СОПЛО С НИЗКИМИ ВЫБРОСАМИ, КАМЕРА СГОРАНИЯ ДЛЯ ДВУХКОМПОНЕНТНОГО ГОРЮЧЕГО С НИЗКИМИ ВЫБРОСАМИ И ГАЗОТУРБОГЕНЕРАТОРНЫЙ АГРЕГАТ

Изобретение относится к области тепловой энергии и энергетики. Предложены сопло с низкими выбросами, камера сгорания для двухкомпонентного горючего с низкими выбросами и газотурбогенераторный агрегат, которые относятся к генераторному агрегату. Настоящее изобретение направлено на решение проблемы избыточного образования высокотемпературного нагара, известной из уровня техники. Согласно настоящему изобретению посредством интегрированной конструкции сопла с низкими выбросами для двухкомпонентного горючего обеспечивается комбинация из диффузного горения горючей жидкости и горения предварительно подготовленной смеси, содержащей газообразное горючее; при использовании газообразного горючего в газовой турбине через небольшие отверстия в завихрителе сопла с низкими выбросами выбрасывается газообразное горючее и воздух с обеспечением хорошего смешивания, при этом путем сжигания предварительно подготовленной смеси горючего и воздуха снижается величина выброса загрязняющих веществ; при использовании ...

СПОСОБ И УСТРОЙСТВО ДЛЯ ОКИСЛЕНИЯ ТОПЛИВА

Изобретение относится к энергетике. Способ окисления топлива включает в себя несколько этапов. В первом рабочем режиме смесь, содержащая топливо, поступившее из источника топлива, сжимается в компрессоре системы окисления топлива; сжатое топливо окисляется в реакционной камере системы окисления топлива; и окисленное топливо расширяется для генерирования кинетической энергии вращения. Во втором рабочем режиме топливо из источника топлива подается в обход компрессора, и топливо, которое прошло в обход компрессора, окисляется в реакционной камере. Также представлено устройство для осуществления способа. Изобретение позволяет принимать топливо из источника топлива и подавать топливо, принятое из источника топлива, в реакционную камеру, или во впуск компрессора для воздушно-топливной смеси, или путем подачи топлива в обход компрессора через теплообменник, нагреваемый потоком газов, выходящих из реакционной камеры. 2 н. и 17 з.п. ф-лы, 4 ил.

СПОСОБ УПРАВЛЕНИЯ МНОГОРЕЖИМНЫМ МНОГОТОПЛИВНЫМ ДВИГАТЕЛЕМ

Изобретение относится к области двигателестроения и может быть использовано в системах управления многорежимными многотопливными газотурбинными двигателями. Техническим результатом является повышение эксплуатационной надежности работы газотурбинного двигателя и повышение эффективности управления многотопливным газотурбинным двигателем на любом установившемся и переходном режимах его работы. В способе выбирают, по меньшей мере, три типа топлив и вводят в программное обеспечение системы управления двигателем значения их теплотворных способностей, регулируемый параметр и закон управления двигателем выбирают в зависимости от назначения силовой установки, в состав которой он входит, запуск и работу двигателя выполняют на смеси, по меньшей мере, двух топлив, контролируют запасы топлив, при этом смену топлив дополнительно выполняют и на переходных режимах работы двигателя, а соответствие суммарного расхода топлив заданному или фактическому значению регулируемого параметра обеспечивают его корректировкой ...

ЭНЕРГЕТИЧЕСКИЙ КОМПЛЕКС

Изобретением представлена новая, надежная, простая, экономичная, высокоэффективная, компактная схема «Энергетический комплекс» для выработки электрической, механической и тепловой энергии. Техническое решение обеспечивает встречное горение различных видов топлива, в том числе природный газ и мазут. Встречные, направленные, реактивные тепловые потоки, которые, отдавая свою кинетическую энергию вращению турбины и далее проходя теплообменник, отдают тепловую энергию, и на выходе через глушитель уходят в атмосферу, что может найти свое применение в различных сферах человеческой деятельности, в том числе в военной промышленности, на транспорте, в авиации, в судостроении, в атомной энергетике и других отраслях народного хозяйства, с высокой экономичностью и экологичностью, с расширенными функциональными возможностями, с высоким КПД и мощностью, что предполагает дальнейшее развитие и большие изменения на нашей планете Земля. 3 ил.

УСОВЕРШЕНСТВОВАНИЯ В СЖИГАНИИ И УТИЛИЗАЦИИ ТОПЛИВНЫХ ГАЗОВ

Изобретение предназначено для использования при сжигании и утилизации топливных газов. Топливный газ, поступающий в камеру сгорания по входному трубопроводу, является сжатой смесью с воздухом с концентрацией ниже низшего предела взрываемости. Смесь топливного газа/воздуха проходит внутри трубы для прохода в зону сгорания, где происходит сгорание в реакции или самосгорание. Продукт сгорания газа проходит по извилистому пути, обеспеченному расположением перегородок, к выходной трубе. Отходящий продукт сгорания газа проходит над внешней поверхностью трубы и отдает подогревающее тепло находящемуся в ней входящему газу. Система газовой турбины для утилизации отработанного топливного газа включает камеру сгорания, которая подает продукт сгорания топлива на ступень расширения турбины. Обеспечивается технологичность процесса и энергосбережение. 4 с. и 16 з.п.ф-лы, 7 ил.

Gasturbinenanlage und Verfahren zu deren Betrieb

GASDURCHFLUSS-REGELSYSTEM

INDUSTRIAL DUAL FUEL GAS TURBINE ELECTRIC POWER PLANT SYXTEM AND METHOD PERMITTING GENERATOR SYNCHRONIZATION

... 1410525 Automatic control of gas turbines WESTINGHOUSE ELECTRIC CORP 20 Nov 1972 [6 Dec 1971] 53473/72 Heading G3N [ Also in Division F 1] A gas turbine electric power plant having a dualfuel combustion system is controlled by a digital computer, having an input/output system comprising an operators control for the selection of dual-fuel options and sensors for monitoring selected turbine parameters, comprising at least dual-fuel system pressures, and generator parameters. The computer is operated to continuously monitor the sensors and operators selection to determine appropriate control actions including operation of a generator breaker and synchronization of the generator to a power system.

Fuel injection

Gas-turbine engine combustion system

Dual fuel system for a gas turbine engine

The system (10) comprises a gaseous fuel duct (30) feeding a manifold (32) and gaseous fuel burners (24) located in the engine combustion chamber or chambers (20). Liquid fuel can be burnt by first burning a small proportion of the liquid fuel in a vapourising combustion chamber (38), injecting the remaining liquid fuel into the vapouriser and ducting the vapourised liquid fuel into the gaseous fuel duct (30). The engine combustion chambers (20) are preferably of the type in which the fuel is burnt rich in the primary zone and is quenched almost immediately by dilution air so as to reduce the NOx emissions. ...

Aircraft fuel management

A method 2000 of identifying a fuel contained in a fuel tank of an aircraft and arranged to power a gas turbine engine of the aircraft is performed by processing circuitry of the aircraft. The method comprises obtaining 2002 a fuel characteristic of fuel already present in the fuel tank prior to refuelling and then determining 2004 a fuel characteristic of fuel added to the fuel tank on refuelling, then and calculating 2006 a fuel characteristic of the resultant fuel in the fuel tank after refuelling. The method 2000, when controlling the propulsion system of the aircraft further comprises controlling 2008 the propulsion system based on the calculated fuel characteristic of the resultant fuel in the fuel tank after refuelling. The propulsion system comprises a gas turbine engine (10, fig. 4), fuel tanks (50, 53, fig. 4) and a fuel composition tracker (202, fig. 4). The fuel composition tracker stores current fuel characteristic data, obtains a characteristic of the fuel added to the tank ...

IMPROVEMENTS IN THE BURN AND IN THE USE OF GASEOUS FUELS

A miniature multifuel gas turbine engine

System and method for operation of a flexible fuel combustor for a gas turbine

The present disclosure relates to systems and methods that are useful for controlling one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants and methods of carrying out a power production method utilizing different fuel chemistries. Combustion of the different fuel mixtures can be controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel chemistries.

Process for the generation of electrical power

GAS TURBINE ENGINE FUEL CONTROL SYSTEM

A fuel control system (22) having a combustive energy value evaluator (38 ) determining a combustive energy value of the fuel, and a controller (26) c alculating a desired flow rate based at least on the combustive energy value and controlling a fuel metering device (24) such that the fuel flow rate co rresponds to the desired fuel flow rate.

GAS TURBINE PLANT CONTROL SYSTEM

AUTOMATIC TEMPERATURE COMPENSATED FUEL FLOW REGULATION

METHODS AND SYSTEMS FOR SUPPLYING FUEL TO GAS TURBINE ENGINES

Methods and systems for supply of fuel for a turbine-driven fracturing pump system used in hydraulic fracturing may be configured to identify when the supply pressure of primary fuel to a plurality of gas turbine engines of a plurality of hydraulic fracturing units falls below a set point, identify a gas turbine engine of the fleet of hydraulic fracturing units operating on primary fuel with highest amount of secondary fuel available, and to selectively transfer the gas turbine engine operating on primary fuel with the highest amount of secondary fuel from primary fuel operation to secondary fuel operation. Some methods and systems may be configured to transfer all gas turbine engines to secondary fuel operation and individually and/or sequentially restore operation to primary fuel operation and/or to manage primary fuel operation and/or secondary fuel operation for portions of the plurality of gas turbine engines.

GAS TURBINE COMBUSTOR APPARATUS

A gas turbine combustor apparatus comprising plural combustors and plural fuel supply systems realizes a combustion of a lean and uniform pre-mixture in each of the combustors to thereby enable to reduce NOx generation. Flow regulating valves 29, 30 are provided in fuel supply systems 23, 24, respectively, that supply combustors 25, 26 with fuel. Pressure gauges 31, 32 are provided in the fuel supply systems 23, 24, respectively, in front of inlets of the combustors 25. 26. The flow regulating valves 29, 30 are controlled so that pressures measured by the pressure gauges 31, 32 become the same.

AUTOMATED TUNING OF MULTIPLE FUEL GAS TURBINE COMBUSTION SYSTEMS

Method for automated control of the gas turbine fuel composition through automated modification of the ratio of fuel gas from multiple sources The method includes providing first and second fuel sources, sensing the operational parameters of a turbine, determining whether the operational parameters are within preset operational limits and adjusting the ratio of the first fuel source to the second filet source, based on whether the operational parameters are within the preset operational limits.

DUAL FUEL AIRCRAFT SYSTEM AND METHOD FOR OPERATING SAME

A dual fuel propulsion system 100 is disclosed including a gas turbine engine 101 capable of generating a propulsive thrust using a cryogenic liquid fuel 1 12. A method of operating an aircraft engine 101 is disclosed using a selected proportion of a first fuel 1 1 and a second fuel 12 during selected portions of a flight profile 120 to generate hot gases that drive a gas turbine engine 101.

Regeleinrichtung für den Brenner einer Gasturbinenbrennkammer für die gleichzeitige Verbrennung eines gasförmigen und eines flüssigen Brennstoffes

Vorrichtung zum Begrenzen des Brennstoff-Luft-Verhältnisses bei Gasturbinenanlagen mit kontinuierlicher Verbrennung.

Verfahren zum Hochfahren einer Gasturbinenanlage

Brennstoffregeleinrichtung für Gasturbinentriebwerke

Verfahren zur Erzeugung der erforderlichen Zusatzleistung durch Einführung eines zusätzlichen Betriebsmittels in eine Gasturbinenanlage bei Entnahme von Druckluft aus derselben sowie Einrichtung zur Ausübung dieses Verfahrens

Verfahren und Vorrichtung zum Steuern von einem Paar durch Servomotoren angetriebener Ventile in der Fluidumzufuhr einer mit zwei Fluiden z. B. Brennstoffen betreibbaren Anlage

Einrichtung zur Steuerung der Brennstoffzufuhr zu einer Gasturbinenanlage

Procedure for the enterprise of a gas turbine.

Die vorliegende Erfindung betrifft ein Verfahren zum Betrieb einer Gasturbine die wahlweise mit einem Gasbrennstoff (A) eines Gasmassenstroms und/oder mit einem Ölbrennstoff (B) eines Ölmassenstroms betrieben wird, wobei ein Wechsel zwischen einer Betriebsart mit dem Gasbrennstoff (A) mit einem unteren Heizwert (LHV gas ) und einer Betriebsart mit dem Ölbrennstoff (B) mit einem unteren Heizwert (LHV oil ) im Lastbetrieb der Gasturbine vorgenommen wird, und wobei wenigstens in der Betriebsart mit dem Ölbrennstoff (B) ein Wasserzusatz (11) eines Wassermassenstroms) vorgesehen ist. Erfindungsgemäss ist vorgesehen, dass das Wassermassenstromverhältnis (m H2O RATIO bzw. norm ) des zugesetzten Wassermassenstroms bezogen auf den Brennstoffmassenstrom beim Wechsel zwischen den Betriebsarten mit dem normierten Heizwert (LHV norm ) bestimmt wird zu ...

Procedure for steering a turbine, which has several parallel arranged fuel valves.

Es ist ein Brennstoffsystem (2) vorgestellt. Das Brennstoffsystem (2) umfasst mehrere parallel angeordnete Brennstoffsteuerventile (80, 90) und ein Steuergerät (100). Das Steuergerät (100) ist ausgelegt zum Öffnen jedes der Brennstoffsteuerventile (80, 90), um eine untere steuerbare Brennstoff-Durchflussmenge durch jedes Brennstoffsteuerventil (80, 90) hindurchzulassen, und zum weiteren Öffnen eines der Brennstoffsteuerventile (80) als Reaktion auf ein Steuersignal zum Steuern der Turbine (6).

Procedure for the supply of turbine fuels of different quality intended for the burn.

Beim Betrieb einer Gasturbine (2) kann ein Unterschied zwischen dem gewünschten Heizwert des Kraftstoffs und den tatsächlichen Anforderungen an den Kraftstoff bestehen, die für eine kontinuierliche Verbrennung in verschiedenen Stadien des Turbinenbetriebs erforderlich sind. Der Betrieb der Gasturbine (2) wird an der unteren Entflammbarkeitsgrenze ohne das Risiko des mageren Verlöschens ermöglicht, indem das Kraftstoff-Luft-Verhältnis des Kraftstoffs und die Eigenschaften des Kraftstoff-Luft-Gemisches auf der Basis der Betriebsanforderungen der Turbine (2) und der Entflammbarkeit der Kraftstoffkomponenten angepasst werden.

gas turbine drive machinefuel supply systems for a.

Es wird ein Brennstoffzuführungssystem (200) für eine Gasturbinenantriebsmaschine bereitgestellt. Das Brennstoffzuführungssystem (200) weist einen primären Brennstoffkreis (202) auf, der dafür eingerichtet ist, ständig Brennstoff an jede von den mehreren Brenneranordnungen (206) während eines ersten Betriebsmodus und eines zweiten Betriebsmodus zu liefern. Wenigstens ein sekundärer Brennstoffkreis (204) des Brennstoffzuführungssystems (200) ist dafür eingerichtet, jedem von den mehreren Brenneranordnungen (206) Brennstoff während des zweiten Betriebsmodus zuzuführen. Der sekundäre Brennstoffkreis weist wenigstens ein Trennventil (215) auf, das mit jeder von den mehreren Brenneranordnungen (206) in Strömungsverbindung verbunden ist. Das wenigstens eine Trennventil (215) ermöglicht die Verhinderung eines Fluidstroms stromaufwärts in den sekundären Brennstoffkreis (204) während des ersten Betriebsmodus. Das Brennstoffzuführungssystem ersetzt durch die Nutzung des Trennventils (215) ein Spülsystem ...

SYSTEM AND METHOD OF OPERATION OF COMBUSTION CHAMBER VARIABLE FUEL FOR GAS TURBINE

Gas turbine apparatus, low calorie content gas feeding apparatus, and method of suppressing rise of calorie content of the gas

A gas turbine apparatus, a low calorie content gas feeding apparatus capable of feeding a low calorie content gas as a fuel for gas turbine stabilized by suppressing the sudden rise of its calorie content, and a method of suppressing the rise of calorie content of the gas. The low calorie content gas feeding apparatus comprises a low calorie content gas feed pipe (3) feeding the low calorie content gas to a gas turbine (2), an exhaust gas feed pipe (4) feeding exhaust gas to the low calorie content gas feed pipe (3), a first mixer (6) disposed in a connection part between the low calorie content gas feed pipe (3) and the exhaust gas feed pipe (4), a calorimeter (11) disposed in the low calorie content gas feed pipe (3) and detecting a heated value in the gas, an oxygen analyzer (15) installed on the downstream side of the first mixer (6) in the low calorie content gas feed pipe (3), and a controller (100). The controller (100) feeds the exhaust gas from the exhaust gas feed pipe (4) when ...

Gas turbine combustor and method of operating the same

The fuel spray nozzle

DEVICE AND PROCESS OF PURGING FOR SYSTEM Of LIQUID FUEL INJECTION IN a GAS TURBINE

Dispositif de purge d'un dispositif d'alimentation (12) en combustible liquide d'une turbine à gaz comprenant une chambre de combustion (7) apte à être alimentée alternativement en combustible gazeux et liquide, comprenant un circuit d'air de purge (17) comportant un collecteur (21) apte à distribuer l'air dans la chambre de combustion (7), et au moins un moyen de régulation (19) de la pression de l'air dans le circuit de purge (17). Le dispositif de purge comprend une unité de commande électronique (26) permettant de réguler la pression et le débit d'air dans le circuit de purge (17) selon le mode de fonctionnement de la turbine à gaz.

SPHERICAL GATE VALVE, PARTICULARLY FOR A GAS TURBINE

La vanne, notamment pour turbine, comprend un corps 12 de vanne, au moins des premier, deuxième et troisième conduits d'amenée 14, 16, 18 de fluide disposés sur le corps de vanne, au moins un conduit de sortie 20 disposé sur le corps de vanne, et un obturateur 22 sphérique mobile à rotation à l'intérieur du corps de vanne et comprenant des premier et deuxième canaux de distribution 26, 28 agencés sur ledit obturateur de manière à pourvoir raccorder sélectivement le conduit de sortie 20 à un des conduits d'amenée 14, 16, 18 lors de la rotation de l'obturateur.

GAS TURBINE APPARATUS, LOW CALORIE CONTENT GAS FEEDING APPARATUS, AND METHOD OF SUPPRESSING RISE OF CALORIE CONTENT OF THE GAS

A gas turbine apparatus, a low calorie content gas feeding apparatus capable of feeding a low calorie content gas as a fuel for gas turbine stabilized by suppressing the sudden rise of its calorie content, and a method of suppressing the rise of calorie content of the gas. The low calorie content gas feeding apparatus comprises a low calorie content gas feed pipe (3) feeding the low calorie content gas to the gas turbine (2), an air feed pipe (4) feeding air to the low calorie content gas feed pipe (3), a first mixer (6) disposed in a connection part between the low calorie content gas feed pipe (3) and the air feed pipe (4), a calorimeter (11) disposed in the low calorie content gas feed pipe (3) and detecting a heated value in the gas, an oxygen analyzer (15) installed on the downstream side of the first mixer (6) in the low calorie content gas feed pipe (3), and a controller (50). The controller (50) feeds the air from the air feed pipe (4) when the detection value of the calorimeter ...

GAS TURBINE IMPROVING COMBUSTION EFFICIENCY AND REDUCING POLLUTANT

The present invention relates to a gas turbine reducing discharge of a pollution such as NOx and improving combustion efficiency. According to the present invention, the gas turbine induces MILD combustion maintaining a flame in a stable state by mixing combustion gas, which is inert gas and is at high temperature in comparison with general air by recirculation of the combustion gas, with air for combustion and supplying the mixed combustion gas to a combustor when the air for the combustion is supplied to the combustor of the gas turbine. The gas turbine efficiently dilutes oxygen concentration of the air for the combustion in short time and heats the air for combustion at high temperature by mixing the combustion gas at the high temperature, which is sucked (or is guided) by supplied air, with the air for the combustion supplied, using Coanda effect when mixed gas of the air for the combustion and the combustion gas is supplied to the combustor. The gas turbine reducing the pollution ...

GAS TURBINE COMBUSTOR AND OPERATING METHOD THEREOF

Provided is a gas turbine combustor (3) equipped with a fuel injection device (15) that has a plurality of annular fuel injection parts (25), each having numerous fuel injection ports (25a) formed therein, the gas turbine combustor being provided with: an auxiliary fuel introduction channel (41) which introduces, into the fuel injection device, an auxiliary fuel (AF) to be supplied to an auxiliary fuel injection part (25A), which is a part of the plurality of annular fuel injection parts (25); a first main fuel introduction channel (43) which is provided with a flow regulating valve (51) and which introduces, into the fuel injection device, a main fuel (MF) to be supplied to main fuel injection parts (25B) which are the annular fuel injection parts other than the auxiliary fuel injection part; and a second main fuel introduction channel (45) which is provided with a flow regulating valve (53) and which introduces, into the fuel injection device, a main fuel (MF) to be supplied to the auxiliary ...

GASIFYING COMPLEX POWER GENERATION SYSTEM, CONTROL METHOD THEREFOR, FUEL GAS PRODUCING METHOD

A complex power generation system (25) for generating power by rotating a gas turbine with a fuel gas produced at a gasifying facility provided with a gasifying furnace (23) for producing a fuel gas, comprising, in order for a gasifying facility to produce a fuel gas necessary for the complex power generation system (25) according to a power generation load requirement, a waste time compensation circuit (71) for compensating for waste time and control lag produced while a fuel gas is supplied from the gasifying facility to the complex power generation system, in addition to control for feed-forward controlling the gasifying facility, whereby the gasifying facility is zero-flare-operated. In addition, a waste time compensation circuit (46) is provided to let the complex power generation system (25) follow-up operate with a constant delay by delaying a power generation load requirement to the complex power generation system (25) based on waste time and control lag existing in the gasifying ...

METHOD FOR OPERATING A GAS TURBINE GROUP

According to the invention, continuously prevailing fuel gas properties (XG) are measured during the operation of a gas turbine group. The C2+ alkane content of the fuel gas is of particular interest, as it has a considerable influence on the ignition performance of the fuel gas in the combustion chamber. According to the invention, the operating parameters of the gas turbine group are directly influenced by the measured fuel gas properties. In a gas turbine group with sequential combustion, for example, especially the distribution of the fuel mass flows (mEV, mSEV) between the combustion chambers (4, 8) of the gas turbine group varies. Furthermore, when inert media, such as water or steam, are to be introduced, the inert media mass flow (mST) can be controlled according to the measured fuel properties.

METHODS AND SYSTEMS FOR SUPPLYING FUEL TO GAS TURBINE ENGINES

Methods and systems for supply of fuel for a turbine-driven fracturing pump system used in hydraulic fracturing may be configured to identify when the supply pressure of primary fuel to a plurality of gas turbine engines of a plurality of hydraulic fracturing units falls below a set point, identify a gas turbine engine of the fleet of hydraulic fracturing units operating on primary fuel with highest amount of secondary fuel available, and to selectively transfer the gas turbine engine operating on primary fuel with the highest amount of secondary fuel from primary fuel operation to secondary fuel operation. Some methods and systems may be configured to transfer all gas turbine engines to secondary fuel operation and individually and/or sequentially restore operation to primary fuel operation and/or to manage primary fuel operation and/or secondary fuel operation for portions of the plurality of gas turbine engines. 122.-. (canceled)23. A system for supplying fuel to a plurality of gas turbine engines , the system comprising:a primary sensor associated with the plurality of gas turbine engines, the primary sensor configured to generate a primary signal indicative of an ability of a primary fuel source to supply an amount of primary fuel sufficient to operate the plurality of gas turbine engines at a first output;a plurality of secondary sensors, each of the plurality of secondary sensors associated with one of the plurality of gas turbine engines and configured to generate a secondary signal indicative of an amount of secondary fuel available from a secondary fuel supply associated with each of the plurality of gas turbine engines; and determine, based at least in part on the primary signal, that the primary fuel source is supplying an insufficient amount of the primary fuel to operate one or more of the plurality of gas turbine engines at the first output;', 'determine, based at least in part on the secondary signals, that the amount of secondary fuel available from ...

