Kraftmaschine

Eine Kraftmaschine, beispielsweise ein Hubkolbenmotor (1), wird mit einem fließfähigen, insbesondere gelförmigen Treibstoff (12) ohne Luftzufuhr betrieben.

Fuel reforming apparatus and electric power generating system having the same

Installation for supplying gas to a blast furnace or the like

... 1,009,978. Gas turbine plant. UNITED AIRCRAFT CORPORATION. Oct. 16, 1963 [Oct. 31, 1962], No. 40752/63. Heading F1G. [Also in Division F4] The invention relates to an installation for supplying gas under pressure to a blast furnace and comprising a gas turbine engine having a main compressor and a turbine which drives the compressor. In accordance with the invention a part of the air discharging from the main compressor to the air inlets of the blast furnace passes through an auxiliary compressor to an oxygen producing plant, the oxygen passing from the oxygen plant in part to a combustion chamber to be mixed with compressed fuel for driving the turbine, and in part into the air from the main compressor conducted to inlets of the blast furnace. The plant shown comprises a main air compressor 4 which is driven by a turbine 6, a portion of the air delivered by the compressor passing through line 10 and air preheater 14 into the inlets of the blast furnace 2. The remaining portion of air from ...

Process for producing one or more hydrocarbon products

A process for producing hydrocarbon products comprising: (a) producing charcoal from vegetal feedstock in the absence of oxygen; (b) producing hydrogen and carbon monoxide from the charcoal in the presence of steam; and (c) producing one or more hydrocarbon products from the mixture of step (b) using the Fischer-Tropsch process; wherein steam is raised as a reactant in step (b) and as a heat source in step (c) by electrically heating water using renewable energy; wherein a portion of the hydrocarbon products is burnt to produce heat and an oxygen-free environment for step (a); and wherein waste heat from step (a) is used to raise steam to maintain operating temperatures for steps (b) and (c) when the source of renewable energy is unavailable or unable to raise steam to at least maintain operating temperatures. The process is preferably carbon-neutral, fossil fuels are not used as feedstock or to produce the electricity for the process. Preferably a portion of the hydrocarbon products is ...

Improvements in or relating to fuel systems for internal combustion engines

... 869,274. Gas turbine plant. ROLLS-ROYCE Ltd. Oct. 24, 1957 [Nov. 8, 1956], No. 34216/58. Class 110 (3). A hydrogen fuel system for a gas turbine engine comprises a storage vessel for the hydrogen in liquefied form from which the fuel is drawn off in gaseous form, means for compressing and thereby heating the gaseous fuel prior to its delivery to the engine, means for controlling the flow of compressed and heated gaseous hydrogen to the engine and means for returning a proportion of the compressed and heated gaseous hydrogen into the liquid hydrogen in the storage vessel to cause evaporation of the liquid hydrogen. The gas turbine fuel system shown comprises a heat-insulated storage vessel 15 containing liquid hydrogen which has the suction pipe 16 of a multi-stage centrifugal compressor 17 connected to its upper surface. The compressor 17 discharges through a pipe 12 containing a control valve 18 to the combustion equipment 11 of a gas turbine engine. An auxiliary engine comprises a compressor ...

Combustion device and gas turbine

This combustion device (C) causes the combustion of fuel ammonia and combustion air within a combustion chamber (N), and is equipped with a combustor liner (3a) which forms the combustion chamber, a burner (3c) which is attached to one end of the combustor liner, a deflecting member (3g) which is provided downstream of the combustor liner in the flow direction of combustion gas and deflects the flow direction of the combustion gas, and at least one ammonia injection hole (3b) which is provided between the burner and the exit of the deflecting member and supplies the fuel ammonia to the interior of the combustion chamber.

SYSTEM FOR VAPORIZATION OF LIQUID FUELS FOR COMBUSTION AND METHOD OF USE

A gas stream with a reduced oxygen concentration relative to ambient air is used to vaporize a liquid fuel or liquified hydrocarbon gas, or is mixed with a vaporized gas, and the reduced oxygen vaporized fuel gas is fed to a combustion device such as a premixed or diffusion combustor. Preferably, the oxygen content of the gas stream is less than the limited oxygen index. By mixing the fuel with a gas stream that has an appropriately reduced oxygen content, auto-ignition prior to the flame front can be avoided. In some embodiements, the reduced oxygen stream is generated from an air separator or taken from the exhaust of the combustion device.

METHOD AND EQUIPMENT FOR COMBUSTION OF AMMONIA

A method for the combustion of ammonia, wherein a first combustion chamber (2) receives ammonia (4) and hydrogen (5) in controlled proportions, and an oxygen-containing gas. Combustion of the ammonia and hydrogen produces NH2 - ions among other combustion products (22). A second combustion chamber (3) receives the combustion products (22) from the first combustion chamber and receives further ammonia (4) and further hydrogen (5) in controlled proportions, wherein combustion produces nitrogen oxides among other combustion products (24). A third combustion chamber (14) receives the nitrogen oxides along with further ammonia and further hydrogen in further controlled proportions along with further oxygen-containing gas, such that the nitrogen oxides are combusted into nitrogen and water.