INDUSTRIAL GAS TURBINE POWER PLANT CONTROL SYSTEM HAVING CAPABILITY FOR EFFECTUATING AUTOMATIC FUEL TRANSFER UNDER LOAD PREFERABLY EMPLOYING A DIGITAL COMPUTER

System and method for operating a gas turbine electric power plant with bypass flow fueling operation to provide improved reliability and extended apparatus life

A gas turbine electric power plant is provided with an industrial gas turbine which is operated by a computer control system. The gas turbine is provided with a liquid fuel system having a turbine driven pump which supplies fuel to turbine nozzles through a throttle valve. A bypass pump pressure regulator valve and a bypass pressure temperature limiter valve function together to provide stable fuel pressure operation and stable turbine inlet air temperature operation during ignition and other turbine operating periods. Such bypass means are operated substantially independently of the control system.

INTEGRATED FUEL GAS HEATER FOR MOBILE FUEL CONDITIONING EQUIPMENT

A system mounted on a skid for use in fracturing operations is disclosed along with an associated method. The system includes a line heater on the skid to enable heating of fuel to be used with a turbine generator and includes one or more pressure regulators coupled to the line heater to enable adjustment of a pressure associated with the fuel.

Gasification power plant control device, gasification power plant, and gasification power plant control method

This IGCC plant is provided with an ASU which separates oxygen gas and nitrogen gas from air, a coal gasification furnace which uses an oxidizing agent to gasify coal, and a gas turbine which is driven by the combustion gas resulting from burning a gas generated by means of the coal gasification furnace. This IGCC plant control device (50) is provided with an air separation amount determination unit (52) which determines the production amount of nitrogen gas produced by the ASU depending on the operating load of the IGCC plant, and supplies to the coal gasification furnace the entire amount of oxygen gas generated as a byproduct in response to the determined nitrogen gas production amount. By this means, the IGCC plant can minimize blow-off of oxygen gas produced from the air.

METHOD OF CONTROLLING A DEVICE FOR SUPPLYING A PROPULSION SYSTEM OF AN AIRCRAFT AND SUPPLY DEVICE ENABLING EXECUTION OF THAT METHOD

A method of controlling a fuel supply device of at least one aircraft propulsion system. The method includes a step of determining the state of the fuel flowrate control system following a change of state that has moved it away from an initial state, a step of modifying the pressure of the fuel as a function of the state of the fuel flowrate control system that has been determined, and a step of changing the state of the fuel flowrate control system to return it to or toward the initial state.

LIQUID FUEL SYSTEM FOR A TURBOMACHINE

Liquid fuel systems and methods are provided. A liquid fuel system includes a mixing unit and a plurality of liquid fuel supply systems. Each liquid fuel supply system is fluidly coupled to the mixing unit. The liquid fuel system further includes a controller communicatively coupled to the mixing unit and the plurality of liquid fuel supply systems. The controller includes memory and one or more processors. The memory stores instructions that when executed by the one or more processors cause the liquid fuel system to perform operations including providing one or more liquid fuels from the plurality of liquid fuel supply systems to the mixing unit. The operations further include mixing, with the mixing unit, the one or more liquid fuels to create a liquid fuel mixture. The operations further include providing the liquid fuel mixture to a combustion section of a turbomachine.

Systems and methods for controlling fuel flow to a turbine component

Systems (200) and methods (300) for controlling fuel flow to a turbine component are provided. One or more parameters associated with a fuel flow to a turbine component may be monitored. The fuel flow may be modeled based at least in part on the one or more monitored parameters. The fuel flow may be adjusted to a target flow based at least in part on the modeling of the fuel flow.

SYSTEMS AND METHODS FOR FUEL CELL AUXILIARY POWER IN SECONDARY FUEL APPLICATIONS

A cryogenic fuel auxiliary power system (200) for an engine (20) may include a cryogenic fuel supply (210), a first valve (212) in fluid communication with the cryogenic fuel supply and configured to control a fuel flow, a first heat exchanger (234), configured to receive the fuel flow, in fluid communication with the first valve and a combustion chamber of the engine, and a fuel cell (220) in fluid communication between the first valve and the first heat exchanger.

FUEL DELIVERY SYSTEM AND METHOD FOR A COMBUSTOR

A fuel delivery system 200 for a combustor is provided. The combustor includes a plurality of burners 114, and each burner includes a pilot injector 202 and a premix injector 201. The fuel delivery system includes a controller 208 operatively coupled to, and configured to selectively activate and deactivate, each premix injector and each pilot injector of the plurality of burners. The controller is programmed to operate each pilot injector of a subset 412 of the plurality of burners in an activated state during a high load phase of the combustor. The subset includes more than zero, but fewer than all of the plurality of burners.

Methods for controlling fuel mixing

SYSTEM, METHOD AND ELECTRONIC CONTROL UNIT FOR METERING THE FUEL SUPPLY TO A COMBUSTION INSTALLATION OPERATING ON MORE THAN ONE TYPE OF FUEL

In order to supply a combustion installation, such as an internal combustion engine (1), with a second type of fuel, in particular LPG, in addition to a first type of fuel, such as petrol, a second control unit (12) is coupled to the first or original electronic control unit (8) of the engine. In response to first control signal values emitted by the first control unit (8), said second control unit (12), during operation on LPG, emits second control signal values for metering the LPG supply. With this arrangement the first control signal values received from the first control unit (8) are compared with the values recorded by the second control unit (12) during operation on petrol. The second control signal values emitted by the second control unit (12) are now so adjusted that, during operation on LPG, the first control signal values are still kept within a predetermined range (operating range) of the first control signal values recorded during operation on petrol.

GAS TURBINE CONTROL DEVICE

PURPOSE: To sufficiently display a NOx reducing effect by preventing instability of switching action for opening/closing a valve when fuel is switched, and suppressing an error to a minimum limit of a distribution characteristic of fuel. CONSTITUTION: A fuel control valve 20 is provided in a fuel supply path 5, the downstream of this valve branches to first/second supply paths 21, 22, the first/second fuel distributing valves 23, 24 are interposed respectively in these first/second supply paths 21, 22, the first supply path 21 in the downstream of this first fuel distributing valve 23 is connected to a diffusion fuel system and pilot premixing fuel system at high load time of a combustor 4, a three-way switching valve 25 is interposed in the second supply path 22 in the downstream of the second fuel distributing valve 24, and two downstream branch paths of this three-way switching valve 25 are respectively connected to a diffusion fuel system and main fuel system at the time of low load ...

FUEL FEEDING DEVICE FOR GAS TURBINE COMBUSTOR

PROBLEM TO BE SOLVED: To surely prevent accidental fire of fuel gas and feed the gas fuel in a stable state by providing a means treating the fuel drain in a fuel system unused during operation of a gas turbine combustor out of a plurality of fuel systems using at least one of a single type of different types of fuel. SOLUTION: This fuel feeding device is provided with a main fuel feeding system, a first sub fuel feeding system 29a which is bypassed therefrom and feeds a high-pressure gas fuel to a first sub nozzle 28a of a gas turbine combustor 18, and a second sub fuel feeding system 29b which is bypassed from the first sub fuel feeding system 29a and feeds the high-pressure gas fuel to a second sub nozzle 28b of the gas turbine combustor 18. The fuel feeding device is provided with a fuel drain treatment system 29a bypassed from the first sub fuel feeding system 29a. The drain treatment system 30 is provided with drain pot 33 which temporarily collects gas fuel drain accumulated in a ...

添加剤送給システム及び方法

GAS TURBINE

PURPOSE: To ensure the supply of gas fuel in an optimum amount at all times and the stable burning thereof by mounting a torque converter between a steam turbine and an increasing gear in a gas turbine for combined cycle power generation, and changing the speed of a gas fuel compressor. CONSTITUTION: A combined cycle power generation system is so made as to operate a generator 4 on a gas turbine 3 and a steam turbine 5. In this case, the drive shaft 6a of a gas fuel compressor 6 is coupled to an increasing gear 8 and a torque converter 41 is mounted between the increasing gear 8 and the steam turbine 5 as coaxially arranged with the gas turbine 3. Also, the oil feed line 42 of the torque converter 41 is fitted with an adjusting valve 43. And the amount of feed oil into the torque converter 41 is regulated with the adjusting valve 43 and a ratio of rotary speeds is adjusted between the input and output shafts 41a and 41b of the torque converter 41, thereby changing the speed of the gas fuel ...

GAS TURBINE COMBUSTOR

PURPOSE: To lower the smoke level of gas turbine exhaust at the time of a high load operation including a rated load. CONSTITUTION: In a gas turbine combustor designed in such a constitution that liquid fuel 7 is burnt in a combustor inner cylinder 1 to film-cool the inner wall of the combustor inner cylinder 1 by cooling air 10, liquid fuel 7 and gas fuel 11 are mixed together and burnt at the time of a high load operation including a rated load. COPYRIGHT: (C)1994,JPO&Japio ...

FUEL CONTROLLER FOR GAS TURBINE

PURPOSE: To prevent the variation of output for an arbitrary mixing ratio by controlling a flow rate adjusting valve on the basis of the calorific power, specific gravity of each fuel, and the mixing ratio of the both fuels, in the use of two kinds of fuels having different calorific power. CONSTITUTION: After two kinds of fuels A and B having different calorific power are mixed in a prescribed mixing ratio in a mixing valve 3, and the flow rate of the mixed fuel is supplied into a conbustor by the control by a flow rate adjusting valve 4. The mixing valve 3 performs feedback control so that the measured mixing ratio RM calculated from the fuel flow rate QAM and QBM measured by the flow rate meters 1 and 2 becomes a prescribed mixing ratio Rs. The flow rate adjusting valve 4 performs feedback control so that the measured flow rate QM becomes a set flow rate Qs. The set flow rate Qs is obtained through the calculation from the volume heat generation coefficients XA and XB of the fuels A ...

GAS TURBINE CONTROL DEVICE

PURPOSE: To stably maintain the flame inside a combustor by making a minimum fuel control signal variable by the density of gas fuel, and also by detecting the position of a gas-fuel distributing valve for changing over the minimum fuel control signal. CONSTITUTION: When fuel becomes lean after a load has been cut off, a gas-fuel analyzing device 15 detects the density of gas fuel, and a function generator 16 increases the value of a minimum fuel request signal 8. Consequently, a gas-fuel control valve 9 supplies more gas fuel to a combustor 7, and a stable flame can be obtained in the inside of the combustor 7. When a gas turbine is operated while using both primary and secondary combustion chambers 7-1, 7-2, if the load is cut off, the signal 8 is selected by a high-value priority circuit 6, thereby the control valve 9 is controlled. In this case, a gas-fuel distributing valve 10 is operated, and a bias is added to the signal 8 by a bias generator 17 until such a condition that fuel is ...

СПОСОБ И УСТРОЙСТВО ДЛЯ ВЫРАВНИВАНИЯ КОЛЕБАНИЙ СОСТАВА ТОПЛИВА В ГАЗОТУРБИННОЙ УСТАНОВКЕ

В способе для выравнивания колебаний состава топлива в газотурбинной установке с, по меньшей мере, двумя параллельно эксплуатируемыми ступенями горелок в качестве реакции на колебания состава топлива производят регулирование подачи топлива к, по меньшей мере, двум из ступеней горелок, причем при регулировании подачи топлива устанавливают разделение топлива между ступенями горелок, то есть относительное распределение топлива по ступеням горелок, на целевое значение или поддерживают на целевом значении. При этом целевое значение может быть, например, постоянной величиной или функцией одной или нескольких переменных. В частности, газотурбинная установка может содержать запальную ступень горелок и главную ступень горелок, причем при регулировании подачи топлива разделение топлива между запальной и главной ступенью горелок устанавливают на целевое значение или поддерживают на целевом значении. Технический результат - эффективно исключить повышенные выбросы или колебания горения при выравнивании ...

СПОСОБ И УСТРОЙСТВО ДЛЯ УПРАВЛЕНИЯ ПОДАЧЕЙ ТОПЛИВА ДЛЯ ГАЗОВОЙ ТУРБИНЫ

Изобретения относятся к способу и устройству для управления подачей топлива в камеру сгорания газовой турбины, содержащей компрессор выше по потоку относительно камеры сгорания, при этом способ содержит подачу топлива в камеру сгорания; получение значения свойства для по меньшей мере одного физического свойства (PT8, PT7, Tinlet, THBOV) воздуха, используемого для сжигания топлива в камере сгорания; оценивание тепловыделения (HIengmodel) топлива, подаваемого в камеру сгорания, на основе значения свойства; измерение калорийности (LCVmea) топлива выше по потоку относительно камеры сгорания; корректировку оцененного тепловыделения (HIengmodel) на основе измеренной калорийности (LCVmea); и управление топливным клапаном, регулирующим подачу топлива в камеру сгорания, на основе скорректированного оцененного тепловыделения (HIexpected) и требуемого тепловыделения (FFDEM). Технический результат изобретения – обеспечение стабильной работы газовой турбины. 2 н. и 17 з.п. ф-лы, 6 ил.

СПОСОБ ЭКСПЛУАТАЦИИ ГАЗО- И ПАРОТУРБИННОЙ УСТАНОВКИ И ГАЗО- И ПАРОТУРБИННАЯ УСТАНОВКА

Изобретение относится к области теплоэнергетики. Способ эксплуатации газо- и паротурбинной установки, в котором тепло, содержащееся в расширенной рабочей среде соответствующей газовой турбины, работающей на газе и на жидком топливе, используют для получения пара для соответствующей паровой турбины, содержащей по меньшей мере одну ступень высокого давления. При этом параллельно подогревателю питательной воды ступени высокого давления включен обводной трубопровод с включенным в него вентилем, который регулируется в зависимости от температуры конденсата, подводимого к ступени высокого давления. Изобретение позволяет повысить кпд. 2 с. и 2 з.п.ф-лы, 1 ил.

БЕСПРОВОДНАЯ ОТКАЗОУСТОЙЧИВАЯ ЭЛЕКТРОННАЯ СИСТЕМА УПРАВЛЕНИЯ ГАЗОТУРБИННЫМ ДВИГАТЕЛЕМ

Беспроводная отказоустойчивая электронная системы управления газотурбинным авиадвигателем, включающая цифровой блок управления, исполнительный механизм регулирования расхода топлива, устройство управления проточной частью газодинамического тракта авиадвигателя и электромагнитные клапаны, при этом цифровой блок управления соединен с исполнительным механизмом регулирования расхода топлива, устройством управления проточной частью газодинамического тракта авиадвигателя и с электромагнитными клапанами, отличающаяся тем, что она дополнительно снабжена комплектом беспроводных интеллектуальных датчиков параметров авиадвигателя, беспроводным рычагом управления, беспроводным пультом управления и индикации, радиомодулем приема и диспетчеризации информации, узлом комплексирования информации, блоком вычисления эталонных значений параметров авиадвигателя, анализатором состояния и замещения информации, беспроводным модулем передачи информации, при этом выходы комплекта беспроводных интеллектуальных датчиков ...

СИСТЕМА (ВАРИАНТЫ) И СПОСОБ СОЗДАНИЯ ОБОГАЩЕННОГО ВОДОРОДОМ ТОПЛИВА

... 1. Система для создания обогащенного водородом топлива, содержащаяa) первую газовую турбину, содержащуюi) первый компрессор, выполненный с возможностью создания первой сжатой рабочей текучей среды,ii) камеру сгорания, расположенную ниже по потоку от первого компрессора,iii) первую турбину, расположенную ниже по потоку от камеры сгорания,b) вторую газовую турбину, содержащуюi) второй компрессор, проточно сообщающийся с первым компрессором с возможностью приема части первой сжатой текучей среды из первого компрессора и выполненный с возможностью создания второй сжатой рабочей среды, имеющей более высокое давление по сравнению с первой сжатой рабочей текучей средой,ii) топливный компрессор, проточно сообщающийся с источником топлива и имеющий впускное отверстие и выпускное отверстие, причем топливный компрессор выполнен с возможностью приема топлива через указанное впускное отверстие из источника топлива под первым давлением и с первой температурой и создания сжатого топлива под более высоким ...

ГАЗОВАЯ ТУРБИНА ВНУТРЕННЕГО СГОРАНИЯ

Газовая турбина внутреннего сгорания, содержащая ротор с полым валом и камерами сгорания, ограниченными внутренними поверхностями газовых сопел, равномерно расположенных на статоре, корпус с патрубками подачи рабочего тела, отвода отработанных газов и газораспределительным коллектором в полости вала, на патрубках отвода отработанных газов установлены клапана с механизмами регулировки, отличающаяся тем, что, с целью использования воды в качестве топлива, на приводном конце полого вала установлена спираль винтового насоса с патрубком для подачи воды, а в стенках камер внутреннего сгорания установлены продольные парообразовательные каналы, на выходном конце каналы соединены с камерой радиолиза пара и последовательно с системой сепаратора, аккумулятoра гремучей смеси, эжектора для смешения компонента с воздухом и подачи в каналы камер.

Устройство для автоматического регулирования скорости газотурбинной установки

Verfahren zum Betreiben einer Gasturbinenvorrichtung, Gasturbinenvorrichtung und Verwendung einer Gasturbinenvorrichtung zur Abgasreinigung

Um ein Verfahren zum Betreiben einer Gasturbinenvorrichtung zu schaffen, welches eine einfache und/oder kompakte Ausgestaltung sowie eine energieeffiziente Nutzung der Gasturbinenvorrichtung zur Rohgasreinigung ermöglicht, wird vorgeschlagen dass das Verfahren zum Betreiben der Gasturbinenvorrichtung Folgendes umfasst:Umsetzen von Brennstoff mit Oxidator in einer Brennkammer der Gasturbinenvorrichtung, wodurch ein Brennergasstrom erhalten wird, der aus der Brennkammer herausströmt; undZuführen eines Turbinengasstroms, welcher den Brennergasstrom teilweise oder vollständig umfasst, zu einer Kühlvorrichtung zum Abkühlen des Turbinengasstroms, bevor der Turbinengasstrom einer Turbinenvorrichtung zugeführt wird.

INDUSTRIAL GAS TURBINE POWER PLANT HAVING CAPABILITY FOR EFFECTUATING AUTOMATIC FUEL TRANSFER UNDER LOAD EMPLOYING A DIGITAL COMPUTER

... 1410526 Automatic control of gas turbines WESTINGHOUSE ELECTRIC CORP 20 Nov 1972 [6 Dec 1971] 53479/72 Heading G3N A gas turbine electric power plant having a plural fuel supply sub-system is controlled by system comprising a digital computer and an associated external circuit means which determines the ratio between fuel control signals. During a change of turbine operation from one fuel to another the control system derives a signal representing computed total fuel demand and a time varying ratio of fuels to satisfy the demand, which are applied to the circuit means to derive individual control signals for each of the plural fuel sub-systems.

Gaseous fuel compression and control system for gas turbine engine

BIOMASS COMBUSTION CHAMBER FOR A GAS TURBINE

MODULAR FUEL CONDITIONING SYSTEM

Combustion device and gas turbine

Provided is a combustion device equipped with: an ammonia supply unit (6) that, by supplying primary reduction ammonia as a nitrogen oxide reducing agent to within a combustor (2) and mixing secondary reduction ammonia with combustion exhaust gas discharged from the combustor (2), reduces nitrogen oxides within the combustion exhaust gas; and a control device (9) that controls at least either the supply amount of the primary reduction ammonia or the mixing amount of the secondary reduction ammonia with the combustion exhaust gas, in accordance with the concentration of residual nitrogen oxides and the concentration of residual ammonia included in the combustion exhaust gas after being discharged from the combustor (2).

Method of controlling a test apparatus for a gas turbine engine and test apparatus

The method allows to control a test apparatus for a gas turbine engine; WI values of one or more tentative fuel gas mixtures are predicted by calculations and the predicted WI values are used for setting the composition of a fuel gas mixture to be supplied to a combustor of a gas turbine (GT) engine under test. The test apparatus (1) comprises: a first supply flow line (11) for fuel gas; a second supply flow line (21) for inert gas; a mixer (30) with a first inlet for fuel gas and a second inlet for inert gas, and with an outlet (31) for supplying the mixture of fuel gas and inert gas to the combustor; a set of meters (12, 13, 14, 22, 23, 24, 25); and a flow control device (40) for the inert gas.

FUEL DELIVERY APPARATUS

GAS TURBINE FUEL SUPPLY METHOD AND ARRANGEMENT

Gas turbine fuel supply method and arrangement It is described a method of controlling a supply of a fuel to a combustor of a gas turbine comprising a compressor upstream of the combustor, the method comprising: supplying the fuel (105) to the combustor (101); obtaining an inlet air pressure (PT7) at a compressor inlet; obtaining an inlet air temperature (Tinlet) at the compressor inlet; obtaining an outlet air pressure (PT8) at a compressor outlet; estimating a heat input (HIengmodel, HIexpected) of the fuel (105) supplied to the combustor (101) based on the inlet air pressure (PT7), the inlet air temperature (Tinlet) and the outlet air pressure (PT8); comparing the estimated heat input (HIengmodel, HIexpected) with a demanded heat input (FFDEM) to derive an error signal (121); and controlling a fuel valve (103) regulating the supply of the fuel (105) to the combustor (101) based on the error signal (121).

TURBINE ENGINE ASSEMBLY AND DUAL FUEL AIRCRAFT SYSTEM

A turbine engine assembly (101) and dual fuel aircraft system having a cryogenic fuel system (500), having a cryogenic fuel reservoir (502), a vaporizer heat exchanger (504), a liquid supply line (506) operably coupling the fuel reservoir to an input of the vaporizer heat exchanger, a gas supply line (508) operably coupling an output of the vaporizer heat exchanger to the combustion section, and a second heat exchanger (510) thermally connecting the liquid supply line and the gas supply line to transfer heat from the gas supply line to the liquid supply line.

METHOD AND ARRANGEMENT FOR CONTROLLING FUEL SUPPLY FOR A GAS TURBINE

It is described a method of controlling a supply of a fuel (105) to a combustor (101) of a gas turbine comprising a compressor upstream of the combustor, the method comprising: supplying the fuel (105) to the combustor (101); obtaining a property value of at least one physical property (PT8, PT7, Tinlet, THBOV) of air used for burning the fuel (105) in the combustor (101); estimating a heat input (HIengmodel) of the fuel (105) supplied to the combustor (101) based on the prop- erty value; measuring a Caloric Value (LCVmea) of the fuel (105) upstream of the combustor (101); adjusting the estimated heat input (HIengmodel) based on the measured Caloric Value (LCVmea); and controlling a fuel valve (103) regulating the supply of the fuel (105) to the combustor (101) based on the adjusted estimated heat input (HIexpected) and a demanded heat input (FFDEM).

System, Method and Electronic Control Unit for Metering the Fuel Supply to a Combustion Installation Operating on More Than One Type of Fuel

The control to the gas turbine fuel supply method and apparatus

FUEL CIRCUIT OF ENGINE HAS GAS TURBINE FOR LIQUID OR GAS FUEL

Device of regulation for the burner of a combustion chamber of gas turbine in which the simultaneous combustion of a gaseous fuel and a liquid fuel is operated

Sophisticated system of control for compressor-turbine groups with gas, deuxarbres

FUEL CONTROL SYSTEMS FOR DUAL FUEL GAS TURBINE ENGINES

DEVICE AND PROCESS OF SWEEPING OF THE LIQUID FUEL FOR A GAS TURBINE MULTI-COMBUSTIBLES

L'invention concerne une turbine 1 comprenant au moins une chambre de combustion 2 et un dispositif de balayage, la chambre de combustion pouvant être alimentée en carburant liquide par un premier circuit 5 comportant un clapet anti-retour 9, et le dispositif de balayage comprenant : un moyen de fourniture 6 d'un gaz de balayage, et un deuxième circuit 7 pour l'alimentation en gaz de balayage, relié au premier circuit, en aval du clapet anti-retour. La turbine 1 comprend un moyen de compensation 12 comportant au moins deux entrées et capable de réduire la différence de pression entre ses deux entrées, l'une des entrées étant raccordée au premier circuit 5, en amont du clapet anti-retour, et l'autre entrée étant raccordée au deuxième circuit 7.

CONTROL DEVICE AND PROCESS OF ORDERING Of a POWER STATION OF ENERGY PRODUCTION

Method for regulating flow of fuel to be injected into combustion chamber of turbomachine of aeroplane, involves correcting setpoint position of metering valve based on difference between measurement value and set point

Le débit de carburant à injecter dans une chambre de combustion de turbomachine est réglé par asservissement de la position d'une vanne de dosage à une position de consigne fonction d'un débit massique de carburant souhaité (dmc). On corrige la position de consigne (pdc) de la vanne de dosage d'une quantité (ccp) fonction au moins de l'écart entre une valeur de mesure (dmm) représentative du débit massique effectif de carburant délivré par la vanne de dosage et une valeur de consigne (dmc') représentative du débit massique de carburant souhaité (dmc).

SYSTEM AND METHOD FOR RAPIDLY CONTROLLING AIR FUEL RATIO IN GAS ENGINE FOR SYNGAS

The present invention relates to a system and a method for rapidly controlling an air fuel ratio in a gas engine for syngas, which can improve operation characteristics of an engine by rapidly controlling an air fuel ratio in a gas engine by responding to generated syngas change characteristics. Moreover, with respect to a dynamic flow rate and a composition change of syngas generated in a gasifier, an air fuel ratio in a gas engine can be rapidly controlled. COPYRIGHT KIPO 2018 (AA) Gasifier (BB) Operation control (CC) Gasifier controller (DD) Engine operation control unit (EE) Mixer (FF) Control additional supply for a small quantity of syngas to an inhale pipe (GG) Combust an engine main body (HH) Exhaust (II) Control additional supply for a large quantity of syngas to an inhale pipe (JJ) Inject the syngas to the inhale pipe in multiple stages ...

SYSTEM FOR SUPPLYING FUEL TO GAS TURBINE COMBUSTOR AND METHOD FOR SUPPLYING FUEL TO GAS TURBINE COMBUSTOR

GAS TURBINE SYSTEM EMPLOYING STEEL PLANT GAS AS FUEL

A gas turbine system (1), employing steel plant gas as fuel, has at least a combustion air compressor (17); at least a steel plant gas compressor (6); a combustion chamber (14) which receives the compressed combustion air and compressed steel plant gas; and a turbine (20), which is driven by the exhaust gas from the combustion chamber (14) to supply mechanical energy to the combustion air compressor (17), and to a drive shaft (21) connected to the steel plant gas compressor (6) by a transmission (25); the transmission (25) has a connecting/disconnecting device (27) provided with a torque converter for disconnecting the steel plant gas compressor (6) from the drive shaft (21) while the turbine (20) is running.

SYSTEMS AND METHODS TO MAINTAIN STABILITY OF FUEL FLOW IN GAS TURBINE ENGINES

A system includes a gas turbine comprising a compressor section, combustor section, and a turbine section. The system further includes a first fuel line and a second fuel line coupled to the gas turbine. The system also includes a feed compressor disposed along the first fuel line upstream of the gas turbine. The feed compressor is configured to pressurize the first fuel provided to the gas turbine. Further, the system includes fuel flow maintenance system configured to provide a pressurized fuel to the first fuel line upstream of the feed compressor in response to an interruption in a flow of the first fuel along the first fuel line to the gas turbine that triggers a transition from the first fuel in the first fuel line to the second fuel in the second fuel line.

TURBINE ENGINE ASSEMBLY AND DUAL FUEL AIRCRAFT SYSTEM

A turbine engine assembly (101) and dual fuel aircraft system having a cryogenic fuel system (500), having a cryogenic fuel reservoir (502), a vaporizer heat exchanger (504), a liquid supply line (506) operably coupling the fuel reservoir to an input of the vaporizer heat exchanger, a gas supply line (508) operably coupling an output of the vaporizer heat exchanger to the combustion section, and a second heat exchanger (510) thermally connecting the liquid supply line and the gas supply line to transfer heat from the gas supply line to the liquid supply line.

GAS TURBINE ENGINE FUEL CONTROL SYSTEM

A fuel control system (22) having a combustive energy value evaluator (38) determining a combustive energy value of the fuel, and a controller (26) calculating a desired flow rate based at least on the combustive energy value and controlling a fuel metering device (24) such that the fuel flow rate corresponds to the desired fuel flow rate.

FUEL CONTROL SYSTEM FOR A MULTI-FUEL GAS TURBINE

Methods and systems for adaptively cooling combustion chambers in engines

The present disclosure is directed to various embodiments of systems and methods for cooling a combustion chamber of an engine. One method includes introducing fuel into the combustion chamber of an engine having an energy transfer device that moves through an intake stroke, a compression stroke, a power stroke, and an exhaust stroke. The method further includes monitoring a temperature of the combustion chamber. When the temperature reaches a predetermined value, the method also includes introducing coolant into the combustion chamber only during at least one of the power stroke and the exhaust stroke of the energy transfer device.

Fuel supply system for gas turbine combustor and fuel supply method for gas turbine combustor

A consumption amount of high-calorific gas such as coke oven gas (COG) during operation of a gas turbine is reduced, halt of the gas turbine due to clogging of a pilot system, a malfunction of a compressor which compresses high-calorific gas is prevented, and reliability of the gas turbine is improved. When operation of the gas turbine ( 11 ) starts, with use of both a first fuel supply system ( 31 ) which supplies a high-calorific fuel for a first nozzle constituting a combustor ( 17 ), and a second fuel supply system ( 32 ) which supplies a low-calorific fuel for a second nozzle constituting the combustor ( 17 ), the high-calorific fuel and the low-calorific fuel are supplied to the combustor ( 17 ), and at a time when the gas turbine ( 11 ) reaches output power which enables continuous operation with only the low-calorific fuel, supply of the high-calorific fuel to the combustor ( 17 ) is shut off, and only the low-calorific fuel is supplied to the combustor ( 17 ).

Method, apparatus and system for igniting wide range of turbine fuels

In operating a gas turbine, there can be a difference between the desired heating value of the fuel and the actual needs of the fuel for the supplied fuel to be ignited. In one aspect, fuel parameters related to the molecular weight of the fuel such as specific gravity and pressure drop are determined. Ignitability of the fuel is calculated based on the fuel parameters and adjusted as necessary to bring the fuel's ignitability to designed values. The fuel's ignitability can be calculated without actually igniting the fuel and also without direct knowledge of the fuel's calorific value or its composition.

Systems, methods, and apparatus for compensating fuel composition variations in a gas turbine

Certain embodiments of the invention may include systems and methods for compensating fuel composition variations in a gas turbine. According to an example embodiment of the invention, a method is provided for compensating for fuel composition variations in a turbine. The method can include: monitoring at least one fuel parameter associated with a turbine combustor; monitoring one or more combustion dynamics characteristics associated with the turbine combustor; monitoring one or more performance and emissions characteristics associated with the turbine; estimating fuel composition based at least in part on the at least one fuel parameter, the one or more combustion dynamics characteristics, and the one or more performance and emissions characteristics, and adjusting at least one fuel parameter based at least in part on the estimated fuel composition.

Method and system for preventing combustion instabilities during transient operations

A method and system for preventing or reducing the risk of combustion instabilities in a gas turbine includes utilizing a turbine controller computer processor to compare predetermined and stored stable combustion characteristics, including rate of change of the characteristics, with actual operating combustion characteristics. If the actual operating combustion characteristics are divergent from stable combustion characteristics then the controller modifies one or more gas turbine operating parameters which most rapidly stabilize the operation of the gas turbine.

METHOD FOR OPERATING A COMBUSTION DEVICE

A method for operating a combustion device includes supplying a fuel and an oxidizer into the combustion device and burning them. According to the method, during at least a part of a transient operation, an additional fluid is supplied together with the fuel, and its amount is regulated to counteract combustion pulsations. 151525. Method for operating a combustion device ( , , ) comprising:{'b': 35', '36', '5', '15', '25, 'supplying a fuel () and an oxidizer () into the combustion device (, , ) and burning them,'}{'b': 37', '35, 'supplying, during at least a part of a transient operation, an additional fluid () together with the fuel (), and'}{'b': '37', 'regulating the amount of the additional fluid () to counteract combustion pulsations.'}2. The method according to claim 1 , further comprising choosing a first parameter indicative of the fuel feed and supplying the additional fluid only when the fuel reaches a critical value of the first parameter.3. The method according to claim 2 , wherein the first parameter is the fuel mass flow (M).451525. The method according to claim 2 , wherein the first parameter is the differential pressure (AP) between a fuel supply and the inside of the combustion device ( claim 2 , claim 2 , ).5. The method according to claim 1 , further comprising choosing a second parameter indicative of the fuel and additional fluid feed claim 1 , the regulation including maintaining the second parameter above or below a given value or maintaining the second parameter within a prefixed range (R).6. The method according to claim 5 , wherein the given value is a critical value of the second parameter.7. The method according to claim 5 , wherein the second parameter range (R) corresponds to the critical value of the second parameter ±10% or to the critical value of the second parameter ±1% or to the critical value of the second parameter.8. The method according to claim 5 , wherein the bottom or the top of the range (R) correspond to the critical ...

TURBINE BURNER

A turbine burner is provided. The turbine burner has a secondary feed unit and a primary feed unit. The primary feed unit has a primary mixing tube and a fuel nozzle that are arranged concentrically around the secondary feed unit. The primary mixing tube and the fuel nozzle have a fluid flow connection. The fuel nozzle has an annular wall that is radially spaced in the axial direction from the secondary feed unit such that a gap height is fainted by the annular wall and the secondary feed unit. The annular wall has an inside wall directed toward the secondary feed unit and having blades with a leading edge on the upstream side. The fuel nozzle has an inlet and the blades have an axial distance from the inlet. The ratio of the distance to the gap height is greater than 1 and less than the gap height. 113.-. (canceled)14. A turbine burner , comprising:a secondary feed unit for supplying a secondary fuel or air and for discharging the secondary fuel or air from an orifice into a combustion zone; anda primary feed unit comprising a primary mixing tube and a fuel nozzle having a fuel nozzle outlet pointing into the combustion zone for supplying a primary fuel,wherein the fuel nozzle and the primary mixing tube are arranged concentrically around the secondary feed unit,wherein the primary mixing tube and the fuel nozzle have a fluid flow connection,wherein the fuel nozzle has an annular wall spaced radially apart from the secondary feed unit in an axial direction to form a gap height by the annular wall and the secondary feed unit,wherein the annular wall has an internal wall directed toward the secondary feed unit,wherein a fluid channel is between the secondary feed unit and the annular wall,wherein the fluid channel comprises blades each having a blade leading edge on an upstream side,wherein the fuel nozzle has a fuel nozzle inlet,wherein the each blade has an axial distance to the fuel nozzle inlet and a ratio of the axial distance to the gap height is greater than 1 ...

GAS TURBINE AND GAS-TURBINE PLANT HAVING THE SAME

The invention provides a gas-turbine fuel nozzle () that includes a plurality of fuel supply channels () to which fuel is supplied, a plurality of fuel/scavenging-fluid supply channels () to which fuel or a scavenging fluid for scavenging the fuel is supplied, and a plurality of injection holes () that are provided at downstream ends of the fuel supply channels () or the fuel/scavenging-fluid supply channels () and that inject the fuel guided from the fuel supply channels () or the fuel/scavenging-fluid supply channels (); a scavenging-fluid supply channel () that is connected to the fuel/scavenging-fluid supply channels () to guide the scavenging fluid; and scavenging-fluid cooling means () for cooling the scavenging fluid to a temperature lower than a self-ignition temperature of the fuel. 1. A gas turbine comprising:a gas-turbine fuel nozzle that includes a plurality of fuel supply channels to which fuel is supplied, a plurality of fuel/scavenging-fluid supply channels to which fuel or a scavenging fluid for scavenging the fuel is supplied, and a plurality of injection holes that are provided at downstream ends of the fuel supply channels or the fuel/scavenging-fluid supply channels and that inject the fuel or the scavenging fluid guided from the fuel supply channels or the fuel/scavenging-fluid supply channels;a scavenging-fluid supply channel that is connected to the fuel/scavenging-fluid supply channels and guides the scavenging fluid; andscavenging-fluid cooling means for cooling the scavenging fluid to a temperature lower than a self-ignition temperature of the fuel.2. A gas turbine according to claim 1 ,wherein the scavenging-fluid supply channel is connected to the fuel/scavenging-fluid supply channels and to a casing of the gas turbine and guides, as the scavenging fluid, a fluid extracted from the casing; andthe scavenging-fluid cooling means is a plurality of projections that are provided around the scavenging-fluid supply channel.3. A gas turbine ...

Automated tuning of multiple fuel gas turbine combustion systems

Provided herein is a method for automated control of the gas turbine fuel composition through automated modification of the ratio of fuel gas from multiple sources. The method includes providing first and second fuel sources. The method further includes sensing the operational parameters of a turbine and determining whether the operational parameters are within preset operational limits. The method also adjusting the ration of the first fuel source to the second fuel source, based on whether the operational parameters are within the preset operational limits.

METHOD FOR OPERATING A GAS TURBINE

A method for operating a gas turbine, which is optionally operated with a gaseous fuel (A) having a gaseous mass flow ({dot over (m)})and/or with an oil fuel (B) having an oil mass flow ({dot over (m)}), wherein a change between an operating mode with gaseous fuel (A) and an operating mode with oil fuel (B) is undertaken during load operation of the gas turbine, and wherein a water addition of a water mass flow ({dot over (m)}) is provided at least in the operating mode with oil fuel (B). The ratio (Ω) of the added water mass flow ({dot over (m)}) to the fuel mass flow during the change between operating modes is determined according to 2. The method of claim 1 , wherein a water mass flow ratio (Ω) is provided during a change from the first operating mode with gaseous fuel (A) to the second operating mode with oil fuel (B).3. The method of claim 1 , wherein a water mass flow ratio (Ω) is provided during a change from the second operating mode with oil fuel (B) to the first operating mode with gaseous fuel (A).4. The method of claim 2 , wherein the change from the first operating mode to the second operating mode comprises activating the water mass flow ({dot over (m)}) before feeding the oil mass flow ({dot over (m)}).5. The method of claim 3 , wherein the change from the second operating mode to the first operating mode comprises activating the water mass flow ({dot over (m)}) feeding the gaseous mass flow ({dot over (m)}).6. The method of claim 1 , wherein the gas turbine includes a guide vane arrangement claim 1 ,wherein a position of a guide vane of the guide vane arrangement remains unchanged during a change between first the operating mode and the second operating mode.7. The method of claim 1 , wherein the gas turbine in the second operating mode is configured to be operated without addition of the water mass flow ({dot over (m)}) claim 1 , and{'sub': 'H2O', 'wherein the adding of the water mass flow ({dot over (m)}) is activated for changing between the ...

BURNER ARRANGEMENT

A burner arrangement includes a carrier and at least two burners which are mounted on the carrier in a flow direction Each burner includes a cylindrical housing having a lance which is arranged centrally therein and having a fuel duct and which is supported on the housing via swirl blades. An attachment is arranged on the side leading to a combustion chamber At least one fuel nozzle is disposed in the attachment and is connected to the fuel duct. The at least two fuel nozzles of the at least two burners have a different functional characteristic and/or spray form, and the at least two fuel nozzles of the at least two burners with a different functional characteristic and/or spray form include at least one full jet nozzle and at least one pressure swirl nozzle. 110-. (canceled)11. A burner arrangement , comprising:a carrier,at least two burners which are mounted on the carrier in a flow direction, a cylindrical housing having a lance which is arranged centrally therein and having a fuel duct and which is supported on the housing via swirl blades,', 'wherein an attachment is arranged on the side leading to a combustion chamber,', 'wherein at least one fuel nozzle is disposed in the attachment and is connected to the fuel duct,, 'wherein each burner compriseswherein the at least two fuel nozzles of the at least two burners have a different functional characteristic and/or spray form.12. The burner arrangement as claimed in claim 11 , wherein for each of the burners claim 11 , the at least one fuel nozzle is arranged downstream of the swirl blades.13. The burner arrangement as claimed in claim 11 ,wherein the fuel nozzles with a different functional characteristic differ from one another at least in a nozzle size or a jet angle or liquid distribution or an atomization characteristic.14. The burner arrangement as claimed in claim 13 ,wherein, in the case of a different atomization characteristic of the fuel nozzles, at least the drop size distributions differ from one ...

DUAL FUEL AIRCRAFT ENGINE CONTROL SYSTEM AND METHOD FOR OPERATING SAME

A dual fuel engine control system comprising a first fuel control system configured to control the flow of a first fuel to an aircraft gas turbine engine, and a second fuel control system configured to control the flow of a second fuel to the aircraft gas turbine engine. 1. A dual fuel aircraft engine control system comprising:a first fuel control system configured to control the flow of a first fuel to an aircraft gas turbine engine; anda second fuel control system configured to control the flow of a second fuel to said aircraft gas turbine engine.2. The control system according to claim 1 , wherein the first fuel and the second fuel are different compositions.3. The control system according to claim 1 , wherein the first fuel is a liquid kerosene-based fuel.4. The control system according to claim 2 , wherein the second fuel is a cryogenic liquid fuel.5. The control system according to claim 2 , wherein the second fuel is Liquefied Natural Gas (LNG).6. The control system according to claim 1 , wherein the first fuel control system is a hydromechanical control system.7. The control system according to claim 1 , wherein the first fuel control system is an electronic control system.8. The control system according to claim 1 , wherein the first fuel control system is a Full Authority Digital Electronic Control (FADEC).9. The control system according to claim 1 , wherein the second fuel control system is an electronic control system.10. The control system according to claim 1 , wherein the first fuel control system and second fuel control system are integrated.11. A method of operating a dual fuel aircraft engine control system claim 1 , the method comprising:activating a first fuel control system configured to control the flow of a first fuel to an aircraft gas turbine engine; andactivating a second fuel control system configured to control the flow of a second fuel to said aircraft gas turbine engine.12. The method according to claim 11 , wherein the first fuel and ...

METHOD AND DEVICE FOR GENERATING ELECTRICITY AND GYPSUM FROM WASTE GASES CONTAINING HYDROGEN SULFIDE

The invention relates to a method and an apparatus for generating current from hydrogen sulphide-containing exhaust gases, particularly from the natural gas industry. 1. Method for generating current from hydrogen sulphide-containing exhaust gases , particularly from the natural gas and petroleum industry ,the hydrogen sulphide-containing exhaust gases being delivered to a current generation device and being burnt there, preferably with air being supplied, the energy released during combustion being employed at least partially for current generation,characterized in thatthe composition of the hydrogen sulphide-containing exhaust gases is measured before combustion and is compared with a stipulated composition or stipulated composition bandwidth, and, in the event of a deviation from the stipulated composition or composition bandwidth, an additional fraction of natural gas and/or other substances, which is required for correction, is determined and is admixed to the hydrogen sulphide-containing exhaust gases before combustion.2. Method according to claim 1 ,characterized in thatthe combustion temperature of hydrogen sulphide-containing exhaust gases is at least about 1,300° C.3. Method according to claim 1 ,characterized in thatthe current generation device comprises a steam generator which is part of the thermodynamic circuit of a steam power process, which, in turn, comprises a steam turbine following the steam generator and a condenser following the steam turbine, the combustion of the hydrogen sulphide-containing exhaust gases taking place in the steam generator, and the energy released being employed at least partially for steam generation, and current generation taking place by means of a generator driven by the steam turbine.4. Method according to claim 3 ,characterized in thatthe current generation device comprises a gas turbine and/or a gas engine, current generation taking place by means of a generator driven by the gas turbine and/or by the gas engine.5. ...

Combustor nozzle assembly, combustor equipped with the same, and gas turbine

A combustor nozzle assembly includes: a nozzle mounting base which blocks a combustor insertion opening formed in a turbine casing; a nozzle rod which passes through the nozzle mounting base and has a rod tip portion and a rod base end portion; an oil fuel pipe which is as a whole inserted into the nozzle rod, which has a pipe tip portion and a pipe base end portion, in which fuel is supplied to the inside through the rod base end portion, and which injects the fuel from the pipe tip portion through the rod tip portion; and an O-ring which is disposed in the rod base end portion and suppresses leakage of fuel to the pipe tip portion side between the inner periphery side of the nozzle rod and the outer periphery side of the oil fuel pipe.

GAS TURBINE COMBUSTOR

A gas turbine combustor includes a burner disposed upstream of the combustion chamber for supplying a gas and air to an interior of the combustion chamber to hold a flame provided with a first swirler in which a gas hole and an air hole are alternately formed in a circumferential direction. A first gas is supplied to the gas hole in the first swirler and air is supplied to the air hole. A swiveling flow path is formed in the gas hole and the air hole in the burner to swivel the gas and the air and supply the gas and the air to the interior of the combustion chamber, a second gas hole is formed in the swiveling flow path in at least one of the air hole and the gas hole, and a second gas is supplied through the second gas hole. 1. A gas turbine combustor having a combustion chamber for mixing a gas and air together to burn the gas , and a burner disposed upstream of the combustion chamber for supplying a gas and air to an interior of the combustion chamber to hold a flame , wherein:the burner is provided with a first swirler in which a gas hole and an air hole are alternately formed in a circumferential direction thereof;a first gas is supplied to the gas hole in the first swirler and air is supplied to the air hole; anda swiveling flow path is formed in the gas hole and the air hole in the burner to swivel the gas and the air and supply the gas and the air to the interior of the combustion chamber, a second gas hole is formed in the swiveling flow path in at least one of the air hole and the gas hole, and a second gas is supplied through the second gas hole.2. The gas turbine combustor according to claim 1 , wherein:the first gas is a low BTU gas and the second gas is a high BTU gas.3. The gas turbine combustor according to claim 1 , wherein:the burner is provided with a plurality of gas holes in an end surface on an inner circumferential side of the first swirler in a radial direction, and the second gas is supplied to the interior of the combustion chamber through ...

METHODS AND SYSTEMS FOR DIESEL FUELED CLC FOR EFFICIENT POWER GENERATION AND CO2 CAPTURE

An integrated chemical looping combustion (CLC) electrical power generation system and method for diesel fuel combining four primary units including: gasification of diesel to ensure complete conversion of fuel, chemical looping combustion with supported nickel-based oxygen carrier on alumina, gas turbine-based power generation and steam turbine-based power generation is described. An external combustion and a heat recovery steam generator (HRSG) are employed to maximize the efficiency of a gas turbine generator and steam turbine generator. The integrated CLC system provides a clean and efficient diesel fueled power generation plant with high COrecovery. 1. A diesel fueled chemical-looping combustion (CLC) electrical power generation system , comprising:a feed source of diesel fuel;a gasification chamber fluidly connected to the feed source, the gasification chamber including a first heat exchanger, a gasification reactor and a gasification splitter;a chemical looping combustion chamber fluidly connected to the gasification chamber, the chemical looping combustion chamber including a first reduction reactor, a first splitter, a second reduction reactor and a second splitter;a gas combustion chamber fluidly connected at a first input to a first output of the first splitter and at a second input to the gasification splitter,a gas turbine power generator connected to the combustor;at least one steam turbine electrical power generator;a heat recovery unit fluidly connected to the at least one steam turbine electrical power generator and to the gasification chamber, the heat recovery unit including a second heat exchanger and a plurality of steam generators; and{'sub': 2', '2, 'a COgas purification stage connected to the heat recovery unit, the COgas purification stage including a plurality of condensers and a plurality of compressors.'}2. The system of claim 1 , wherein the first heat exchanger is connected at a first input to the diesel fuel source claim 1 , and at a ...

POWER GENERATION APPARATUS, POWER GENERATION METHOD, DECOMPOSITION-GAS TURBINE AND DECOMPOSITION-GAS BOILER

A power generation apparatus, a power generation method, a decomposition-gas boiler, and a decomposition-gas turbine with which nitrous oxide may be used as an environmentally friendly energy source. A fuel gas including nitrous oxide (NO) is supplied to a decomposition reactor () in which a catalyst () for decomposing nitrous oxide is disposed. Steam is generated by a decomposition-gas boiler by heat recovery from decomposition gas (N, O) generated by decomposing the nitrous oxide, the steam generated by the decomposition-gas boiler is used to drive the rotation of a steam turbine to obtain motive power, and the motive power is subsequently used to drive a generator to obtain electrical power. Alternatively, the decomposition gas (N, O) generated by decomposing the nitrous oxide is used to drive the rotation of a decomposition-gas turbine to obtain motive power. 1. (canceled)2. (canceled)3. A power generation apparatus , comprising:a decomposition-gas boiler, generating steam by heat recovery from a decomposition gas produced by decomposition of nitrous oxide,a steam turbine, rotationally driven by the steam generated by the decomposition-gas boiler, andan electric generator, generating electric power by driving the steam turbine;ora decomposition-gas turbine, rotationally driven by decomposition gas produced by decomposition of nitrous oxide andan electric generator, generating electric power by driving the decomposition-gas turbine;wherein the decomposition-gas turbine or the decomposition-gas boiler comprise a decomposition reaction unit, in which a nitrous oxide decomposition catalyst for decomposition of the nitrous oxide is placed; anda fuel gas supply device, which supplies a fuel gas comprising nitrous oxide to the decomposition reaction unit, andin the decomposition reaction unit, after decomposition of the nitrous oxide contained in the fuel gas using the nitrous oxide decomposition catalyst, decomposition of a nitrous oxide contained in a fuel gas which ...