A PROCESS FOR UPGRADING PYROLYSIS OIL, TREATED PYROLYSIS OIL AND THE USE THEREOF

The present invention relates to a process for upgrading pyrolysis oil comprising heating pyrolysis oil in the absence of added catalyst at 100°C to 200°C temperature and 50 bar to 250 bar pressure, and heating the product of the first heating in the absence of added catalyst at 200°C to 400°C temperature and 50 bar to 250 bar pressure. The present invention also relates to the product obtained by the process according to the invention and to the use of treated pyrolysis oil. The invention further describes methods where the treated pyrolysis oil according to any process of the invention is fed to a power plant for producing electricity; is burned in a boiler for producing heating oil and/or is used as transportation fuel or as a blending component in transportation fuel.

Windanlage zur Speisung eines Hochofens mit Druckgas

PROCEDURE FOR BURNING HEAVY FUELS IN A GAS TURBINE AND A VERDAMPFUNGSBRENNER FOR IT.

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 ...

SYSTEMS AND METHODS TRAPPING CARBON DIOXIDE AND GENERATION OF ENERGY IN TYRBINY SYSTEMS WITH LOW EMISSION OF

SYSTEMS AND METHODS TRAPPING CARBON DIOXIDE AND GENERATION OF ENERGY IN TYRBINY SYSTEMS WITH LOW EMISSION OF

Gas turbine combustor and method of operating the same

Method and installation for producing mechanical or electrical energy, in particular for gas turbines

Improvements with the fuel feeding attachments for internal combustion engines

Method of and apparatus for improved methanol operation of combustion systems

METHOD USING BI-METALLIC ADDITIVES FOR INHIBITING VANADIUM CORROSION IN GAS TURBINES

L'invention a pour objet un procédé de combustion d'un combustible liquide contaminé au vanadium dans un système de combustion d'une turbine à gaz munie d'une turbine de détente des gaz, ladite combustion conduisant à la formation de pentoxyde de vanadium V2O5, le procédé étant destiné à inhiber la corrosion vanadique d'une pièce chaude de la turbine à gaz, le procédé étant caractérisé en ce qu'il comprend une étape d'introduction dans le système de combustion d'un premier oxyde qui est l'oxyde de magnésium et d'au moins un second oxyde choisi parmi Al2O3, Fe2O3, TiO2 et SiO2, le rapport m du nombre de moles de MgO au nombre de moles de V2O5 et le rapport a du nombre total de mole de second(s) oxyde(s) au nombre de moles de V2O5 satisfaisant aux deux conditions : (i) a + 3 < m < 15, et (ii) [1/(1 + K)] (m - 2) ≤ a ≤ [10/(10 + K)] (m - 2) K étant défini par la relation : K= MV * HK * e (-0,0056*T), où : - T désigne la température de flamme de la turbine à gaz, - MV et HK désignent respectivement: la masse volumique moyenne et la dureté Knoop moyenne des oxydes doubles formés par la réaction entre l'oxyde de magnésium et le(s) second(s) oxyde(s). The invention relates to a method of combustion of a vanadium-contaminated liquid fuel in a combustion system of a gas turbine provided with a gas expansion turbine, said combustion leading to the formation of vanadium pentoxide V2O5 , the method being intended to inhibit the vanadic corrosion of a hot part of the gas turbine, the method being characterized in that it comprises a step of introduction into the combustion system of a first oxide which is the magnesium oxide and at least one second oxide selected from Al2O3, Fe2O3, TiO2 and SiO2, the ratio m of the number of moles of MgO to the number of moles of V2O5 and the ratio a of the total number of moles of second (s) oxide (s) at the number of moles of V2O5 satisfying both conditions: (i) a + 3 <m <15, and (ii) [1 ...

Process for generating power in a gas turbine cycle

Process for generating power in a gas turbine cycle comprising an air compression stage, a fuel gas combustion stage and an expansion stage providing mechanical power in a rotating power generator, the improvement of which comprises recovering heat contained in exhaust gas from the expansion step by means of endothermic catalytic conversion of primary fuel comprising dimethylether and/or methanol with water to a gas comprising hydrogen and carbon monoxide and employing at least a part of the hydrogen and/or carbon monoxide comprising gas as fuel gas in the fuel gas combustion stage.