Integrated Power Generation Using Molten Carbonate Fuel Cells

In various aspects, systems and methods are provided for integrated operation of molten carbonate fuel cells with turbines for power generation. Instead of selecting the operating conditions of a fuel cell to improve or maximize the electrical efficiency of the fuel cell, an excess of reformable fuel can be passed into the anode of the fuel cell to increase the chemical energy output of the fuel cell. The increased chemical energy output can be used for additional power generation, such as by providing fuel for a hydrogen turbine. 1. A method for producing electricity , the method comprising:introducing a fuel stream comprising a reformable fuel into an anode of a molten carbonate fuel cell, an internal reforming element associated with the anode, or a combination thereof;{'sub': 2', '2, 'introducing a cathode inlet stream comprising COand Ointo a cathode of the molten carbonate fuel cell;'}generating electricity within the molten carbonate fuel cell, the molten carbonate fuel cell being operated such that a fuel utilization in the anode is about 50% or less at steady state conditions;{'sub': 2', '2, 'generating an anode exhaust comprising H, CO, and CO;'}{'sub': '2', 'separating, from at least a portion of the anode exhaust, a first H-rich gas stream; and'}{'sub': '2', 'combusting at least a portion of the first H-rich gas stream to produce electricity.'}2. The method of claim 1 , further comprising performing a water gas shift process on the anode exhaust claim 1 , the at least a portion of the anode exhaust claim 1 , or a combination thereof.3. The method of claim 1 , further comprising separating COand/or HO from the anode exhaust claim 1 , the at least a portion of the anode exhaust claim 1 , or a combination thereof.4. The method of claim 1 , wherein the separating step comprises:performing a water gas shift process on the anode exhaust or at least a portion of the anode exhaust to form a shifted anode exhaust portion; and{'sub': 2', '2', '2, 'separating HO ...

INDEPENDENTLY CONTROLLED THREE STAGE WATER INJECTION IN A DIFFUSION BURNER

A turbine engine combustion system is disclosed including a fuel nozzle assembly having three independently controlled stages of water injection. A first stage includes water mixed with a gaseous fuel upon inlet to the nozzle, where the first stage water mixes and travels with the gaseous fuel to be injected into a combustor. A second stage includes water injected into the combustor via a secondary liquid nozzle which is used for fuel oil during liquid fuel operation, but which may be used for the secondary water during gaseous fuel operation. A third stage includes water injected into the combustor via a plurality of nozzle holes known as an atomizing air cap. An algorithm and criteria are also defined for controlling the three stages of water injection to achieve the optimum balance of turbine operational criteria including NOx emissions, combustion dynamics and water impingement downstream of the nozzle. 1. A method for determining water flow rates for three stage water injection in a turbine engine combustion system , said method comprising:providing a turbine engine with injection of primary water, secondary water and tertiary water in the combustion system;setting the turbine engine to operate at a load point and measuring turbine operational data;determining if a plurality of turbine operational criteria are satisfied at the load point using single stage water injection or two stage water injection in the combustion system using the operational data;starting three stage water injection if the turbine operational criteria are not satisfied at the load point using single stage water injection or two stage water injection;setting primary/secondary/tertiary water fractions to preliminary values for the load point;setting water/fuel ratio to a preliminary value for the load point;operating the turbine engine using the water/fuel ratio and the primary/secondary/tertiary water fractions and measuring the turbine operational data;determining if the plurality of ...

METHOD AND INSTALLATION FOR STORING AND RECOVERING ENERGY

A method and installation for storing and recovering energy, according to which a condensed air product is formed in an energy storage period, and in an energy recovery period, a pressure flow is formed and is expanded to produce energy using at least part of the condensed air product. For the formation of the condensed air product: the compression of air in an air conditioning unit, at least by means of at least one isothermally operated compressor device and the adsorptive cleaning of the air by means of at least one adsorptive cleaning device at a hyperbaric pressure level. 1. A method for storing and recovering energy in which , in an energy storage period , an air liquefaction product is formed and , in an energy recovery period , a pressurized stream is formed and expanded to perform work by using at least part of the air liquefaction product , the method comprising , compressing air in an air conditioning unit, at least by means of at least one isothermally operated compressor device, and adsorptively purifying the air by means of at least one adsorptive purification device at a superatmospheric pressure level,', 'liquefying the compressed and adsorptively purified air, starting from a temperature level in a range of 0 to 50° C., in a first fraction in a fixed-bed cold storage unit and in a second fraction in a counterflow heat exchanger unit at a liquefaction pressure level in a range of 40 to 100 bara, and', 'subsequently expanding the liquefied air in at least one cold production unit,, 'for the formation of the air liquefaction product,'} producing a vaporization product from at least part of the liquefaction product at a vaporization pressure level, which deviates by no more than 5 bar from the liquefaction pressure level, in the fixed-bed cold storage unit, and', 'forming a fluid stream from at least part of the vaporization product and conducting it through at least one combustion device, in which a fuel is burned., 'and, for the formation of the ...

System and Method for Providing Highly Reactive Fuels to a Combustor

A system and related method for providing a highly reactive fuel to a combustor of a gas turbine are disclosed herein. The system includes a fuel supply system that is in fluid communication with a fuel supply. The fuel supply system includes multiple fuel circuits. Each fuel circuit individually feeds fuel to a corresponding fuel distribution manifold. The system further includes a steam injection system. The steam injection system includes at least one flow control valve that is in fluid communication with at least one of the fuel circuits. The flow control valve provides for fluid communication between a superheated steam source and the fuel circuit during both fueled operation and during non-fueled operation of the corresponding fuel circuit.

SYSTEM AND METHOD FOR OPERATING A POWER PLANT

A system including a fuel-supply system including, an auxiliary-fuel-gas compressor configured to compress a fuel for use by a gas-turbine system, an expander configured to generate power by expanding an oxidant from the gas-turbine system, and a motor/generator configured to function in a motor mode and in a generator mode, wherein the motor/generator drives fuel compression with the auxiliary fuel-gas compressor in the motor mode, and the motor/generator generates power in the generator mode as the expander uses oxidant from the gas-turbine system to drive the motor/generator 1. A system , comprising:an auxiliary-fuel-gas compressor configured to compress a fuel for use by a gas-turbine system;an expander configured to generate power by expanding an oxidant from the gas-turbine system; anda motor-generator configured to function in a motor mode and in a generator mode, wherein the motor-generator drives fuel compression with the auxiliary fuel-gas compressor in the motor mode, and the motor-generator generates power in the generator mode as the expander uses oxidant from the gas-turbine system to drive the motor-generator.2. The system of claim 1 , comprising a fuel-gas compressor-expander having both the auxiliary-fuel gas compressor and the expander as a single dual-purpose unit.3. The system of claim 1 , comprising a controller configured to change the motor-generator between the motor mode and the generator mode.4. The system of claim 3 , comprising a compressor clutch configured to engage and disengage the auxiliary-fuel-gas compressor from the motor-generator claim 3 , wherein the controller controls operation of the auxiliary-fuel-gas compressor by engaging and disengaging the compressor clutch.5. The system of claim 4 , comprising an expander clutch configured to engage and disengage the expander from the motor-generator claim 4 , wherein the controller controls operation of the expander by engaging and disengaging the expander clutch.6. The system of ...

ENERGY-EFFICIENT AND CONTROLLED VAPORIZATION OF CRYOFUELS FOR AIRCRAFT ENGINES

A method and apparatus of using cryogenic fuel in an engine for an aircraft wherein the cryogenic fuel is supplied to the engine for combustion. 1. A method of using cryogenic fuel in an engine for aircraft generating waste heat , the method comprising:supplying liquid cryogenic fuel for combustion in the engine; andvaporizing the liquid cryogenic fuel with the waste heat from the aircraft to form vaporized fuel from the liquid cryogenic fuel prior to combustion in the engine.2. The method of further comprising combusting the vaporized cryogenic fuel in the engine.3. The method of wherein vaporizing the liquid cryogenic fuel with waste heat from the aircraft comprises passing the waste heat and the liquid cryogenic fuel through a heat exchanger to heat the liquid cryogenic fuel with the waste heat.4. The method of wherein passing the waste heat through the heat exchanger comprises passing multiple sources of waste heat through the heat exchanger.5. The method of wherein passing the waste heat and liquid cryogenic fuel through the heat exchanger comprises passing the waste heat and liquid cryogenic fuel through multiple heat exchangers.6. The method of wherein passing the waste heat through the multiple heat exchangers comprises passing different sources of waste heat to different heat exchangers of the multiple heat exchangers.7. The method of wherein passing the waste heat through multiple heat exchangers further comprises passing the liquid cryogenic fuel through a first heat exchanger such that the first heat exchanger heats the fuel to a temperature below the fuel vaporization temperature claim 6 , and passing the liquid cryogenic fuel from the first heat exchanger to a second heat exchanger such that the second heat exchanger vaporizes the fuel claim 6 , and wherein the passing the liquid cryogenic fuel through both heat exchangers occurs if a single heat exchanger is unable to vaporize the fuel.8. The method of wherein vaporizing the liquid cryogenic fuel with ...

COMBUSTION SYSTEM AND METHOD FOR ATTENUATION OF COMBUSTION DYNAMICS IN A GAS TURBINE ENGINE

The present disclosure is directed to a method of operating a combustion system to attenuate combustion dynamics. The method includes flowing, via a compressor section, an overall supply of air to the combustion system; flowing, via a fuel supply system, an overall flow of fuel to the combustion system; flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer burning fuel-air mixture at the first fuel nozzle; flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner burning fuel-air mixture at the second fuel nozzle; and igniting the richer burning fuel-air mixture and the leaner burning fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system. 117-. (canceled)18. A combustion system for a gas turbine engine , the combustion system comprising:a liner and dome assembly together defining a combustion chamber;a first fuel nozzle and a second fuel nozzle together in alternating circumferential arrangement around a longitudinal centerline; and{'b': '50', 'a fuel supply system providing a first supply of fuel to the first fuel nozzle and a second supply of fuel to the second fuel nozzle, wherein at least % of an overall supply of fuel is the first supply of fuel.'}19. The combustion system of claim 18 , wherein the fuel supply system comprises a first fuel manifold coupled to the first fuel nozzle and a second fuel manifold coupled to the second fuel nozzle claim 18 , wherein the fuel supply system provides at least 50% of the overall supply of fuel to the first fuel nozzle and a remainder of the overall supply of fuel to the second fuel nozzle.20. The combustion system of claim 18 , wherein the fuel supply system comprises a main fuel manifold coupled to the first fuel nozzle and the second fuel nozzle claim 18 , and wherein each of the first fuel nozzle and the second fuel nozzle define a proportion of the overall supply of fuel.21. The ...

FUEL PLENUM FOR A FUEL NOZZLE AND METHOD OF MAKING SAME

A fuel plenum for a fuel nozzle assembly includes a gaseous fuel conduit, a conduit passage, and a liquid fuel conduit. Said gaseous fuel conduit received at a first end of said fuel plenum. Said fuel plenum is configured to distribute gaseous fuel received from said gaseous fuel conduit. Said conduit passage extends from the first end to a second end of said fuel plenum. Said conduit passage is at least partially defined by at least one interior wall of said fuel plenum. Said liquid fuel conduit defined by an outer wall and a portion of said liquid fuel conduit extending through said conduit passage. Said liquid fuel conduit outer wall is offset from said at least one interior wall. 1. A fuel plenum for a fuel nozzle assembly , said fuel plenum comprising:a gaseous fuel conduit received at a first end of said fuel plenum, said fuel plenum is configured to distribute gaseous fuel received from said gaseous fuel conduit;a conduit passage that extends from the first end to a second end of said fuel plenum, said conduit passage is at least partially defined by at least one interior wall of said fuel plenum; anda liquid fuel conduit defined by an outer wall, a portion of said liquid fuel conduit extends through said conduit passage, said liquid fuel conduit outer wall is offset from said at least one interior wall.2. The fuel plenum of claim 1 , wherein said liquid fuel conduit is received at said first end of said fuel plenum claim 1 , said liquid fuel conduit outer wall is offset by a first distance from an outer wall of said gaseous fuel conduit at said fuel plenum first end.3. The fuel plenum of claim 1 , wherein said liquid fuel conduit outer wall is offset by a second distance from said at least one interior wall.4. The fuel plenum of claim 1 , wherein said portion of said liquid fuel conduit is structurally coupled to the fuel nozzle assembly at a single location proximate said fuel plenum claim 1 , such that an end of said portion opposite the single location is ...

Gas turbine energy supplementing systems and heating systems, and methods of making and using the same

Electrical power systems, including generating capacity of a gas turbine are provided, where additional electrical power is generated utilizing a separate engine and auxiliary air injection system. The gas turbine and separate engine can operate on different fuel types.

System and Methods for Recycling Hydrocarbon Waste Gas That is Generated During Cleaning of a Hydrocarbon Storage Tank

A hydrocarbon waste-gas recycling method having the steps of: transporting a hydrocarbon waste-gas composition, which is generated during a hydrocarbon storage-tank cleaning process, from a storage tank that is being cleaned to a fuel-gas blend controller; blending the hydrocarbon waste-gas composition with a second hydrocarbon gas-phase composition to thereby create a third gas-phase composition; and using the third gas-phase composition to fuel a combustion engine. 1. A hydrocarbon waste-gas recycling method comprising the steps:transporting a hydrocarbon waste-gas composition, which is generated during a hydrocarbon storage-tank cleaning process, from a storage tank that is being cleaned to a fuel-gas blend controller;blending the hydrocarbon waste-gas composition with a second hydrocarbon gas-phase composition to thereby create a third gas-phase composition; andusing the third gas-phase composition to fuel a combustion engine.2. The hydrocarbon waste-gas recycling method of claim 1 , wherein the hydrocarbon storage-tank cleaning process is a crude-oil storage-tank cleaning process.3. The hydrocarbon waste-gas recycling method of claim 1 , wherein the combustion engine powers an electric generator.4. The hydrocarbon waste-gas recycling method of claim 1 , wherein the second hydrocarbon gas-phase composition is propane gas.5. The hydrocarbon waste-gas recycling method of claim 3 , further comprising the step of using electricity generated by the electric generator to power at least one electric motor.6. The hydrocarbon waste-gas recycling method of claim 1 , further comprising the step of using a heat recovery unit to recover heat from exhaust emitted by the combustion engine.7. The hydrocarbon waste-gas recycling method of claim 1 , wherein a pipeline is used to transport the hydrocarbon waste-gas composition from the storage tank that is being cleaned to the fuel-gas blend controller.8. The hydrocarbon waste-gas recycling method of claim 1 , wherein a pipeline ...

SYSTEM AND METHOD FOR MONITORING FUEL ADDITIVES

A system for monitoring fuel additives on board a vehicle includes a fuel line carrying fuel from a fuel source to an engine; a fuel additive sensor configured to measure concentration of additives in fuel at a point along the fuel line; a fuel additive dispenser connected in parallel to the fuel line; at least one flow control device for controlling an amount of flow from the fuel line into the fuel additive dispenser; and a controller configured to receive input from the fuel additive sensor and to control the flow control device to adjust the amount of the flow from the fuel line into the fuel additive dispenser. 110-. (canceled)11. A method for monitoring fuel additives on board a vehicle , comprising:flowing fuel from a fuel tank along a fuel line to an engine;sensing concentration of additives in the fuel at a point along the fuel line;determining whether the concentration of the additive in the fuel is less than a fuel additive specification;when the concentration is less than the specification, operating a flow control device to divert a portion of the fuel from the fuel line along a parallel line to a fuel additive dispenser.12. The method of claim 11 , wherein the fuel additive dispenser is positioned along a fuel additive bypass line connected at an upstream end to the flow control device and connected at a downstream end back to the fuel line.13. The method of claim 12 , wherein the fuel additive sensor is positioned upstream of or at the flow control device.14. The method of claim 12 , wherein the fuel additive sensor is positioned downstream of the downstream end of the fuel additive bypass line.15. The method of claim 11 , wherein the controller is configured to compare the concentration with a pre-set additive requirement specification claim 11 , and to control the flow control device to increase flow through to fuel additive dispenser when the concentration is less than the specification.16. The method of claim 15 , wherein the controller is ...

SYSTEMS AND METHODS FOR VANADIUM CORROSION INHIBITORS

A system includes a turbine combustor and one or more supply circuits configured to supply one or more fluids to the turbine combustor. The one or more supply circuits include at least a liquid fuel supply circuit fluidly coupled to a liquid fuel source and configured to supply a liquid fuel from the liquid fuel source to the turbine combustor. The system also includes a corrosion inhibitor injection system including a magnesium source storing a magnesium-based inhibitor that includes magnesium oxide (MgO) and an yttrium source storing an yttrium-based inhibitor that includes yttrium oxide (YO). The corrosion inhibitor injection system is fluidly coupled to the turbine combustor and the one or more supply circuits, and is configured to inject the magnesium-based inhibitor and the yttrium-based inhibitor as vanadium corrosion inhibitors into the turbine combustor or the one or more supply circuits. 1. A system , comprising:a turbine combustor;one or more supply circuits configured to supply one or more fluids to the turbine combustor, wherein the one or more supply circuits comprise at least a liquid fuel supply circuit fluidly coupled to a liquid fuel source and configured to supply a liquid fuel from the liquid fuel source to the turbine combustor; and{'sub': 2', '3, 'a corrosion inhibitor injection system comprising a magnesium source storing a magnesium-based inhibitor comprising magnesium oxide (MgO) and an yttrium source storing an yttrium-based inhibitor comprising yttrium oxide (YO), the corrosion inhibitor injection system being fluidly coupled to the turbine combustor and the one or more supply circuits, and wherein the corrosion inhibitor injection system is configured to inject the magnesium-based inhibitor and the yttrium-based inhibitor as vanadium corrosion inhibitors into the turbine combustor or the one or more supply circuits.'}2. The system of claim 1 , wherein the liquid fuel contains vanadium claim 1 , sodium claim 1 , potassium claim 1 , or any ...

GAS TURBINE BURNER

The burner of a gas turbine includes a swirl generator and, downstream of it, a mixing tube. The swirl generator is defined by at least two walls facing one another to define a conical swirl chamber and is provided with nozzles arranged to inject a fuel and apertures arranged to feed an oxidiser into the swirl chamber. The burner includes a lance which extends along a longitudinal axis of the swirl generator and is provided with side nozzles for ejecting a fuel within the burner. The side nozzles have their axes inclined with respect to the axis of the lance and can be positioned along the axis of the burner. 2. A method for operating a burner having a swirl generator defined by at least two walls facing one another to define a substantially conical swirl chamber , the swirl generator including nozzles arranged to inject a fuel and apertures arranged to feed an oxidizer into said swirl chamber , a mixing tube positioned downstream of the swirl generator , and a lance positioned inside at least the swirl generator , the lance extending along a longitudinal axis of the swirl generator and being provided with side nozzles for ejecting fuel oil within the burner , the lance side nozzles having axes inclined with respect to an axis of the lance , the method comprising:at starting, injecting about 80% of the oil through lance tip nozzle and injecting about 20% through the lance side nozzles;at idle operation, injecting about 75% of the oil through the lance tip nozzle and injecting about 25% through the lance side nozzles;at part load, injecting about 50% of the oil through the lance tip nozzle and injecting about 50% through the lance side nozzles; andat full load, injecting about 10% of the oil through the lance tip nozzle and injecting about 90% through the lance side nozzles.3. A method for operating a burner having a swirl generator defined by at least two walls facing one another to define a substantially conical swirl chamber , the swirl generator including nozzles ...

SYSTEM AND METHOD FOR ABATEMENT OF DYNAMIC PROPERTY CHANGES WITH PROACTIVE DIAGNOSTICS AND CONDITIONING

A system includes a fluid transfer system that has instrumentation configured to measure fuel properties; a fluidic buffer volume device located downstream of a fuel sensing point, wherein the fluidic buffer volume device is configured to provide a residence time for the fuel within the fluidic buffer volume device to enable a signal representative of the fuel properties to be communicated to enable adjustment of operating conditions of a fuel consuming system as the fuel is provided; and a controller programmed to receive properties of the fuel consuming system, receive the signal, receive properties of the fluidic buffer volume device, and generate a time-resolved volumetric grid that characterizes fuel transport properties of the fuel for different flow conditions and times based on the properties of the fuel consuming system, the fuel properties, and the properties of the fluidic buffer volume device. 1. A system , comprising: instrumentation configured to measure one or more properties of a fuel;', 'a fluidic buffer volume device located downstream of a fuel sensing point of the instrumentation, wherein the fluidic buffer volume device is configured to provide a residence time for the fuel within the fluidic buffer volume device to enable a signal from the instrumentation representative of an analysis of the one or more properties of the fuel to be communicated to enable adjustment of operating conditions of a fuel consuming system by a time that the fuel is provided to the fuel consuming system; and', 'a controller programmed to receive one or more properties of the fuel consuming system, to receive the signal from the instrumentation representative of the one or more properties of the fuel, and to receive one or more properties of the fluidic buffer volume device, and to generate a time-resolved volumetric grid that characterizes fuel transport properties of the fuel for different flow conditions and flow times based at least on the one or more properties of ...

INJECTOR DEVICE AND METHOD FOR MANUFACTURING AN INJECTOR DEVICE

An injector device is disclosed which includes an elongated body with a leading edge and a trailing edge, gas nozzles and oil nozzles, an oil supply duct housed within the elongated body and connected to the oil nozzles, and a gas supply duct housed within the elongated body and connected to the gas nozzles. The oil supply duct is connected to the gas supply duct only between one or more oil nozzles and one gas nozzles, and the gas supply duct is connected to the elongated body only via bridges. 1. An injector device for a burner of a gas turbine comprising:an elongated body with a leading edge and a trailing edge;gas nozzles and oil nozzles;an oil supply duct housed within the elongated body and connected to the oil nozzles; anda gas supply duct housed within the elongated body and connected to the gas nozzles;wherein:the oil supply duct is connected to the gas supply duct only between at least one oil nozzles and one gas nozzles; andthe gas supply duct is connected to the elongated body only via at least one bridge.2. The injector device of claim 1 , wherein:a connection between the oil supply duct and the gas supply duct is at a the terminal part of the oil nozzle and gas nozzle.3. The injector device of claim 1 , wherein the elongated body comprises:at least a channel at the leading edge, wherein the at least one bridge is provided only between the gas supply duct and the channel.4. The injector device of claim 1 , comprising:only two bridges, each bridge being connected at one side of the gas supply duct.5. The injector device of claim 1 , wherein:the trailing edge has a lobed configuration or a straight configuration or a zig-zag configuration.6. The injector device of claim 1 , comprising:air nozzles.7. The injector device of claim 6 , wherein:the air nozzles and/or gas nozzles and/or oil nozzles are at the trailing edge.8. The injector device of claim 1 , being a selective laser melted (SLM) structure.9. A method for manufacturing an injector device having: ...

Control Method for Gasification Power Generation System

The present invention relates to an operation control method for a gasification power generation system for gasifying carbon-based fuel such as coal in a gasifier using oxygen or oxygen-enriched air as an oxidizing agent, burning the obtained syngas as fuel in a gas turbine, driving the gas turbine by the syngas, driving a steam turbine by steam generated using exhaust heat of the gas turbine, thus executing combined power generation. 1. A control method for a gasification power generation system including a gasifying equipment for gasifying carbon based fuel by an oxidizing agent in a gasifier and generating syngas , a gas clean-up unit for obtaining a syngas purified by removing a sulfur compound in the syngas generated in the gasifier , and a gas turbine equipment for generating power by burning the purified syngas obtained by the gas clean-up unit as fuel , comprising the steps of:inferring a syngas beating value at a gasifier outlet and a syngas quantity from a property and a feed rate of the carbon based fuel fed to the gasifier of the gasifying equipment, a flow rate of nitrogen or water used for transport of the carbon based fuel to the gasifier, and a property and a feed rate of the oxidizing agent fed to the gasifier;analyzing syngas sampled from instruments or pipes between the gasifier of the gasifying equipment and the gas turbine equipment, and correcting the inferred value of the syngas heating value using analytical values of the sampled syngas;inferring a time lag until the syngas heating value is changed at a gas turbine equipment inlet after the feed rate of the carbon based fuel fed to the gasifier is changed from the inferred value of the syngas quantity, volumes of the instruments and the pipes between the gasifier of the gasifying equipment and the gas turbine equipment, and a temperature and a pressure of the syngas in the instruments and the pipes; andsetting the syngas heating value inferred from the feed rate of the carbon based fuel fed ...

DUAL FUEL COMBUSTOR FOR A GAS TURBINE ENGINE

The present application and the resultant patent provide a dual fuel combustor for a gas turbine engine. The combustor may include a primary premixer positioned within a head end plenum of the combustor, and a dual fuel, injection system positioned within the head end plenum and upstream of the premixer. The injection system may be configured to inject a gas fuel about an inlet end of the premixer when the combustor operates on the gas fuel. The injection system also may be configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel. The present application and the resultant patent also provide a related method of operating a dual fuel combustor. 1. A dual fuel combustor for a gas turbine engine , the combustor comprising;a primary premixer positioned within a head end plenum of the combustor; and a dual fuel injection system positioned within the head end plenum and upstream of the premixer;wherein the injection system is configured to inject a gas feel about an inlet end of the premixer when the combustor operates on the gas fuel; andwherein the injection system is configured to vaporize and inject a liquid fuel about the inlet end of the premixer when the combustor operates on the liquid fuel,2. The dual fuel combustor of claim 1 , wherein the premixer comprises a micro-mixer comprising a. plurality of micro-mixer tubes positioned about at least one fuel tube.3. The dual fuel claim 1 , combustor of claim 1 , wherein the injection system comprises at least one toroidal injection manifold extending about a circumference of the premixer.4. The dual fuel combustor of claim 3 , wherein the toroidal injection manifold comprises an internal sleeve and an external sleeve surrounding the internal sleeve claim 3 , wherein the internal sleeve is configured to receive a flow of the liquid fuel therein claim 3 , and wherein the external sleeve is configured to direct a flow of air against the internal ...

Gas Turbine Combustion System

The present invention provides a gas turbine combustion system capable of minimizing unburned content of a gas fuel under all load conditions from partial load to rated load. A gas turbine combustion system includes: a plurality of gas fuel burners 32, 33; an IGV 9 that adjusts a flow rate of air to be mixed with a gas fuel; and a control system 500 that temporarily reduces an air flow rate from a reference flow rate to a set flow rate by outputting a signal to the IGV 9 when a combustion mode is switched from a partial combustion mode in which the gas fuel is burned with part of the gas fuel burners 32, 33 to a full combustion mode in which the gas fuel is burned with all of the gas fuel burners 32, 33.

SYSTEMS AND METHODS FOR OPERATION OF A FLEXIBLE FUEL COMBUSTOR

The present disclosure relates to systems and methods that are useful for controlling one or more aspects of a power production plant. More particularly, the disclosure relates to power production plants and methods of carrying out a power production method utilizing different fuel chemistries. Combustion of the different fuel mixtures can be controlled so that a defined set of combustion characteristics remains substantially constant across a range of different fuel chemistries. 1. A method for normalizing combustion in a power production process , the method comprising:inputting to a combustor with a combustion zone and a dilution zone that is downstream from the combustion zone a fuel, an oxidant, and diluent so that the fuel is combusted to provide a combustor exhaust stream; andpassing the combustor exhaust stream through a turbine to generate power;wherein the fuel is a variable fuel is that subject to compositional changes during the power production process;wherein the diluent comprises carbon dioxide;wherein the diluent is mixed with the fuel, is mixed with the oxidant, and is also separately injected into the dilution zone of the combustor; andwherein the method also comprises implementing at least one control function such that one or more of fuel heating value, flame temperature, combustion pressure, combustor exit temperature, mass flow out of the combustor, turbine inlet flow chemistry, and turbine speed varies from a predetermined value by no greater than 10% and thus accounts for the compositional changes to the fuel during the power production process so that combustion is normalized, said control function including one or more of:varying a ratio of diluent mixed with oxygen in the oxidant;varying a temperature of the oxidant input to the combustor;varying a temperature of the fuel input to the combustor;varying a temperature of the diluent input to the combustor in the dilution zone;varying a flow rate of the oxidant input to the combustor;varying ...

Gaseous Fuel Wobbe Index Modification Skid

A method of regulating a Modified Wobbe index number (MWI) of a multi-composition gas fuel supplied to one or more combustors of a gas turbine is disclosed. A rapid temperature swing absorber comprising a skid or platform comprising one or more reactor vessels is also disclosed, the one or more vessels comprising a plurality of hollow fibers each of which is impregnated by one or more sorbents for the separation of one or more deleterious gases from a fuel stream. 1. A method of regulating a Modified Wobbe index number (MWI) of a multi-composition gas fuel comprising:separating particulates and moisture from an initial gas fuel stream, the separating performed with a media that is both hydrophobic and oleophobic; andabsorbing one or more deleterious gases present in the initially treated gas fuel stream using a plurality of fibers impregnated with sorbents to absorb the one or more deleterious gases to afford a secondary gas fuel stream, thereby changing the MWI of the secondary gas fuel stream relative to the initial gas fuel stream.2. A method of regulating a MWI of a multi-composition gas fuel according to claim 1 , wherein the multi-composition gas fuel is supplied to one or more combustors of a gas turbine.3. A method of regulating a MWI of a multi-composition gas fuel according to claim 2 , further comprising providing a control system for regulating fuel and air flow to one or more combustors.4. A method of regulating a MWI of a multi-composition gas fuel according to claim 1 , wherein the hydrophobic and oleophobic media is an ePTFE media.5. A method of regulating a MWI of a multi-composition gas fuel according to claim 1 , wherein the plurality of fibers impregnated with sorbents are hollow fibers.6. A method of regulating a MWI of a multi-composition gas fuel according to claim 4 , wherein the plurality of hollow fibers impregnated with sorbents are present in one or more reactor vessels.7. A method of regulating a MWI of a multi-composition gas fuel ...

Method for controlling a gas turbine

The invention relates to a method for controlling a gas turbine, operating with an integral fuel reactivity measurement concept. In order to fast determine a safe operation range of the gas turbine with respect to flashback and blow-out, the method includes deducing the fuel composition and therefore the fuel reactivity by combined measurements of (n−1) physico-chemical properties of a fuel mixture with n>1 fuel components, for deriving the concentration of one component for each physico-chemical property of the fuel gas mixture or for determining of a ratio of the fuels with known compositions and adjusting at least one operation parameter of the gas turbine at least partially based on the determined property of the fuel gas mixture entering the combustors. With the technical solution of the present invention, by way of detecting fast changes in fuel gas, it is assured that the gas turbine may operate with varieties of fuel gas under optimized performance and in safe operation ranges. In actual applications, the present invention may improve flexibility of gas turbines and cost effectiveness of operation of the gas turbines.

COMBUSTION SYSTEM AND METHOD FOR ATTENUATION OF COMBUSTION DYNAMICS IN A GAS TURBINE ENGINE

The present disclosure is directed to a method of operating a combustion system to attenuate combustion dynamics. The method includes flowing, via a compressor section, an overall supply of air to the combustion system; flowing, via a fuel supply system, an overall flow of fuel to the combustion system; flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer burning fuel-air mixture at the first fuel nozzle; flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner burning fuel-air mixture at the second fuel nozzle; and igniting the richer burning fuel-air mixture and the leaner burning fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system. 1. A method of operating a combustion system to attenuate combustion dynamics , the method comprising:flowing, via a compressor section, an overall supply of air to the combustion system;flowing, via a fuel supply system, an overall flow of fuel to the combustion system;flowing, to a first fuel nozzle of the combustion system, a first supply of fuel defining a richer fuel-air mixture at the first fuel nozzle;flowing, to a second fuel nozzle of the combustion system, a second supply of fuel defining a leaner fuel-air mixture at the second fuel nozzle; andigniting the richer fuel-air mixture and the leaner fuel-air mixture to produce an overall fuel-air ratio at a combustion chamber of the combustion system.2. The method of claim 1 , further comprising:determining a desired overall fuel-air ratio at the combustion chamber based at least on the overall supply of air and the overall supply of fuel.3. The method of claim 2 , further comprising:determining a fuel split to the first fuel nozzle and to the second fuel nozzle based on the overall flow of fuel that is further based at least on an operating condition of the engine, the overall supply of air, and the desired overall fuel-air ratio.4. The ...

Method And Device For Storing And Recovering Energy

The invention relates to a method for storing and recovering energy, wherein an air liquefaction product (LAIR) is formed during an energy storage period, and a fluid pressure flow () is formed during an energy recovery period using at least one part of the air liquefaction product (LAIR) and is expanded for operation in at least one energy recovery device (). The air liquefaction product (LAIR) is obtained as a liquid medium during the energy storage period by compressing air in an air conditioning device (), said compression being operated while supplying energy, in particular while supplying a current (), optionally stored in a cold state, and fed to an evaporator unit (). The air liquefaction product (LAIR) is expanded for operation as a fluid pressure flow () in the at least one energy recovery device () during the energy recovery period after a pressure increase. The aim of the invention is to provide a solution with which even existing gas and steam power plants or open gas turbines are to be equipped with an energy storage capability. This is achieved in that the fluid pressure flow (), in particular an air flow, is expanded in a first energy recovery device () and conducted through a recuperator device (), in particular a heat boiler, upstream of said first energy recovery device (), and thermal energy which has been decoupled from a flue gas flow () fed to the recuperator device () is coupled into the fluid pressure flow () in said heating tank. The flue gas flow () is fed to the recuperator device () from a fuel-fired second energy recovery device (), in particular a gas turbine. 1. A method of storing and recovering energy , in which an air liquefaction product (LAIR) is formed in an energy storage period and a fluid pressure stream is formed using at least a portion of the air liquefaction product (LAIR) in an energy recovery period and is expanded to perform work in at least one energy generation device ,in which the air liquefaction product (LAIR) is ...

COMBINATION AIR ASSIST AND PILOT GASEOUS FUEL CIRCUIT

When starting a dual fuel turbine engine on liquid fuel, a flow of air assist into a combined pilot gaseous fuel and air assist tube is supplied. The velocity of the flow of air assist is increased as it is expelled through an outlet of the tube. The flow of air assist is directed into a first end of a pilot injector barrel. Additional air is drawn into the first end of the pilot injector barrel from an enclosure containing both the first end of the pilot injector barrel and the tube outlet. Liquid pilot fuel is supplied at a second end of the pilot injector barrel, and this fuel is atomized by the flow of the air assist and additional air. The atomized pilot liquid fuel may then be combusted, 1. A method for starting a turbine engine , comprising;supplying a flow of air assist to a combined pilot gaseous fuel and air assist tube, the flow having a first velocity;increasing the velocity of the flow to a second velocity as it is expelled through an outlet of the tube;directing the flow into a first end of a pilot injector barrel;drawing additional air from an enclosure into the first end of the pilot injector barrel, the enclosure containing the outlet of the tube and the first end of the pilot injector barrel;supplying pilot liquid fuel to a second end of the pilot injector barrel;atomizing the supplied pilot liquid fuel with the flow of air assist and the additional air; andcombusting the atomized pilot liquid fuel.2. The method of claim 1 , wherein supplying the flow of air assist includes routing air assist from an air assist source to the combined pilot gaseous fuel and air assist tube.3. The method of claim 2 , wherein routing air assist from the air assist source to the combined pilot gaseous fuel and air assist tube includes:routing air assist from the air assist source to a combined pilot gaseous fuel and air assist manifold; androuting air assist from the combined pilot gaseous fuel and air assist manifold to the combined pilot gaseous fuel and air assist ...

GASIFICATION POWER PLANT CONTROL DEVICE, GASIFICATION POWER PLANT, AND GASIFICATION POWER PLANT CONTROL METHOD

This IGCC plant is provided with an ASU which separates oxygen gas and nitrogen gas from air, a coal gasification furnace which uses an oxidizing agent to gasify coal, and a gas turbine which is driven by the combustion gas resulting from burning a gas generated by means of the coal gasification furnace. This IGCC plant control device () is provided with an air separation amount determination unit () which determines the production amount of nitrogen gas produced by the ASU depending on the operating load of the IGCC plant, and supplies to the coal gasification furnace the entire amount of oxygen gas generated as a byproduct in response to the determined nitrogen gas production amount. By this means, the IGCC plant can minimize blow-off of oxygen gas produced from the air. 1. A gasification power plant control device , in which a gasification power plant includes an air separation unit which separates oxygen gas and nitrogen gas from air , a gasification furnace which gasifies a carbon-containing fuel with the oxygen gas as an oxidizing agent , and a gas turbine which is driven by combustion gas resulting from burning fuel gas which is obtained by refining gas generated by the gasification furnace using gas clean-up equipment , the device comprising:an air separation amount determination unit which determines a production amount of the nitrogen gas produced by the air separation unit depending on an operation load of the gasification power plant,wherein the entire amount of oxygen gas generated as a byproduct in response to the production amount of the nitrogen gas determined by the air separation amount determination unit is supplied to the gasification furnace.2. The gasification power plant control device according to claim 1 ,wherein a total amount of the oxidizing agent supplied to the gasification furnace is adjusted by an amount of air extracted from the gas turbine.3. The gasification power plant control device according to claim 1 ,wherein the operation ...

A GAS TURBINE COMBUSTOR ASSEMBLY WITH A TRAPPED VORTEX FEATURE

A combustor assembly of a gas turbine engine having a trapped vortex feature to reduce emissions where the trapped vortex is formed using ammonia injected into an annular cavity located in a wall surrounding a combustion chamber of the combustor assembly. The annular cavity, and therefore the trapped vortex, is positioned such that when the combustion occurs within the combustion chamber the position of the annular cavity, and therefore of the trapped vortex, is downstream of a flame front. The emissions resulting from combustion travel through the combustion chamber and pass by the annular cavity before exiting the combustion chamber. The trapped vortex in the combustion chamber supplies NHradicals, resulting from the ammonia of the trapped vortex, to the passing by emissions and converts NOx and/or NO in the emissions to non-polluting products, mainly water and nitrogen. 1. A method for operating a combustor assembly for a gas turbine engine , comprising:combusting at least a first fuel in a reaction zone of a combustion chamber of the combustor assembly, wherein the reaction zone comprises a reaction zone front; andinjecting ammonia into the combustion chamber to form a trapped vortex in the combustion chamber, wherein the ammonia is injected such that the trapped vortex is formed in the combustion chamber at a position downstream of the reaction zone front.2. The method according to the claim 1 ,wherein the first fuel comprises or is one of Hydrogen, a hydrocarbon, a mixture of hydrocarbons, Ammonia, and a combination thereof.3. The method according to claim 1 ,wherein combusting at least the first fuel includes combusting at least a second fuel, andwherein the method further comprises:injecting the second fuel into the combustion chamber such that the second fuel enters the reaction zone, wherein the second fuel is less reactive than the first fuel;wherein combusting the first fuel comprises injecting the first fuel into the combustion chamber such that the ...

DUAL FUEL GAS TURBINE THRUST AND POWER CONTROL

An aircraft, controller, and method for simultaneously using a liquid fuel and a gaseous fuel. The use of natural gas and other similar fuels in gas turbines engines can enable an aircraft to operate less expensively. However, aircraft often use liquid fuels en route to the gas turbine engine burners for secondary purposes, such as oil cooling and hydraulic pressure. The aircraft, controllers, and methods described herein feed a minimal quantity of liquid fuel to an engine to satisfy the secondary purposes while simultaneously feeding a quantity of gaseous fuel to the engine to satisfy a thrust command for the engine. 1. An aircraft , comprising:a first fuel storage container configured to store a liquid fuel;a second fuel storage container configured to store a gaseous fuel;a gas turbine engine that includes fuel nozzles configured to inject the liquid fuel and the gaseous fuel into a burner of the gas turbine engine; anda controller configured to simultaneously meter flow of both the liquid fuel and the gaseous fuel to the fuel nozzles from the first fuel storage container and the second fuel storage container, wherein the controller is configured to meter the flow of the liquid fuel to satisfy an operating limit of the gas turbine engine.2. The aircraft of claim 1 , further comprising a selectable switch in communication with the controller claim 1 , wherein the controller does not permit flow of the gaseous fuel when the switch is in a first position claim 1 , and wherein the controller permits flow of the gaseous fuel when the switch is in a second position.3. The aircraft of claim 2 , wherein the switch automatically switches to the second position when the aircraft is configured for cruise flight.4. The aircraft of claim 1 , further comprising a throttle control in communication with the controller claim 1 , wherein the throttle control provides a thrust request claim 1 , wherein the controller is configured to meter the flow of the gaseous fuel to satisfy ...

BURNER

A burner of a gas turbine extending along an axis is provided having in axial order: a swirler section, mixing section, outlet section, and main combustion zone. The swirler section has swirler vanes to swirl a stream of fuel and oxygen containing gas entering therein in a circumferential direction. The mixing section conducts the premix of fuel and oxygen containing gas to the outlet section. The outlet section discharges the premix into the combustion zone expanding the flow of premix from a smaller axial cross section of the mixing section to a larger cross section of the combustion zone which streamlines the flow to diverge radially. A surface of the outlet section facing the flow of the premix is provided with first fuel nozzles injecting fuel into the premix into a radial inwardly inclined direction before the flow of the premix enters the outlet section into the combustion zone. 16-. (canceled)7. A burner (B) of a gas turbine extending along an axis (X) and comprising in axial ordera swirler section (SW),a mixing section (MX),an outlet section (OT), anda main combustion zone (CZ),wherein said swirler section (SW) comprises swirler vanes (SWV) made to swirl a stream of fuel (F) and oxygen containing gas (OCG) entering the swirler section (SW) in a circumferential direction,wherein said mixing section (MX) conducts the premix (MFOCG) of fuel (F) and oxygen containing gas (OCG) to said outlet section (OT),wherein said outlet section (OT) discharges said premix (MFOCG) into said combustion zone (CZ) expanding the flow of premix (MFOCG) from a smaller axial cross section of said mixing section (MX) to a larger cross section of said combustion zone (CZ) which makes streamlines of said flow to diverge radially, and{'b': 1', '2, 'wherein a surface of the outlet section (OT) facing the flow of said premix (MFOCG) is provided with first fuel nozzles (FN) injecting fuel into said premix (MFOCG) into a radial inwardly inclined direction before the flow of said premix ( ...

FUEL SUPPLY SYSTEM FOR GAS TURBINE

A system includes a fuel supply system. The fuel supply includes a primary fuel supply, a fuel additive supply, and a common pipeline coupled to the primary fuel and fuel additive supplies. The primary fuel supply includes a primary fuel having a first average molecular weight. The fuel additive includes a fuel additive having a second molecular weight that is greater than the first average molecular weight. The common pipeline is configured to direct a mixture of the primary fuel and the fuel additive into a fuel nozzle. 1. A system , comprising: a primary fuel supply configured to deliver a primary fuel comprising substantially methane and having a first average molecular weight;', 'a fuel additive supply configured to deliver a fuel additive having a second average molecular weight that is greater than the first average molecular weight;', 'a common pipeline coupled to the primary fuel supply and the fuel additive supply and configured to direct a mixture of the primary fuel and the fuel additive into a fuel nozzle; and', 'a controller configured to control a ratio of the primary fuel to the fuel additive based on an operating mode of the fuel nozzle., 'a fuel supply system, comprising2. The system of claim 1 , wherein the primary fuel and the fuel additive each comprise one or more hydrocarbons claim 1 , the primary fuel comprises a first average number of carbon atoms per molecule claim 1 , the fuel additive comprises a second average number of carbon atoms per molecule claim 1 , and the second average number is at least two greater than the first average number.3. The system of claim 1 , comprising the fuel nozzle configured to receive the mixture of the primary fuel and the fuel additive.4. The system of claim 3 , wherein the fuel nozzle comprises a plurality of pilot tubes or a plurality of swirl vanes configured to mix the primary fuel claim 3 , the fuel additive claim 3 , and air.5. The system of claim 3 , comprising:a sensor configured to detect an ...

INDEPENDENTLY CONTROLLED THREE STAGE WATER INJECTION IN A DIFFUSION BURNER

A turbine engine combustion system is disclosed including a fuel nozzle assembly having three independently controlled stages of water injection. A first stage includes water mixed with a gaseous fuel upon inlet to the nozzle, where the first stage water mixes and travels with the gaseous fuel to be injected into a combustor. A second stage includes water injected into the combustor via a secondary liquid nozzle which is used for fuel oil during liquid fuel operation, but which may be used for the secondary water during gaseous fuel operation. A third stage includes water injected into the combustor via a plurality of nozzle holes known as an atomizing air cap. An algorithm and criteria are also defined for controlling the three stages of water injection to achieve the optimum balance of turbine operational criteria including NOx emissions, combustion dynamics and water impingement downstream of the nozzle. 1. A combustion system for a turbine engine , said combustion system comprising:a combustion chamber;a fuel nozzle assembly having a primary fuel outlet configured to provide a gaseous fuel into the combustion chamber where the gaseous fuel combusts in a flame zone, a secondary liquid nozzle configured to spray a secondary liquid into the flame zone, and an atomizing air cap configured to spray water into the flame zone;a gaseous fuel line in fluid communication with the primary fuel outlet for supplying the gaseous fuel to the primary fuel outlet;a primary water line, in fluid communication with the gaseous fuel line, which supplies primary water to mix with the gaseous fuel in the gaseous fuel line upstream of the primary fuel outlet;a secondary water line, in fluid communication with the secondary liquid nozzle, which supplies secondary water to the flame zone through the secondary liquid nozzle; anda tertiary water line, in fluid communication with the atomizing air cap, which supplies tertiary water to the flame zone through the atomizing air cap,where flow ...

HYDROGEN FUEL VAPORISER

A hydrogen fuel vaporiser () is shown for vaporising cryogenically-stored hydrogen fuel prior to injection into a gas turbine engine. The vaporiser () comprises a fuel offtake () configured and arranged to divert a portion of hydrogen fuel from a main fuel conduit (), a burner () configured and arranged to burn the portion of hydrogen fuel diverted from the main fuel conduit (), and a heat exchanger configured and arranged to transfer heat produced by the burner to hydrogen fuel in the main fuel conduit (). 1. A hydrogen fuel vaporiser for vaporising cryogenically-stored hydrogen fuel prior to injection into a gas turbine engine , comprising:a fuel offtake configured and arranged to divert a portion of hydrogen fuel from a main fuel conduit;a burner configured and arranged to burn the portion of hydrogen fuel diverted from the main fuel conduit; anda heat exchanger configured and arranged to transfer heat produced by the burner to hydrogen fuel in the main fuel conduit.2. The hydrogen fuel vaporiser of claim 1 , in which the burner comprises the heat exchanger.3. The hydrogen fuel vaporiser of claim 1 , the burner and the heat exchanger are separate units.4. The hydrogen fuel vaporiser of claim 1 , in which the heat exchanger comprises a first pass for hydrogen fuel and a second pass for exhaust from the burner.5. The hydrogen fuel vaporiser of claim 4 , the first pass is the main fuel conduit claim 4 , and the second pass surrounds the main fuel conduit.6. The hydrogen fuel vaporiser of claim 4 , in which the first pass comprises a plurality of fuel passages for hydrogen fuel received from the main fuel conduit claim 4 , and the second pass comprises a plurality of exhaust passages for exhaust received from the burner.7. The hydrogen fuel vaporiser of claim 1 , further comprising a pre-mixer configured and arranged to mix the portion of hydrogen fuel diverted from the main fuel conduit and a supply of air prior to admission into the burner.8. The hydrogen fuel ...

Systems and Methods for Late Lean Injection Premixing

A late lean injection combustor assembly may include a first interior in which a first fuel supplied thereto is combustible, a flow sleeve annulus including a second interior in which a second fuel supplied thereto is combustible, at least one fuel injector disposed about the second interior, and at least one elongate premixing conduit disposed about the flow sleeve annulus and in fluid communication with the at least one fuel injector. The at least one elongate premixing conduit may be in fluid communication with a compressor discharge air and the second fuel such that the compressor discharge air and the second fuel are premixed within the elongate premixing conduit before entering the second interior by way of the at least one fuel injector. 1. A late lean injection combustor assembly including a first fuel , a second fuel , and compressor discharge air , the late lean injection combustor assembly comprising:a first interior in which the first fuel supplied thereto is combustible;a flow sleeve annulus comprising a second interior in which the second fuel supplied thereto is combustible, the flow sleeve annulus fluidly coupling the first interior and the second interior;at least one fuel injector disposed about the second interior, the at least one fuel injector configured to supply the second fuel to the second interior;at least one elongate premixing conduit disposed about the flow sleeve annulus and in fluid communication with the at least one fuel injector; andthe at least one elongate premixing conduit being in fluid communication with the compressor discharge air and the second fuel such that the compressor discharge air and the second fuel are premixed within the elongate premixing conduit before entering the second interior by way of the at least one fuel injector.2. The late lean injection combustor assembly of claim 1 , further comprising a fuel manifold inlet disposed about the flow sleeve annulus claim 1 , the fuel manifold inlet being in fluid ...

SYSTEM AND METHOD FOR CONVERTING SOLIDS INTO FUEL

A system for converting a solid fuel into a fuel including a pyrolytic unit for producing a pyro gas comprising hydrocarbons, a synthesis gas production unit for converting the pyro gas into a synthesis gas comprising a mixture of hydrogen and carbon monoxide, and a gas-to-liquid unit for converting the synthesis gas into a fuel. 1. A method for converting a solid fuel into a fuel product , comprising:gasifying in a retort comprising one or more augers a solid fuel into a pyro gas comprising less than about 15% carbon dioxide, the gasifying being conducted at about 800° F. to about 1300° F., and wherein the solid fuel is gasifying while the one or more augers move it through the retort;reforming the pyro gas into a synthetic gas; andconverting the synthetic gas into a fuel product.2. The method of claim 1 , wherein the gasifying is conducted without introduction of an oxygen claim 1 , air claim 1 , or steam stream.3. The method of claim 1 , wherein the retort is sealed and equipped with air tight inlet and outlet valves configured to prevent introduction of air into the reactor during operation.4. The method of claim 1 , wherein the solid fuel comprises municipal solid waste claim 1 , municipal sludge claim 1 , biosolid claim 1 , rubber claim 1 , plastic claim 1 , coal claim 1 , organic waste claim 1 , inorganic waste claim 1 , medical waste claim 1 , by-products thereof claim 1 , or combinations thereof.5. The method of claim 1 , further comprising removing pollutants from the pyro gas.6. The method of claim 1 , further comprising removing pollutants from the synthetic gas to form a processed synthetic gas.7. The method of claim 1 , wherein the fuel product is a wax claim 1 , liquid claim 1 , a gas claim 1 , or a combination thereof.8. The method of claim 7 , wherein the liquid comprises diesel claim 7 , gasoline claim 7 , jet fuels claim 7 , alcohols claim 7 , or mixtures thereof.9. The method of claim 1 , wherein gasifying the solid fuel comprises continuous ...

Membrane Separation Of Carbon Dioxide From Natural Gas With Energy Recovery

Carbon dioxide is separated from natural gas using a single stage membrane separation system to produce a retentate gas that typically meets the specification for pipeline distribution of natural gas, and a permeate gas comprising methane that is combusted to generate power and/or heat, e.g. for use in providing the utility requirements of the process itself or for export to an integrated process. Advantages include an overall reduction in power consumption and improvement in process efficiency. 1. A process for separating carbon dioxide from natural gas , said process comprising:introducing natural gas feed comprising carbon dioxide to a single stage membrane separation system for separation of carbon dioxide from said natural gas feed to produce methane-enriched retentate gas and carbon dioxide-enriched permeate gas comprising methane;combusting at least a portion of said permeate gas to generate a combustion exhaust gas; andrecovering energy from said combustion.2. The process according to claim 1 , wherein said natural gas feed has a higher heating value of at least about 780 BTU/scf (31 MJ/Nm)3. The process according to claim 1 , wherein said natural gas feed comprises at least about 1.5% carbon dioxide.4. The process according to claim 1 , wherein said natural gas feed comprises no more than about 97% methane.5. The process according to claim 1 , wherein said natural gas feed is introduced to said single stage membrane separation system at a pressure from about 275 psi (19 bar) to about 1200 psi (85 bar).6. The process according to claim 1 , wherein said natural gas feed is introduced to said single stage membrane separation system at a temperature from about 40° C. to about 80° C.7. The process according to claim 1 , wherein said permeate gas has a higher heating value of at least about 400 BTU/scf (15 MJ/Nm).8. The process according to claim 1 , wherein said permeate gas is compressed prior to combustion.9. The process according to claim 1 , wherein energy ...

Aromatization of Non-Aromatic Hydrocarbon

The invention relates to producing aromatic hydrocarbon by aromatization of non-aromatic hydrocarbon, including feed pretreatment, aromatization of the aromatization feed's Chydrocarbon and C non-aromatic hydrocarbon, and recovery of an aromatic product. The invention also relates to modules for carrying out the pretreatment, aromatization, and recovery, and also modules for auxiliary function such as power generation. 1. A system for producing aromatic hydrocarbon , comprising:{'sup': '3', 'sub': 2', '3+', '2+', '3+', '2, "(a) a an aromatizer configured for (i) receiving a preselected amount ≧1 million standard cubic feet per day [MSCFD] (29,000 NMD) of an aromatization feed, the aromatization feed comprising Chydrocarbon and C non-aromatic hydrocarbon and having a preselected C non-aromatic hydrocarbon concentration in the range of from 15 mole % to 90 mole % per mole of aromatization feed, and (ii) aromatization of (A) at least a portion of the aromatization feed's C non-aromatic hydrocarbon and (B) at least a portion of the aromatization feed's Chydrocarbon to produce a reaction effluent comprising molecular hydrogen, non-aromatic hydrocarbon, and aromatic hydrocarbon; and"}(b) a product recoverer in fluidic communication with the aromatizer, the product recoverer being configured for recovering at least first and second products from the reaction effluent, wherein the first product comprises at least a portion of the reaction effluent's aromatic hydrocarbon and the second product comprises a tail gas containing (i) at least a portion of the reaction effluent's molecular hydrogen and (ii) at least a portion of the reaction effluent's non-aromatic hydrocarbon.2. The system of claim 1 , wherein the system further comprises a feed pretreater configured for (A) receiving ≧2 MSCFD (57 claim 1 ,000 NMD) of a gaseous feed and (B) producing the aromatization feed from the gaseous feed claim 1 , the gaseous feed comprising 0 mole % to 98 mole % methane claim 1 , 1 mole % ...

HYBRID EXPANDER CYCLE WITH PRE-COMPRESSION COOLING AND TURBO-GENERATOR

A gas turbine engine system includes a gas turbine engine and a fuel turbine system. The gas turbine engine includes an air inlet, compressor, combustor, turbine, and heat exchange system. The heat exchange system is configured to transfer thermal energy from an inlet air flow or exhaust air flow to a fuel to produce a gaseous fuel that is used to drive a fuel turbine and fuel pump and used for combustion in the gas turbine engine. The fuel turbine is in fluid communication with the heat exchange system and the combustor and configured to extract energy from expansion of the gaseous fuel. The fuel pump is configured to be driven by the fuel turbine and is in fluid communication with the heat exchanger system. 1. A gas turbine engine system comprising: an air inlet configured to receive an inlet air flow;', 'a compressor configured to compress the inlet air flow to produce a compressed air flow;', 'a combustor configured to combust a mixture of the compressed air flow and a gaseous fuel at a first pressure to produce a combustion gas flow;', 'a turbine configured to extract energy from expansion of the combustion gas flow to produce an exhaust gas flow; and', 'a heat exchange system configured to transfer thermal energy from an air flow to a fuel to produce the gaseous fuel at a second pressure greater than the first pressure, wherein the air flow is selected from the group consisting of the inlet air flow and the exhaust gas flow; and, 'a gas turbine engine comprising a fuel turbine in fluid communication with the heat exchange system and the combustor, wherein the fuel turbine is configured to extract energy from expansion of the gaseous fuel at the second pressure to produce the gaseous fuel at the first pressure; and', 'a fuel pump configured to be driven by the fuel turbine, wherein the fuel pump is in fluid communication with the heat exchanger system., 'a fuel turbine system comprising2. The gas turbine engine system of claim 1 , wherein the heat exchange ...

HYBRID EXPANDER CYCLE WITH TURBO-GENERATOR AND COOLED POWER ELECTRONICS

A gas turbine engine system includes a gas turbine engine and a turbo-generator. The gas turbine engine includes a heat exchange system configured to transfer thermal energy from an air flow (i.e., inlet air flow or exhaust gas flow) to a fuel to produce a gaseous fuel. The turbo-generator includes a fuel turbine fluidly coupled to the heat exchange system and a combustor of the gas turbine engine, a fuel pump configured to be driven by the fuel turbine and fluidly coupled to the heat exchange system, and a motor/generator configured to be driven by the fuel turbine. The fuel turbine is configured to extract energy from expansion of the gaseous fuel to produce a gaseous fuel for combustion in the combustor. The motor/generator includes a cooling jacket, which is fluidly coupled to the fuel pump. 1. A gas turbine engine system comprising: an air inlet configured to receive an inlet air flow;', 'a compressor configured to compress the inlet air flow to produce a compressed air flow;', 'a combustor fluidly coupled to the compressor and configured to combust a mixture of the compressed air flow and a gaseous fuel at a first pressure to produce a combustion gas flow;', 'a turbine fluidly coupled to the combustor and configured to extract energy from expansion of the combustion gas flow to produce an exhaust gas flow; and', 'a heat exchange system configured to transfer thermal energy from an air flow to a fuel to produce the gaseous fuel at a second pressure greater than the first pressure, wherein the air flow is selected from the group consisting of the inlet air flow and the exhaust gas flow; and, 'a gas turbine engine comprising a fuel turbine fluidly coupled to the heat exchange system and the combustor, wherein the fuel turbine is configured to extract energy from expansion of the gaseous fuel at the second pressure to produce the gaseous fuel at the first pressure;', 'a fuel pump configured to be driven by the fuel turbine, wherein the fuel pump is fluidly coupled ...

METHODS AND SYSTEMS FOR HEAVY FUEL OIL IN GAS TURBINES

A control system for a gas turbine includes a controller. The controller includes a processor configured to receive a plurality of signals from sensors disposed in the gas turbine engine system, wherein the gas turbine system engine comprises a compressor section fluidly coupled to a gas turbine section. The processor is additionally configured to derive a vanadium content in a gas turbine engine fuel based on at least one of the plurality of signals. The processor is also configured to determine if a control curve should be adjusted based on the vanadium content in the gas turbine engine fuel, and if it is determined that the control curve should be adjusted, then deriving an adjustment to the control curve based on the vanadium content, and applying the adjustment to the control curve to derive an adjusted control curve. 1. A control system for a gas turbine system , comprising:a controller comprising a processor, wherein the processor is configured to:receive a plurality of signals from sensors disposed in the gas turbine engine system, wherein the gas turbine system engine comprises a compressor section fluidly coupled to a gas turbine section;derive a vanadium content in a gas turbine engine fuel based on at least one of the plurality of signals;determine if a control curve should be adjusted based on the vanadium content in the gas turbine engine fuel; andif it is determined that the control curve should be adjusted, then deriving an adjustment to the control curve based on the vanadium content, and applying the adjustment to the control curve to derive an adjusted control curve.2. The control system of claim 1 , wherein the control curve is plotted against a compressors pressure ratio (CPR) ordinate axis and an exhaust temperature abscissa axis.3. The control system of claim 2 , wherein the processor is configured to derive a CPR and a sensed exhaust temperature based on the plurality of signals claim 2 , and to adjust fuel flow claim 2 , air flow claim 2 , ...

AUTOMATED TUNING OF MULTIPLE FUEL GAS TURBINE COMBUSTION SYSTEMS

Provided herein is a method for automated control of the gas turbine fuel composition through automated modification of the ratio of fuel gas from multiple sources. The method includes providing first and second fuel sources. The method further includes sensing the operational parameters of a turbine and determining whether the operational parameters are within preset operational limits. The method also adjusting the ration of the first fuel source to the second fuel source, based on whether the operational parameters are within the preset operational limits. 1. A tuning system for tuning the operation of a gas turbine , the system comprising:operational turbine controls for controlling operational control elements of the turbine, receiving operational data about the turbine,', 'providing a hierarchy of tuning issues,', 'determining whether sensed operational data is within predetermined operational limits and producing one or more indicators if said operational data is not within predetermined operational limits,', 'ranking the one or more indicators to determine the dominant tuning concern, and', 'tuning the operation of the turbine based on the dominant tuning concern., 'a tuning controller communicating with the operational turbine controls, the turbine controller configured to tune the operation of the turbine in accordance with the following'}2. The tuning system according to claim 1 , wherein tuning the operation of the turbine comprises making incremental adjustments of at least one operational control element of the turbine.3. The tuning system according to claim 1 , further comprising at least one sensor for sensing at least one of combustor dynamics or turbine exhaust emissions.4. The tuning system according to claim 1 , wherein the one or more indicators are ranked based on the severity of each indicator.5. The tuning system according to claim 4 , wherein the one or more indicators are further ranked based on the tuning priorities claim 4 , such that ...

FUEL DELIVERY SYSTEM

This invention concerns a fuel delivery system for an engine, in which two or more discrete fuel compositions are made available to the engine. The system has a vapour trail detection sensor configured to generate a detection signal indicative of a characteristic of a vapour trail. A regulator is configured to regulate a percentage of a first and a second fuel composition delivered to the engine as resultant fuel composition. A controller is arranged to undertake a search of trial fuel compositions by controlling the regulator to deliver to the engine a plurality of trial fuel compositions having different ratios of the first and second fuel compositions. The controller controls delivery of a resultant fuel composition to the engine in response to the vapour trail characteristic detection signals for said plurality of trial fuel compositions. 1. A fuel delivery system for an engine , the system comprising:a vapour trail detection sensor configured to generate a detection signal indicative of a characteristic of a vapour trail;a regulator configured to regulate a volume of a first and a second fuel composition delivered to the engine as resultant fuel composition; anda controller arranged to undertake a search of trial fuel compositions by controlling the regulator to deliver to the engine a plurality of trial fuel compositions having different ratios of the first and second fuel compositions and to control delivery of a resultant fuel composition to the engine in response to the vapour trail characteristic detection signals for said plurality of trial fuel compositions.2. A fuel delivery system according to claim 1 , wherein the controller comprises a search algorithm arranged to perform a sweep through a range of fuel composition ratios upon detection of a change in one or more engine operating condition and/or ambient condition.3. A fuel delivery system according to claim 2 , wherein the ambient condition comprises the sensed vapour trail characteristic and/or the ...

AIRCRAFT ENGINE FUEL SYSTEM

This invention concerns a method of delivering fuel to an aircraft engine , which involves providing a plurality of distinct fuel sources , a first fuel source comprising a first fuel having a first aromatic content and a second fuel source comprising a second fuel having a second aromatic content. One or more ambient atmospheric condition is determined for at least a portion of a flight path of the aircraft, said condition being indicative of a likelihood of contrail formation by the engine . A desirous fuel composition for combustion by the engine is determined based upon the one or more ambient atmospheric condition and a ratio of the first and second fuels from said respective fuel sources is selected according to said desirous fuel composition. The selected ratio of the first and second fuels is delivered to the aircraft engine 2. A method according to claim 1 , wherein the plurality of distinct fuel sources are provided on the ground and the determining of the ambient atmospheric condition comprises determining actual ambient conditions or predicting ambient conditions for a proposed flight path.3. A method according to claim 2 , wherein the blending of the first and second fuels is performed prior to delivery of the final fuel composition to one or more tank on the aircraft.4. A method according to claim 1 , wherein the determining of a desirous fuel composition comprises determining a desirous aromatic content of the fuel composition for delivery to the engine.5. A method according claim 1 , wherein the average value comprises an average lower threshold value claim 1 , such that an instantaneous value of said fuel property is permitted to fall below said lower threshold provided the average value is equal to or greater than said threshold.6. A method according to claim 1 , wherein the determining of a desirous fuel composition comprises applying a plurality of predetermined threshold values of a fuel property for the desirous fuel composition and determining ...

Gas Turbine Combustor and its Operating Method

A hydrogen content fuel can be stably ignited using a gaseous fuel that does not contain hydrogen and dispersibility of the hydrogen content fuel is enhanced. 1. A gas turbine combustor comprising a startup fuel pipe in which a startup fuel circulates;', 'a first main fuel pipe in which a main fuel circulates;', 'a second main fuel pipe in which the main fuel circulates;', 'a fuel mixer to which the startup fuel pipe and the first main fuel pipe are connected;', 'an inner fuel nozzle to which the fuel mixer is connected;', 'a plurality of outer fuel nozzles to which the second main fuel pipe is connected;', 'a startup fuel control valve provided in the startup fuel pipe;', 'a first fuel control valve provided in the first main fuel pipe; and', 'a second fuel control valve provided in the second main fuel pipe., 'a burner including2. The gas turbine combustor according to claim 1 , further comprising:a controller configured to control the startup fuel control valve, the first fuel control valve, and the second fuel control valve, whereinthe controller executes procedures including(1) raising an opening degree of the startup fuel control valve to supply the startup fuel to the inner fuel nozzle,(2) raising an opening degree of the second fuel control valve to supply the main fuel to the plurality of outer fuel nozzles when a gas turbine load rises up to a first set value, and(3) raising an opening degree of the first fuel control valve to supply a mixed gaseous fuel of the startup fuel and the main fuel to the inner fuel nozzle when the gas turbine load further rises up to a second set value.3. The gas turbine combustor according to claim 2 , whereinthe controller executes procedures including(4) closing the first fuel control valve to stop to supply the main fuel to the inner fuel nozzle, and lowering the opening degree of the second fuel control valve when the opening degree of the second fuel control valve is lowered and the gas turbine load falls down to a third ...

METHODS AND SYSTEMS FOR SUPPLYING FUEL TO GAS TURBINE ENGINES

Methods and systems for supply of fuel for a turbine-driven fracturing pump system used in hydraulic fracturing may be configured to identify when the supply pressure of primary fuel to a plurality of gas turbine engines of a plurality of hydraulic fracturing units falls below a set point, identify a gas turbine engine of the fleet of hydraulic fracturing units operating on primary fuel with highest amount of secondary fuel available, and to selectively transfer the gas turbine engine operating on primary fuel with the highest amount of secondary fuel from primary fuel operation to secondary fuel operation. Some methods and systems may be configured to transfer all gas turbine engines to secondary fuel operation and individually and/or sequentially restore operation to primary fuel operation and/or to manage primary fuel operation and/or secondary fuel operation for portions of the plurality of gas turbine engines. 1. A method of controlling fuel supply to a plurality of gas turbine engines associated with a hydraulic fracturing system , the method comprising:(a) receiving a signal indicating that supply pressure of primary fuel to one or more gas turbine engines of the plurality of gas turbine engines falls below a set point; initiating a timer; and', 'increasing a data sampling rate associated with the plurality of gas turbine engines;, '(b) based at least in part on the signal(c) if the supply pressure of primary fuel to the one or more gas turbine engines remains below the set point when the timer reaches a predetermined end time, identifying a gas turbine engine of the plurality of gas turbine engines operating on primary fuel having a highest amount of secondary fuel available; and(d) causing supply of secondary fuel to the identified gas turbine engine in place of at least some of the primary fuel supplied to the identified gas turbine engine.2. The method of claim 1 , further comprising repeating (a) claim 1 , (b) claim 1 , (c) claim 1 , and (d) for at least ...

MULTIPLE CIRCUIT MANIFOLDS

A fluid manifold includes a manifold body, a first annular passage and a second annular passage. The first annular passage is defined within the manifold body between a first passage inlet and a first passage outlet downstream from the first passage inlet. The second annular passage is defined within the manifold body nested radially outward from the first annular passage, and between a second passage inlet and a second passage outlet downstream from the second passage inlet. The first and second annular passages are concentric about a manifold axis. The first passage outlet and the second passage outlet are positioned at the same axial position relative to the manifold axis. 1. A fluid manifold comprising:a manifold body;a first annular passage defined within the manifold body between a first passage inlet and a first passage outlet downstream from the first passage inlet; anda second annular passage defined within the manifold body nested radially outward from the first annular passage, and between a second passage inlet and a second passage outlet downstream from the second passage inlet, wherein the first and second annular passages are concentric about a manifold axis, wherein the first passage outlet and the second passage outlet are positioned at the same axial position relative to the manifold axis.2. The fluid manifold as recited in claim 1 , wherein the first passage outlet and the second passage outlet are circumferentially offset from one another relative to the manifold axis.3. The fluid manifold as recited in claim 1 , further comprising at least one additional annular passage defined within the manifold body claim 1 , wherein a first one of the at least one additional annular passage is nested radially outward of the second annular passage.4. The fluid manifold as recited in claim 1 , wherein the manifold body includes a cylindrical dividing portion claim 1 , wherein the first annular passage and the second annular passage are fluidically isolated ...

Systems and Methods for Injection of Bio-Diesel into a Gas Turbine Combustor

Certain embodiments may include systems and methods that comprise a first unit controller associated with a first gas turbine and a second unit controller associated with a second gas turbine. A first unit human machine interface is coupled to the first unit controller and is operable to provide first blend information to the first unit controller. Additionally, a second unit human machine interface is coupled to the second unit controller and is operable to provide second blend information to the second unit controller. A splitter panel, coupled to the first unit controller and the second unit controller, is operable to transfer control of a plurality of common skids between the first unit controller and the second unit controller. The transfer of control may occur by toggling a plurality of relays housed in the splitter panel. A plurality of common skids is operable to provide biofuel to a plurality of injection skids. The plurality of common skids may comprise a heating skid, a filtration skid, and a pumping skid shared by the first gas turbine and the second gas turbine. 1. A system for injecting biofuel into a gas turbine system , comprising:a first unit controller associated with a first gas turbine;a second unit controller, coupled to the first unit controller; associated with a second gas turbine;a first unit human machine interface coupled to the first unit controller, wherein the first unit human machine interface is operable to provide first blend information to the first unit controller;a second unit human machine interface coupled to the second unit controller, wherein the second unit human machine interface is operable to provide second blend information to the second unit controller; anda splitter panel, coupled to the first unit controller and the second unit controller, wherein the splitter panel is operable to transfer control of a plurality of common skids between the first unit controller and the second unit controller;wherein the plurality of ...

CARBON DIOXIDE MEMBRANE SEPARATION SYSTEM IN COAL GASIFICATION PROCESS, AND INTEGRATED COAL GASIFICATION COMBINED CYCLE POWER GENERATION FACILITY USING SAME

The carbon dioxide membrane separation system in a coal gasification process contains introduction of a mixed gas of hydrogen (H) and carbon dioxide (CO) in a high temperature and high pressure condition generated through water gas shift reaction from a water gas shift reaction furnace, while maintaining the temperature and pressure condition, to a zeolite membrane module containing a zeolite membrane for removing carbon dioxide, thereby removing carbon dioxide and generating a fuel gas rich in hydrogen. The fuel gas rich in hydrogen in a high temperature and high pressure condition discharged from the zeolite membrane module is fed to a gas turbine of the power generation facility while maintaining the temperature and pressure condition. 1. A carbon dioxide membrane separation system in a coal gasification process , comprising introduction of a mixed gas of hydrogen (H) and carbon dioxide (CO) in a high temperature and high pressure condition generated through water gas shift reaction from a water gas shift reaction furnace , while maintaining the temperature and pressure condition , to a zeolite membrane module containing a zeolite membrane for removing carbon dioxide , thereby removing carbon dioxide and generating a fuel gas rich in hydrogen.2. An integrated coal gasification combined cycle power generation facility comprising the carbon dioxide membrane separation system in a coal gasification process according to claim 1 , wherein the fuel gas rich in hydrogen in a high temperature and high pressure condition discharged from the zeolite membrane module is fed to a gas turbine of the power generation facility while maintaining the temperature and pressure condition.3. A carbon dioxide membrane separation system in a fuel gas production process claim 1 , comprising plural fuel gas generation and carbon dioxide separation units connected continuously claim 1 , each of which contains the water gas shift reaction furnace and the zeolite membrane module containing a ...

METHOD OF PRODUCING CARBON BLACK AND GENERATING ENERGY

There is provided a process of producing carbon black and generating energy. The process includes converting a carbon black-yielding material supply into reaction product material. The reaction product material includes gaseous product material and solid particulate matter. The solid particulate matter includes carbon black. At least a fraction of the carbon black is recovered, and at least a fraction of the gaseous product material is combusted and used to effect generation of energy. 1. A process of producing carbon black and generating energy comprising:converting a carbon black-yielding material supply into reaction product material, wherein the reaction product material includes gaseous product material and solid particulate matter, wherein the solid particulate matter includes carbon black;treating a solid particulate matter-comprising intermediate supply material, including at least a fraction of the gaseous product material, so as to effect production of a solid particulate matter-depleted intermediate supply material, wherein the ratio of [mass of solid particulate matter within the solid particulate matter-depleted intermediate supply material] to [total mass of solid particulate matter-depleted intermediate supply material] is less than the ratio of [mass of the solid particulate matter within the solid particulate matter-comprising intermediate supply material] to [total mass of the solid particulate matter-comprising intermediate supply material];supplying a fuel supply material, including at least a fraction of the solid particulate matter-depleted intermediate supply material, to a combustor; andcombusting at least a fraction of the fuel supply material.2. The process as claimed in ;wherein the treating includes separating a solid particulate matter-comprising product material from the solid particulate matter-comprising intermediate supply material, such that production of the solid particulate matter-depleted intermediate supply material is effected ...

MODULAR SYNGAS SYSTEM, MARINE VESSEL POWERED THEREBY, AND METHOD OF OPERATION

A land based or marine vessel based system for generating power from syngas utilizes a feedstock of waste material acquired from waste dumps, municipalities, and/or ports of call of the marine vessel. The marine vessel or land based system can be retrofitted to be fueled by the waste material. The syngas is used to provide propulsive and/or electrical power for the marine vessel or the land based system. The waste material is not just a feedstock for the syngas but is provided with payment from the ports of call to take the waste material away. The marine vessel also collects garbage floating on the waterway along the voyage between the various ports of call for use as feedstock in the production of syngas. The modular syngas generation system further generates Hfrom the syngas. The Hgenerated thereby is used to fuel an Hfuel cell for the generation of electrical power. 1. A modular system for generating power from syngas , comprising:a modular system for producing syngas from a feedstock;a modular combustor or a combined modular combustor and modular boiler assembly; andone or more modular turbines; whereinat least a portion of the syngas produced by the modular system for producing syngas is burned in the modular combustor to produce hot exhaust gases; whereinthe hot exhaust gases are passed through the one or more modular turbines, or are directed to the modular boiler to produce steam that is passed through the one or more modular turbines.2. The modular system of claim 1 , wherein the modular system is selected from the group consisting of a system disposed on land and a system disposed on a marine vessel.3. The modular system of claim 2 , wherein a portion of the syngas produced by the modular system for producing syngas is stored in a storage tank.4. The modular system of claim 2 , wherein the system is disposed on a marine vessel and the marine vessel is selected from the group consisting of a self-powered marine vessel and an unpowered barge that is towed ...

Gas turbine combustor and method of operating the same

The gas turbine combustor and the operation method thereof are designed to minimize visualization of exhaust gas from the gas turbine upon switching of the gas turbine fuel from the oil fuel to the gas fuel. Upon switching of the combustion by the pilot burner from the oil burning to the gas burning, the gas fuel is supplied to the main burners so as to start the gas burning. Then the gas fuel is supplied to the pilot burner to start the gas burning.

Fuel delivery

A fuel delivery system (201) is shown for delivering the hydrogen fuel from a cryogenic storage system to a fuel injection system in a gas turbine engine. The fuel delivery system includes a pump (301), a metering device (302), and a fuel heating system (303,304) for heating the hydrogen fuel to an injection temperature for the fuel injection system.

METHOD OF OPERATING AN AIRCRAFT ENGINE AND FUEL SYSTEM USING MULTIPLE FUEL TYPES

The method can include simultaneously conveying a controlled flow rate of jet fuel from a first reservoir area of the aircraft to a fuel nozzle across at least one auxiliary system, including the at least one auxiliary system using the controlled flow rate of jet fuel for operation and conveying a controlled flow rate of an alternative fuel from a second reservoir area of the aircraft to the fuel nozzle. 1. A method of operating an aircraft gas turbine engine having at least one fuel nozzle in fluid communication with a combustion chamber , the method comprising:conveying a first fuel at a first controlled flow rate from a first reservoir of the aircraft towards the at least one fuel nozzle through at least one auxiliary system, the at least one auxiliary system using the first fuel for operation, the at least one auxiliary system requiring a minimal flow rate of the first fuel for operation, the first controlled flow rate being equal to or greater than the minimal flow rate;directing at least a portion of the first fuel from a location downstream of the at least one auxiliary system towards the first reservoir; andsimultaneously to the conveying of the first fuel at the first controlled flow rate, conveying an alternative fuel at a second controlled flow rate from a second reservoir of the aircraft towards the at least one fuel nozzle.2. The method of wherein an engine power requirement is satisfied solely by the alternative fuel claim 1 , the redirecting of the at least the portion of the first fuel including redirecting an entirety of the first fuel towards the first reservoir.3. The method of wherein the at least one auxiliary system includes a fuel to oil heat exchanger claim 1 , including passing at least some of the first fuel at the first controlled flow rate through the fuel to oil heat exchanger and using the of first fuel at the first controlled flow rate to cool oil in the fuel to oil heat exchanger.4. The method of wherein the at least one auxiliary ...

GAS TURBINE USING A CRYOGENIC FUEL AND EXTRACTING WORK THEREFROM

There is disclosed a method of operating a gas turbine engine of a type having a compressor section, a combustor section, and a turbine section arranged in flow series. The method involves the steps of: providing a supply of cryogenic liquid fuel; vaporising the cryogenic liquid fuel to produce a gaseous fuel; expanding said gaseous fuel in at least one fuel turbine external to the engine's turbine section; and thereafter directing said expanded gaseous fuel into the engine's combustion section for combustion therein. A related gas turbine arrangement configured for implementation of the method is also disclosed. 1. A method of operating a gas turbine engine having a compressor section , a combustor section , and a turbine section arranged in flow series , the method comprising the steps of: providing a supply of cryogenic liquid fuel; vaporising the cryogenic liquid fuel to produce a gaseous fuel; expanding said gaseous fuel in at least one fuel turbine external to the engine's turbine section ; and thereafter directing said expanded gaseous fuel into the engine's combustion section for combustion therein.2. A method according to claim 1 , wherein the or each said fuel turbine is used to drive a load.3. A method according to claim 2 , wherein the engine's turbine section includes a turbine which is also configured to drive said load claim 2 , such that the or each said fuel turbine is operable to augment the power output of the engine in driving said load.4. A method according to claim 1 , wherein said gaseous fuel is expanded in a plurality of said fuel turbines arranged in flow series.5. A method according to claim 1 , wherein said cryogenic liquid fuel is vaporized by being passed through a heat exchanger.6. A method according to claim 5 , wherein said heat exchanger is an inlet cooler arranged to cool inlet air before the inlet air passes through the engine's compressor section.7. A method according to claim 5 , wherein said heat exchanger is an intercooler ...

COMBUSTOR ARRANGEMENT FOR A GAS TURBINE

A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner. 1. A combustor arrangement for a gas turbine assembly , comprising:a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection, wherein the first burner, the first combustion chamber, the mixer for admixing the dilution gas before the second burner and the second combustion chamber are arranged in a row to form a flow path extending between the first combustion chamber and the second burner, wherein the combustor arrangement includes a central lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and optionally into the second burner, wherein the central lance body includes at least one fuel duct for providing fuel for the first burner and/or for the second burner.2. The combustor arrangement according to claim 1 , wherein at least one of the fuel ducts are double line ducts arranged within the lance body to transport a first liquid fuel product and a second gaseous fuel product to the burners.3. The combustor arrangement according to claim 1 , wherein ...

System and Method for Extending Minimum Turn Down Load of Combined Cycle Power Plant

A system including a gas turbine system and an electrolysis unit configured to produce a hydrogen gas for reducing a minimum emissions compliance load of the gas turbine system. 1. A system comprising:a gas turbine system; andan electrolysis unit configured to produce a hydrogen gas for reducing a minimum emissions compliance load of the gas turbine system.2. The system of claim 1 , wherein the electrolysis unit is configured to generate the hydrogen gas from a supply of steam.3. The system of claim 2 , comprising a first electrical generator driven by the gas turbine system.4. The system of claim 3 , wherein the first electrical generator is configured to supply an electrical power to the electrolysis unit.5. The system of claim 2 , comprising a heat recovery steam generator configured to recover heat from an exhaust output by the gas turbine system claim 2 , generate the steam with the recovered heat claim 2 , and supply the steam to the electrolysis unit.6. The system of claim 5 , comprising a steam turbine system coupled to the heat recovery steam generator.7. The system of claim 6 , comprising a second electrical generator driven by to the steam turbine system.8. The system of claim 7 , wherein the second electrical generator is configured to supply an electrical power to the electrolysis unit.9. The system of claim 1 , comprising a storage container configured to store the hydrogen gas created by the electrolysis unit for use by the gas turbine system.10. A system comprising:a gas turbine system configured to drive a load with combustion gases;a heat recovery steam generator configured to generate steam by recovering heat from the combustion gases; andan electrolysis unit configured to receive the steam from the heat recovery steam generator for use in producing hydrogen gas to reduce a minimum emissions compliance load of the gas turbine system.11. The system of claim 10 , comprising a storage container configured to capture the hydrogen produced by the ...

Combustion Chamber Of A Gas Turbine, Gas Turbine And Method For Operating The Same

A combustion chamber of a gas turbine combusts a fuel in the presence of combustion air. The combustion chamber is configured as dual-fuel combustion chamber, wherein the combustion chamber, in a gas fuel operating mode, is supplied with a mixture of a gaseous fuel and combustion air via a main swirl body. In a liquid fuel operating mode, the combustion chamber is supplied with a liquid fuel via an atomization apparatus and combustion air via the main swirl body. The atomization apparatus has an atomization lance with an atomization nozzle centrally arranged with respect to a longitudinal center axis of a prechamber of the combustion chamber. The atomization nozzle of the central atomization lance includes a swirl chamber and, downstream of the swirl chamber, a nozzle orifice. The swirl chamber is supplied with the liquid fuel via a radial swirl generator and an axial swirl generator. 111. A combustion chamber () of a gas turbine , for combusting a fuel in the presence of combustion air , the combustion chamber () being configured as a dual fuel combustion chamber , comprising:{'b': '2', 'a main swirl body ();'}{'b': 3', '6', '7', '7', '9', '9', '28, 'an atomization apparatus () having an atomization lance () that comprises an atomization nozzle (), the atomization nozzle () comprising a swirl chamber () and, downstream of the swirl chamber (), a nozzle orifice ();'}{'b': '5', 'a prechamber ();'}{'b': '10', 'a radial swirl generator (); and'}{'b': '11', 'an axial swirl generator (),'}{'b': '1', 'claim-text': [{'b': 1', '2, 'in a gas fuel operating mode the combustion chamber () is supplied with a mixture of gaseous fuel and combustion air via the main swirl body (), and'}, {'b': 1', '3', '2, 'in a liquid fuel operating mode the combustion chamber () is supplied with liquid fuel via the atomization apparatus () and supplied with combustion air via the main swirl body (),'}], 'wherein the combustion chamber () is configured such that{'b': 7', '4', '1', '4', '5, ' ...

METHOD FOR PURGING FUEL CHANNEL, PURGING DEVICE FOR EXECUTING SAID METHOD, AND GAS TURBINE INSTALLATION PROVIDED WITH SAID DEVICE

A water supplying step of supplying water to a liquid-fuel channel of a nozzle is executed during a liquid fuel supply state in which only liquid fuel is supplied to the nozzle; a post-switch water purging step of supplying water to the liquid-fuel channel of the nozzle is executed during a gas fuel supply state in which only gas fuel is supplied to the nozzle; and a mid-switch water purging step of supplying water to the liquid-fuel channel of the nozzle is executed during a fuel switching state which is a state of transition from the liquid fuel supply state to the liquid fuel supply state. A second flow rate of water supplied in the mid-switch water purging step is lower than a first flow rate of water supplied in the water supplying step. In the post-switch water purging step, water is temporarily supplied at a third flow rate which is higher than the second flow rate. 1. A method for purging a fuel channel in a combustor having a nozzle that selectively sprays liquid fuel and gas fuel , the nozzle having formed therein a liquid-fuel channel , through which the liquid fuel flows and which is open at a tip portion of the nozzle , and a gas-fuel channel , through which the gas fuel flows and which is open at the tip portion of the nozzle , the method for purging the fuel channel comprising:a water supplying step of supplying water to the liquid-fuel channel in a liquid fuel supply state in which, of the liquid fuel and the gas fuel, only the liquid fuel is supplied to the nozzle;a mid-switch water purging step of supplying water to the liquid-fuel channel at the time of a fuel switching state, during which, from the liquid fuel supply state, the liquid fuel being supplied to the liquid-fuel channel of the nozzle decreases while the gas fuel starts to be supplied to the gas-fuel channel of the nozzle, and the gas fuel supplied to the gas-fuel channel increases; anda post-switch water purging step of supplying water to the liquid-fuel channel after the fuel ...

System and method for determining fuel composition for fuel used in gas turbines

A system is provided. The system includes a combustor assembly that receives a fuel flow. The system includes a pressure sensor disposed within the combustor assembly that measures a pressure of the fuel flow from a fuel supply to a fuel nozzle of the combustor assembly. The system includes a controller communicatively coupled to the pressure sensor. The controller is configured to receive a pressure measurement from the pressure sensor. The pressure measurement is a current operating parameter of the combustor assembly. The controller is configured to determine a predicted fuel flow based at least in part on the pressure measurement, determine a fuel composition factor based on a comparison of the predicted fuel flow with a commanded fuel flow, and adjust control of the combustor assembly based on the fuel composition factor. The fuel composition factor is indicative of a change in a fuel composition of the fuel flow.

POWER GENERATION SYSTEM AND OPERATING METHOD THEREOF

A power generation system has a fuel cell, a gas turbine, an exhausted oxidant line, a fuel gas supply line, an exhausted fuel gas supply line, a supply amount adjustment unit, and a control system including an information acquisition unit, a calculation unit, and a fuel gas supply control unit. The information acquisition unit acquires an output command of the gas turbine, an atmospheric temperature, a temperature of the exhausted oxidant supplied to the gas turbine, and a temperature of the exhausted fuel gas supplied to the gas turbine. The calculation unit calculates a heat input of the exhausted oxidant, calculates a heat input of the exhausted fuel gas, and calculates by the output command and the atmospheric temperature to calculate a gas turbine heat input command. 1. A power generation system comprising:a fuel cell;a gas turbine including a combustor;an exhausted oxidant line that supplies exhausted oxidant from the fuel cell to the combustor;a fuel gas supply line that supplies fuel gas to the combustor;an exhausted fuel gas supply line that supplies exhausted fuel gas from the fuel cell to the combustor;a supply amount adjustment unit that adjust an amount of the fuel gas supplied from the fuel gas supply line to the combustor; anda control system including an information acquisition unit that acquires information from each unit, an calculation unit that executes an calculation process using the information acquired by the information acquisition unit, and a fuel gas supply control unit that controls the supply amount adjustment unit using a result operated by the calculation unit and controls a flow rate of fuel gas supplied to the gas turbine,wherein the information acquisition unit acquires an output command of the gas turbine, an atmospheric temperature, a temperature of the exhausted oxidant supplied to the gas turbine, and a temperature of the exhausted fuel gas supplied to the gas turbine, andthe calculation unit calculates a heat input of the ...

BURNER, BURNER SYSTEM, INTEGRATED GASIFICATION COMBINED CYCLE, AND METHOD FOR MOVING BURNER

To provide a burner that makes it possible to reduce error displacement of the distal end position of a burner main body when the burner main body is inserted. A burner () includes: a burner main body (); a plurality of driving cylinders () that are disposed parallel to a direction of an axis line in which the burner main body () moves, and drive movement of the burner main body (); a connecting member that connects the burner main body () and the plurality of driving cylinders (); and a fitting member () that is provided between the burner main body () and the connecting member, and constrains relative movement in the direction of the axis line (X) and permits relative movement in a direction perpendicular to the direction of the axis line (X). 1. A burner comprising:a burner main body;a plurality of driving cylinders that are disposed parallel to a direction of an axis line in which the burner main body moves, and drive movement of the burner main body;a connecting member that connects the burner main body and the plurality of driving cylinders; anda fitting member that is provided between the burner main body and the connecting member, and constrains relative movement in the direction of the axis line and permits relative movement in a direction perpendicular to the direction of the axis line.2. The burner according to claim 1 , further comprising:a burner-main-body-side groove provided on a periphery-side surface of the burner main body; anda connecting-member-side groove provided on a surface of the connecting member that faces the periphery-side surface of the burner main body in a position that faces the burner-main-body-side groove,wherein the fitting member is fitted and fixed into the burner-main-body-side groove and the connecting-member-side groove.3. The burner according to or claim 1 , comprising one electric motor that moves the connecting member connecting the plurality of driving cylinders in the direction of the axis line.4. The burner according to ...

Two-Shaft Gas Turbine Having Steam Injection Mechanism

A two-shaft gas turbine having a steam injection mechanism, comprising: a compressor having an inlet guide vane, a combustor, turbines, a heat recovery steam generator, a steam valve to control a flow rate of steam to be supplied to the combustor, a fuel valve to control a flow rate of fuel to be supplied to the combustor, characterized in that, the two-shaft gas turbine further comprising: a rotational frequency meter, a flow rate meter to measure the flow rate of the steam to be supplied to the combustor from the heat recovery steam generator, an inlet guide vane position gauge provided to the compressor, a steam valve position gauge, and a control system calculates and outputs command signals to operate openings of the fuel valve, the steam valve, and the inlet guide vane based on measurement signals obtained by the rotational frequency meter, the inlet guide vane position gauge, or the steam valve position gauge, and an output increase command value to the gas turbine. 1. A two-shaft gas turbine having a steam injection mechanism , comprising: a compressor having an inlet guide vane to control a flow rate of air to be introduced ,a combustor to mix the air compressed by the compressor with fuel and combust the air with the fuel to generate a combustion gas,a turbine having a high pressure turbine driven by the combustion gas generated in the combustor and a low pressure turbine disposed on a downstream side of the high pressure turbine,a heat recovery steam generator to generate steam using an exhaust gas discharged from the low pressure turbine as a heat source,a steam system to supply the combustor with the steam generated by the heat recovery steam generator,a fuel valve provided to a fuel system to supply the combustor with the fuel and control a flow rate of the fuel to be supplied to the combustor,a steam valve provided to the steam system and control a flow rate of the steam to be supplied from the heat recovery steam generator to the combustor through ...

PURGING SYSTEM FOR TURBINE FRACTURING APPARATUS GROUP, PURGING METHOD AND TURBINE FRACTURING APPARATUS GROUP

Embodiments of the present disclosure provide a purging system for a turbine fracturing apparatus group and a turbine fracturing apparatus group. The turbine fracturing apparatus group includes a plurality of gas turbines, each gas turbine includes a plurality of fuel supply pipelines. The purging system includes: a first air compressor and a purging pipeline, the purging pipeline communicates the first air compressor with the plurality of fuel supply pipelines of each gas turbine in the turbine fracturing apparatus group, and the first air compressor is configured to, in a case where at least part of the plurality of fuel supply pipelines is stopped from supplying fuel, supply compressed air to the at least part of the plurality of fuel supply pipelines which has been stopped from supplying fuel, so as to perform purging. 1. A purging system for a turbine fracturing apparatus group , wherein the turbine fracturing apparatus group comprises a plurality of turbine fracturing apparatuses , each of the plurality of turbine fracturing apparatuses comprises a gas turbine , each gas turbine comprises a plurality of fuel supply pipelines ,the purging system comprises:a first air compressor and a purging pipeline, wherein the purging pipeline is configured to communicate the first air compressor with the plurality of fuel supply pipelines of each gas turbine in the turbine fracturing apparatus group, the first air compressor is configured to, in a case where at least part of the plurality of fuel supply pipelines is stopped from supplying fuel, supply compressed air to the at least part of the plurality of fuel supply pipelines which has been stopped from supplying fuel, so as to perform purging.2. The purging system for the turbine fracturing apparatus group according to claim 1 , wherein the first air compressor is arranged outside a plurality of turbine fracturing apparatuses of the turbine fracturing apparatus group.3. The purging system for the turbine fracturing ...

SYSTEM AND METHOD FOR MONITORING FUEL ADDITIVES

A system for monitoring fuel additives on board a vehicle includes a fuel line carrying fuel from a fuel source to an engine; a fuel additive sensor configured to measure concentration of additives in fuel at a point along the fuel line; a fuel additive dispenser connected in parallel to the fuel line; at least one flow control device for controlling an amount of flow from the fuel line into the fuel additive dispenser; and a controller configured to receive input from the fuel additive sensor and to control the flow control device to adjust the amount of the flow from the fuel line into the fuel additive dispenser. 1. A system for monitoring fuel additives on board a vehicle comprising;a fuel line carrying fuel from a fuel source to an engine;a fuel additive sensor configured to measure concentration of additives in fuel at a point along the fuel line;a fuel additive dispenser connected in parallel to the fuel line;at least one flow control device for controlling an amount of flow from the fuel line into the fuel additive dispenser; anda controller configured to receive input from the fuel additive sensor and to control the flow control device to adjust the amount of the flow from the fuel line into the fuel additive dispenser.2. The system of claim 1 , wherein the fuel additive dispenser is positioned along a fuel additive bypass line connected at an upstream end to the flow control device and connected at a downstream end back to the fuel line.3. The system of claim 2 , wherein the fuel additive sensor is positioned upstream of or at the flow control device.4. The system of claim 2 , wherein the fuel additive sensor is positioned downstream of the downstream end of the fuel additive bypass line.5. The system of claim 1 , wherein the controller is configured to compare the concentration with a pre-set additive requirement specification claim 1 , and to control the flow control device to increase flow through to fuel additive dispenser when the concentration is ...

Gas turbine firing temperature optimization based on sulfur content of fuel supply

Gas turbine firing temperature optimization based on a measured sulfur content of a fuel supply of the gas turbine system is provided. In one embodiment, a system includes a diagnostic system configured to determine a maximum firing temperature for a combustor of a gas turbine system. The diagnostic system may determine the maximum firing temperature based on a predetermined sulfur content to maximum firing temperature correlation and an actual sulfur content of a fuel supplied to the combustor. The diagnostic system may also be configured to provide an indicator for a change in an actual firing temperature in the combustor of the gas turbine system. The diagnostic system may provide the indicator in response to the determined maximum firing temperature differing from the actual firing temperature of the combustor of the gas turbine system.

DIFFUSION COMBUSTOR FUEL NOZZLE FOR LIMITING NOx EMISSIONS

The present application and the resultant patent provide a diffusion combustor fuel nozzle for a gas turbine engine. The fuel nozzle may include one or more gas fuel passages for one or more flows of gas fuel, a swirler surrounding the one or more gas fuel passages and positioned about a downstream face of the fuel nozzle, a number of swirler gas fuel ports defined in the swirler, and a number of downstream face gas fuel ports defined in the downstream face of the fuel nozzle. The swirler may include a number of swirl vanes and a number of air chambers defined between adjacent swirl vanes. The present application and the resultant patent further provide a method of operating a diffusion combustor fuel nozzle of a gas turbine engine. 1. A diffusion combustor fuel nozzle for a gas turbine engine , the fuel nozzle comprising:one or more gas fuel passages for one or more flows of gas fuel;a swirler surrounding the one or more gas fuel passages and positioned about a downstream face of the fuel nozzle, the swirler comprising a plurality of swirl vanes and a plurality of air chambers each defined between adjacent swirl vanes;a plurality of swirler gas fuel ports defined in the swirler; anda plurality of downstream face gas fuel ports defined in the downstream face of the fuel nozzle.2. The diffusion combustor fuel nozzle of claim 1 , wherein each of the swirler gas fuel ports is defined in the swirler between adjacent swirl vanes.3. The diffusion combustor fuel nozzle of claim 1 , wherein each of the swirler gas fuel ports is defined in the swirler upstream of the downstream face of the fuel nozzle.4. The diffusion combustor fuel nozzle of claim 1 , wherein each of the swirler gas fuel ports extends from one of the gas fuel passages to one of the air chambers.5. The diffusion combustor fuel nozzle of claim 1 , wherein each of the swirler gas fuel ports extends towards the downstream face of the fuel nozzle.6. The diffusion combustor fuel nozzle of claim 1 , wherein each ...

SYSTEM AND METHOD FOR FUEL BLENDING AND CONTROL IN GAS TURBINES

A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured composition of the first fuel. 1. A system , comprising:a gas turbine engine comprising a combustor; and a first fuel supply configured to supply a first fuel;', 'a second fuel supply configured to supply a second fuel;', 'a first fuel circuit configured to blend the first fuel and the second fuel to form a first fuel mixture;', 'a second fuel circuit configured to blend the first fuel and the second fuel to form a second fuel mixture; and', 'a controller configured to regulate blending of the first fuel mixture and blending of the second fuel mixture based on a measured composition of the first fuel., 'a fuel blending system, comprising2. The system of claim 1 , wherein the first fuel comprises a process gas claim 1 , and the second fuel comprises a natural gas.3. The system of claim 2 , wherein the process gas comprises a coke oven gas claim 2 , a blast furnace gas claim 2 , a refinery flue gas claim 2 , a synthetic gas generated as a result of a refinery or chemical process claim 2 , or a combination thereof.4. The system of claim 1 , wherein the controller is configured to regulate blending of the first fuel mixture and the second fuel mixture based on the measured composition of the second fuel.5. The system of claim 1 , wherein the first fuel mixture has a first blending ratio of the first and second fuels ...

Integrated Power Generation Using Molten Carbonate Fuel Cells

In various aspects, systems and methods are provided for integrated operation of molten carbonate fuel cells with turbines for power generation. Instead of selecting the operating conditions of a fuel cell to improve or maximize the electrical efficiency of the fuel cell, an excess of reformable fuel can be passed into the anode of the fuel cell to increase the chemical energy output of the fuel cell. The increased chemical energy output can be used for additional power generation, such as by providing fuel for a hydrogen turbine. 1. A method for producing electricity , the method comprising:introducing a fuel stream comprising a reformable fuel into an anode of a molten carbonate fuel cell, an internal reforming element associated with the anode, or a combination thereof;{'sub': 2', '2, 'introducing a cathode inlet stream comprising COand Ointo a cathode of the molten carbonate fuel cell;'}generating electricity within the molten carbonate fuel cell, the molten carbonate fuel cell being operated at a fuel utilization of about 60% or less;{'sub': 2', '2, 'generating an anode exhaust comprising H, CO, and CO;'}{'sub': 2', '2, 'separating, from at least a portion of the anode exhaust, a first H-rich gas stream comprising at least about 80 vol % H; and'}{'sub': '2', 'combusting at least a portion of the first H-rich gas stream to produce electricity.'}2. The method of claim 1 , further comprising performing a water gas shift process on the anode exhaust claim 1 , the at least a portion of the anode exhaust claim 1 , or a combination thereof.3. The method of claim 1 , further comprising separating COfrom the anode exhaust claim 1 , the at least a portion of the anode exhaust claim 1 , or a combination thereof.4. The method of claim 1 , further comprising separating HO from the anode exhaust claim 1 , the at least a portion of the anode exhaust claim 1 , or a combination thereof.5. The method of claim 1 , wherein the separating step comprises:performing a water gas shift ...

Variable Heat/Power Ratio Cogeneration System

A variable heat/power ratio cogeneration system is provided that is capable of suppressing NOx emissions to a minimum while ensuring stability of combustion of a gas turbine combustor even when the ratio of gasification gas to normal fuel (e.g., natural gas or light fuel oil) to be used is changed or the composition of the gasification gas fuel is changed. The system includes a first steam system injecting extra steam upstream of the flame zone; a second steam system branched from the first system and injecting extra steam downstream of the flame zone; first and second steam flow rate control valves controlling steam injected by first and steam systems, respectively; and a controller that controls first and second control valves based on (1) flow rates of the gasification gas and normal fuel and (2) demanded steam. 1. A variable heat/power ratio cogeneration system comprising:a gas turbine that uses gasification gas obtained by gasifying a solid or liquid fuel and a normal fuel that is natural gas, oil gas, or light fuel oil, the normal fuel being used as an alternative or auxiliary fuel when the gas turbine is start-up and stopped or when the amount of the gasification gas to be supplied is small;a combustor that combusts the gasification gas and the normal fuel to generate combustion gas;a heat recovery steam generator that uses exhaust gas of the gas turbine to generate steam;a process system that supplies the generated steam to a steam consumption facility;a steam system that injects extra steam into the gas turbine;a first steam system that injects the extra steam on the upstream side of a flame zone with respect to the flow of the combustion gas in the combustor;a second steam system that is branched from the first steam system and injects the extra steam on the downstream side of the flame zone with respect to the flow of the combustion gas in the combustor;a first steam flow rate control valve that is arranged in the first steam system and capable of ...

TURBINE INCLUDING FLUE GAS RECIRCULATION COMBUSTOR

A flue gas recirculation combustor includes a combustor chamber configured such that fuel and combustion gas are injected therein to cause combustion and having a nozzle-side end and a combustor outlet, a nozzle can connected to the nozzle-side end of the combustor chamber, a plurality of nozzles disposed in the nozzle can and configured such that an injection direction thereof is directed to a side of the combustor chamber, and a sleeve disposed in a premixing space defined between the nozzle can and the nozzle-side end of the combustor chamber, the sleeve including a recirculation pathway to recirculate combustion air from the combustor chamber to the premixing space. 1. A flue gas recirculation combustor comprising:a combustor chamber configured to receive fuel and combustion gas to cause combustion, the combustor chamber including a nozzle-side end and a combustor outlet;a nozzle can connected to the nozzle-side end of the combustor chamber;a plurality of nozzles disposed in the nozzle can and arranged such that an injection direction thereof is directed to a side of the combustor chamber; anda sleeve disposed in a premixing space defined between the nozzle can and the nozzle-side end of the combustor chamber, the sleeve including a recirculation pathway to recirculate combustion air from the combustor chamber to the premixing space.2. The flue gas recirculation combustor of claim 1 , wherein the recirculation pathway includes at least one of a bypass path and an ejector nozzle.3. The flue gas recirculation combustor of claim 1 , wherein the plurality of nozzles is configured to premix and inject combustion air and fuel.4. The flue gas recirculation combustor of claim 1 , wherein the recirculation pathway is provided on an inner surface of the sleeve along a circumferential direction.5. The flue gas recirculation combustor of claim 2 , wherein the recirculation pathway includes both the bypass path and the ejector nozzle claim 2 , wherein the ejector nozzle is ...

Systems and methods for fuel cell auxiliary power in secondary fuel applications

A cryogenic fuel auxiliary power system for an engine may include a cryogenic fuel supply, a first valve in fluid communication with the cryogenic fuel supply and configured to control a fuel flow, a first heat exchanger, configured to receive the fuel flow, in fluid communication with the first valve and a combustion chamber of the engine, and a fuel cell in fluid communication between the first valve and the first heat exchanger.

SYSTEMS AND METHODS OF ESTIMATING A COMBUSTION EQUIVALENCE RATIO IN A GAS TURBINE WITH EXHAUST GAS RECIRCULATION

A system includes an exhaust gas recirculation (EGR) gas turbine system which includes a combustor configured to receive and combust a fuel with an oxidant and a turbine driven by combustion products from the combustor and a turbine driven by combustion products from the combustor. The EGR gas turbine system further includes an exhaust gas recirculation section fluidly coupled to the turbine and to the combustor, wherein the exhaust gas recirculation section is configured to intake an exhaust gas from the turbine and to recirculate at least a portion of the exhaust gas to the combustor as a diluent. The EGR gas turbine system additionally includes a control system, comprising one or more processors configured to receive a first signal representative of an exhaust flow composition of the exhaust gas and to receive a second signal representative of a diluent flow composition of the diluent. 1. A system , comprising:an exhaust gas recirculation (EGR) gas turbine system, comprising:a combustor configured to receive and combust a fuel with an oxidant;a turbine driven by combustion products from the combustor;an exhaust gas recirculation section fluidly coupled to the turbine and to the combustor, wherein the exhaust gas recirculation section is configured to intake an exhaust gas from the turbine and to recirculate at least a portion of the exhaust gas to the combustor as a diluent; and receive a first signal representative of an exhaust flow composition of the exhaust gas;', 'receive a second signal representative of a diluent flow composition of the diluent;', {'sub': 'COMB', 'derive a combustion equivalence ratio Φbased at least in part on the first and the second signal; and'}, {'sub': 'COMB', 'control the EGR gas turbine system based at least in part on the combustion equivalence ratio Φ.'}], 'a control system, comprising one or more processors configured to2. The system of claim 1 , wherein the one or more processors are configured to control the EGR gas turbine ...

System and method for purging fuel from turbomachine

A system includes a fuel premixer configured to distribute a fuel to a combustor and a purge system configured to purge the fuel from the fuel premixer. The purge system includes a discharge line configured to receive a flow of a purge mixture from the fuel premixer. The purge system includes an orifice coupled to the discharge line and an eductor having an interior, an opening, and an outlet. The orifice is configured to constrict the flow of the purge mixture. The interior is fluidly coupled to the orifice, to the opening, and to the outlet. The purge mixture is configured to flow through the interior from the orifice to the outlet, the flow of the purge mixture through the orifice is configured to draw coolant into interior of the eductor through the opening, and the coolant drawn through the opening is configured to mix with the purge mixture.

TURBINE ENGINE ASSEMBLY AND METHOD OF OPERATING

A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture formed at least partially from a primary fuel including methane. The assembly also includes a fuel reformer configured to produce a secondary fuel, wherein the fuel reformer is further configured to channel a flow of secondary fuel towards the rotating detonation combustor such that the fuel-air mixture further includes the secondary fuel. 1. A turbine engine assembly comprising:a rotating detonation combustor configured to combust a fuel-air mixture formed at least partially from a primary fuel comprising methane; anda fuel reformer configured to produce a secondary fuel, wherein said fuel reformer is further configured to channel a flow of the secondary fuel towards said rotating detonation combustor such that the fuel-air mixture further comprises the secondary fuel.2. The turbine engine assembly in accordance with further comprising a flow controller coupled between said rotating detonation combustor and said fuel reformer claim 1 , said flow controller configured to regulate the flow of the secondary fuel channeled towards said rotating detonation combustor based on an operating condition of the turbine engine assembly.3. The turbine engine assembly in accordance with claim 2 , wherein said flow controller is further configured to channel the flow of the secondary fuel towards said rotating detonation combustor at least one of during startup of said turbine engine assembly claim 2 , or as a rotational speed of said turbine engine assembly increases towards a steady state operating condition.4. The turbine engine assembly in accordance with claim 3 , wherein said flow controller is further configured to progressively reduce an amount of the secondary fuel channeled towards said rotating detonation combustor as the rotational speed of said turbine engine assembly increases towards the steady state operating condition.5. The turbine engine assembly in ...

PROCESS AND APPARATUS FOR GENERATING ELECTRIC ENERGY

The invention provides a process and apparatus to generate electric energy in a system comprising a power station and air treatment plant. The power station has a first gas expansion unit connected to a generator. The air treatment plant has an air compression unit, heat exchanger system and tank for liquid. In a first operating mode, feed air is compressed in the air compression unit and cooled in the heat exchanger system. A storage fluid containing less than 40 mol % of oxygen is produced and stored as low-temperature liquid in the tank for liquid. In a second operating mode, low-temperature liquid is taken from the tank for liquid and vaporized or pseudovaporized under superatmospheric pressure. The gaseous high-pressure storage fluid produced in this way is expanded in a gas expansion unit. The (pseudo)vaporization of the low-temperature liquid is carried out in the heat exchanger system of the air treatment plant. 23132. The method as claimed in claim 1 , characterized in that the auxiliary air is further compressed in at least two cold compressors ( claim 1 , ) claim 1 , which are connected in parallel.310410421. The method as claimed in claim 1 , characterized in that the power station has a gas turbine system with combustion chamber claim 1 , gas turbine expander and generator claim 1 , and at least part of the gaseous high-pressure storage fluid () is expanded in the gas turbine expander of a gas turbine system claim 1 , wherein the storage fluid () is fed to the gas turbine system downstream of the (pseudo-)vaporization ().4. The method as claimed in claim 1 , characterized in that the gas expansion unit has a hot-gas turbine system which has at least one heater and one hot-gas turbine.5. The method as claimed in claim 3 , characterized in that the gaseous high-pressure storage fluid is expanded in two steps claim 3 , wherein the first step is carried out as a work-performing expansion in the hot-gas turbine system and the second step is carried out in ...

Method for operating a supply assembly for supplying fuel gas and inert media to a gas turbine combustor, such supply assembly and a gas turbine comprising such supply assembly

A method for operating a supply assembly configured for supplying fuel gas and an inert purge media to a gas turbine combustor, the method including supplying fuel gas in a fuel gas circuit with an upper flow rate; reducing the fuel gas flow rate in the fuel gas circuit from the upper flow rate to a lower flow rate; stopping the supply of the fuel gas in the fuel gas circuit; and starting the supply of the inert purge media in the inert purge media circuit, wherein the starting is performed before the stopping to have a temporary parallel supply of fuel gas and of inert purge media to a fuel distribution system.

TWO STREAM LIQUID FUEL LEAN DIRECT INJECTION

A method for lean direct injection of a liquid fuel from a fuel injector into a combustion chamber of a gas turbine engine is disclosed. The method includes injecting all of the liquid fuel into the combustion chamber through a pilot liquid fuel circuit during light off and during acceleration towards idle. The method also includes injecting the liquid fuel in two streams including injecting a majority of the liquid fuel as an annular film through a main liquid fuel circuit and injecting a remainder of the liquid fuel through the pilot liquid fuel circuit when the gas turbine engine is at idle and for operating ranges of the gas turbine engine above idle. 1. A method for lean direct injection of a liquid fuel from a fuel injector into a combustion chamber of a gas turbine engine , the method comprising:injecting all of the liquid fuel into the combustion chamber during light off through a pilot liquid fuel circuit including injecting the liquid fuel through a pilot liquid tube and directing the liquid fuel out of a pilot tube tip into the combustion chamber;injecting all of the liquid fuel into the combustion chamber through the pilot liquid fuel circuit during acceleration of the gas turbine engine towards idle; andinjecting the liquid fuel in two streams when the gas turbine engine is at idle including injecting the liquid fuel into the combustion chamber through the pilot liquid fuel circuit and injecting from eighty to ninety percent of the liquid fuel as an annular film through a main liquid fuel circuit;wherein injecting the liquid fuel through the main liquid fuel circuit includes swirling the liquid fuel by directing the liquid fuel from a liquid gallery formed in a center body assembly through a plurality of swirl slots formed in the center body assembly and into an annular prefilm passage formed in the center body assembly adjacent the swirl slots, and directing the liquid fuel out of the prefilm passage as the annular film that expands outward from an ...

FUEL INJECTOR ASSEMBLIES

A method for assembling a fuel distribution system for a turbomachine fuel injector includes inserting a liquid fuel distributor into an interior cavity of a shroud to create a liquid fuel distribution circuit between the liquid fuel distributor and the shroud and inserting a gas fuel distributor into the interior cavity of the shroud and into an interior cavity of the liquid fuel distributor to create a gas fuel distribution circuit between the gas fuel distributor and the liquid fuel distributor. The method includes inserting a fuel transfer tube into an outer diameter of the shroud. The method includes brazing or shrink fitting at least one of the fuel transfer tube, the gas fuel distributor, or the liquid fuel distributor to the shroud. 1. A method for assembling a fuel distribution system for a turbomachine fuel injector , comprising:inserting a liquid fuel distributor into an interior cavity of a shroud to create a liquid fuel distribution circuit between the liquid fuel distributor and the shroud;inserting a gas fuel distributor into the interior cavity of the shroud and into an interior cavity of the liquid fuel distributor to create a gas fuel distribution circuit between the gas fuel distributor and the liquid fuel distributor;inserting a fuel transfer tube into an outer diameter of the shroud, the fuel transfer tube including a liquid fuel channel configured to be in fluid communication with the liquid fuel distribution circuit and a gas fuel channel configured to be in fluid communication with the gas fuel distribution circuit; andbrazing or shrink fitting at least one of the fuel transfer tube, the gas fuel distributor, or the liquid fuel distributor to the shroud.2. The method of claim 1 , further comprising press fitting at least one of the liquid fuel distributor or the gas fuel distributor to the shroud.3. The method of claim 2 , wherein press fitting includes heating the shroud before inserting the liquid fuel distributor so that the liquid fuel ...

GAS TURBINE SYSTEM

The gas turbine system (GT) includes a combustor () having a fuel injection nozzle assembly () for jetting hydrogen gas (H) and pure water (W), a reservoir () for pooling the pure water (W) to be supplied to the combustor (), a gas compressing device () for boosting the hydrogen gas (H) to be supplied to the combustor (), a fuel supply passage () for guiding the boosted hydrogen gas (H) towards the combustor (), and a pressurizing passage () communicating between the reservoir () and the fuel supply passage () for pressurizing the pure water (W) by means of the boosted hydrogen gas (H). 1. A gas turbine system which comprises:a combustor, having a fuel injection nozzle assembly to inject a gas fuel and an injection water;a reservoir to pool the injection water to be supplied to the combustor;a fuel boosting unit to increase the pressure of the gas fuel to be supplied to the combustor;a fuel supply passage to supply the boosted gas fuel into the combustor; anda pressurizing passage communicated with the reservoir and the fuel supply passage to increase the pressure of the injection water by the aid of the boosted gas fuel.2. The gas turbine system as claimed in claim 1 , in which the combustor is of a premixing type in which the gas fuel and the injection water are premixed.3. The gas turbine system as claimed in claim 2 , in which the gas fuel comprises a hydrogen gas.4. The gas turbine system as claimed in claim 1 , further comprising a pure water making device to manufacture the injection water in the form of a pure water.5. The gas turbine system as claimed in claim 1 , in which the fuel boosting unit comprises a gas compressing device.6. The gas turbine system as claimed in claim 1 , in which the fuel boosting unit comprises a liquid fuel compressing device to boost the pressure of a liquid fuel and an evaporator to generate the gas fuel from the boosted liquid fuel. This application is based on and claims Convention priority to Japanese patent application No. ...

SYSTEM AND METHOD FOR CONTROLLED FUEL BLENDING IN GAS TURBINES

A system includes a gas turbine engine having a combustor, and a fuel blending system. The fuel blending system further includes a first fuel supply configured to supply a first fuel, a second fuel supply configured to supply a second fuel, a first fuel circuit, a second fuel circuit, and a controller. The first fuel circuit may be configured to blend the first fuel and the second fuel to form a first to form a first fuel mixture. The second fuel circuit may be configured to blend the first fuel and the second fuel to form a second fuel mixture. The controller may be configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured operating parameter of the combustor. 1. A system , comprising:a gas turbine engine comprising a combustor; and a first fuel supply configured to supply a first fuel;', 'a second fuel supply configured to supply a second fuel;', 'a first fuel circuit configured to blend the first fuel and the second fuel to form a first fuel mixture;', 'a second fuel circuit configured to blend the first fuel and the second fuel to form a second fuel mixture; and', 'a controller configured to regulate blending of the first fuel mixture and blending of the second fuel mixture, wherein the controller is configured to regulate blending based on a measured operating parameter of the combustor., 'a fuel blending system, comprising2. The system of claim 1 , wherein the first fuel comprises a process gas and the second fuel comprises a natural gas claim 1 , wherein the process gas comprises a coke oven gas claim 1 , a blast furnace gas claim 1 , a refinery flue gas claim 1 , a synthetic gas generated as a result of a refinery or chemical process claim 1 , or a combination thereof.3. The system of claim 1 , wherein the controller is configured to regulate blending of the first fuel mixture and the second fuel mixture based on a measured composition of the first fuel and/or the second fuel.4. The system of claim 1 , wherein ...

Power plant having a gas turbine and a hydrogen-cooled generator

A power station having a gas turbine, a generator driven by the gas turbine for generation of electrical power, and a hydrogen cooling circuit for discharging lost heat from the generator, wherein the hydrogen cooling circuit has a feed line for feeding hydrogen from a hydrogen tank into the generator and a discharge line for discharging heated hydrogen from the generator, and wherein the discharge line is connected to a mixing device, such that the heated hydrogen from the discharge line can be mixed with a further fuel and is fed by means of a fuel feed line to the gas turbine.

System and Method for Estimation of Gas Fuel Lower Heating Value using Energy Balances and Parametric Error Modeling

Systems and methods for improved gas turbine engine performance are disclosed. The method can include receiving an error function for a wide range of fuels. The error function can provide lower heating value (LHV) corrections over the wide range of fuels. The method can include receiving gas turbine engine operation data for a first period of run time on the gas turbine from one or more sensors of the gas turbine engine. The engine operation data can include a performance data points. The method can include determining an optimum LHV based on the engine operation data for the first period of run time and the error function. The method can then include adjusting fuel consumption of the gas turbine engine based on the optimum LHV. 1. A method for operating a gas turbine engine , the method comprising:receiving a first error function for a plurality of fuels;receiving, at a fuel controller, first engine operation data for a first period of run time on the gas turbine from one or more sensors of the gas turbine engine, the first engine operation data having a plurality of performance data points each referenced to a discrete time;determining, at the fuel controller, a first lower heating value (LHV) based on the first engine operation data for the first period of run time and the error function; andoperating the gas turbine based on the first LHV.2. The method of wherein the operating comprises adjusting a fuel and air mixture supplied to the gas turbine engine based on the first LHV.3. The method of claim 2 , wherein the first engine operation data comprises data related to fuel consumption by the gas turbine engine.4. The method of further comprising claim 2 ,receiving, after a first delay time, second engine operation data for a second period of run time on the gas turbine from the one or more sensors of the gas turbine engine;determining, at the fuel controller, a second LHV based on the second fuel consumption data for the first period of run time and the error ...

COMBUSTION CHAMBER OF A GAS TURBINE, GAS TURBINE AND METHOD FOR OPERATING THE SAME

A combustion chamber assembly of a gas turbine, for combusting a fuel in the presence of combustion air, is configured as a dual-fuel combustion chamber assembly. In a gas fuel operating mode a mixture of a gaseous fuel and combustion air is supplied to the combustion chamber via a swirl body. In a liquid fuel operating mode liquid fuel is fed to the combustion chamber via a fuel lance and combustion air is fed to the combustion chamber via the swirl body. The fuel lance is surrounded by an adjoining lance cap to form a radial clearance therebetween such that the combustion chamber is feedable with combustion air via the radial clearance, bypassing the swirl body. 1. A combustion chamber assembly of a gas turbine , for combusting a fuel in the presence of combustion air , the combustion chamber assembly comprising:{'b': 1', '1', '2, 'a combustion chamber (), in which combustion of fuel occurs, the combustion chamber () being delimited by a wall ();'}{'b': 9', '1, 'a mixing chamber () arranged upstream, in a fuel feeding direction, of the combustion chamber ();'}{'b': 4', '9, 'a fuel lance () configured to feed liquid fuel into the mixing chamber ();'}{'b': 6', '6', '4', '6, 'a lance cap () adjoining, and surrounding at least in sections, the fuel lance () so as to define a radial clearance between the fuel lance () and the lance cap (); and'}{'b': 3', '9, 'a swirl body () configured to feed combustion air and gaseous fuel to the mixing chamber (),'}{'b': 1', '3', '1', '4', '1', '3, 'wherein the combustion chamber assembly is configured as a dual-fuel combustion chamber assembly, which, in a gas fuel operating mode, feeds a mixture of a gaseous fuel and combustion air to the combustion chamber () via the swirl body (), and which, in a liquid fuel operating mode, feeds liquid fuel to the combustion chamber () via the fuel lance () and combustion air to the combustion chamber () via the swirl body (), and'}{'b': 6', '1', '3', '6, 'wherein the radial clearance () is ...

EXPANDED GAS TURBINE PROCESS WITH NATURAL GAS REGASIFICATION

A power plant with a multi-stage intercooled compressor, a combustion chamber, a turbine which is arranged downstream of the combustion chamber, a compressor air line which connects the compressor to the combustion chamber, and a first heat exchanger which is connected into the compressor air line and into an exhaust gas line branching off from the turbine. A first compressor air expander is arranged in the compressor air line between the first heat exchanger and the combustion chamber, and the power plant includes a device for regasifying liquid natural gas, having a natural gas line, wherein a heat exchanger device is connected into the natural gas line between two compressor stages of the compressor. 114.-. (canceled)15. A power station plant comprising:a multistage compressor with intermediate cooling,a combustion chamber,a turbine located downstream of the combustion chamber,a compressor air conduit which connects the compressor to the combustion chamber and a first heat exchanger installed in the compressor air conduit and in an exhaust gas conduit branching off from the turbine,wherein the power station plant comprises a device for regasifying liquid natural gas having a natural gas conduit,wherein a heat transfer device is installed between two compressor stages of the compressor and in the natural gas conduit,wherein a first compressor air expander is arranged in the compressor air conduit between the first heat exchanger and the combustion chamber.16. The power station plant as claimed in claim 15 ,wherein the heat transfer device comprises a second heat exchanger which is installed between two compressor stages and in the natural gas conduit.17. The power station plant as claimed in claim 15 ,wherein the heat transfer device comprises a nitrogen circuit having a nitrogen conduit in which a third heat exchanger and a fourth heat exchanger are installed, where the third heat exchanger is installed in the natural gas conduit between two compressor stages and ...