Liquid fuel nozzle apparatus with passive water injection purge

In a gas turbine having a compressor, a combustor and a turbine, a gaseous fuel supply coupled to provide gaseous fuel to the combustor, a liquid fuel supply coupled to provide liquid fuel to the combustor via nozzle assembly. The nozzle assembly includes a plurality of passageways for flowing a fluid into the combustor, one of the passageways being an atomizing air passageway conduit interconnecting the atomizing air passageway to one of the plurality of passageways to enable fluid flow therebetween, while not allowing the flow of fluid back into the atomizing air passageway. High pressure air from the atomizing air passageway is diverted into one of the plurality of passageways via the conduit to protect the nozzle from ingestion of hot combustor gases, thus eliminating a need for a dedicated air purge system for that one of the plurality of passageways.

Reformed-fuel-burning gas turbine system and method of operating the same

The present invention provides a reformed-fuel-burning gas turbine system that constantly generates good-quality reformed fuel even when heavy fuel has a different composition. The reformed-fuel-burning gas turbine system according to the present invention comprises a heavy oil heater; a water heater; a reformer vessel for mixing high-temperature, high-pressure water with high-temperature, high-pressure heavy oil to cause a hydrothermal reaction and producing reformed fuel from heavy oil; and a gas turbine which operates on the reformed fuel. The reformed-fuel-burning gas turbine system according to the present invention further comprises a detector for detecting the static dielectric constants or solubility of high-temperature, high-pressure heavy oil heated by the heavy oil heater and high-temperature, high-pressure water heated by the water heater; a first temperature regulating valve for adjusting the thermal dose of the heavy oil heater; a second temperature regulating valve for adjusting ...

MICRO GAS TURBINE SYSTEMS AND USES THEREOF

The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine. Lastly, the present disclosure describes features of a fuel capture system that allow the injection of wellhead gas, which typically is a mixture of gaseous and liquid fuels, into ...

КАМЕРА СГОРАНИЯ ГАЗОВОЙ ТУРБИНЫ И СПОСОБ ЕЁ ЭКСПЛУАТАЦИИ

Задачей создания камеры сгорания газовой турбины и способа ее эксплуатации является уменьшение заметности отработавшего газа газовой турбины при переключении топлива газовой турбины с нефтяного топлива на газовое топливо до минимума. При переключении сгорания во вспомогательной горелке со сжигания нефти на сжигание газа газовое топливо подается в основные горелки и начинается сжигание газа в основных горелках. Затем газовое топливо подается во вспомогательную горелку и начинается сжигание газа во вспомогательной горелке. 2 н. и 2 з.п. ф-лы, 6 ил.

ENERGIEGEWINNUNG DURCH METHANOLVERBRENNUNG

Method and equipment for combustion of ammonia

A first combustion chamber 2 receives ammonia and hydrogen in controlled proportions, and an oxygen-containing gas. Combustion of the ammonia and hydrogen produces NH2- ions among other combustion products 22. A second combustion chamber 3 receives the combustion products 22 from the first chamber 2 and receives further ammonia and hydrogen in controlled proportions, wherein combustion produces nitrogen oxides among other combustion products 24. A third combustion chamber 14 receives the combustion products 24 from the second chamber 3 along with ammonia and hydrogen in controlled proportions and oxygen-containing gas, such that the nitrogen oxides are combusted into nitrogen and water. Energy from the first 2, second 3 and third 14 chambers may be recovered by operating turbines (34, Fig. 2), 6 and 32 with exhaust gases from the first 2, second 3 and third 14 chambers respectively. The turbine 32 may be driven by steam from a heat exchanger 30 which recovers energy from combustion in the ...

Fuel reforming apparatus and electric power generating system

A fuel reforming apparatus comprising a first chamber having a reforming catalyst bed inside, and a second chamber for introducing a cooling medium into said first chamber, said second chamber being arranged adjacent to said first chamber. One embodiment describes a cylindrical fuel reforming apparatus covered with a thermal insulating layer 16 comprises a fuel flow passage 1 contoured by a cylindrical contour wall 2 in its central axial direction and a reforming catalyst bed 3 in the middle of the flow passage for reforming gas to be reformed flowing from the upstream of the fuel flow passage 1 into a proper reformed gas. A cooling jacket 10 is arranged in the upstream of the reforming catalyst bed 3 so as to surround the fuel flow passage 1 and to be supplied with steam 11 for cooling the cylindrical contour wall 2. ...

Electricity generation method and device using combustion of fossil fuels and having zero-carbon emission

Combustion device and gas turbine

This combustion device (C) is provided with a combustor (3) for causing the combustion of fuel ammonia and combustion air within a combustion chamber (N), and the combustor is equipped with a cooling ammonia supply unit (3g) for mixing the fuel ammonia into the combustion air and supplying the mixture to within the combustor.

Advanced combined cycle systems and methods based on methanol indirect combustion

A methanol indirect combustion combined-cycle power generation apparatus and method. A liquid methanol input stream is evaporated to provide a gaseous methanol stream which is converted to syngas that is combusted in a gas turbine assembly to drive a first electrical generator and produce an exhaust gas. Heat from the exhaust gas of the gas turbine assembly is used to produce first and second steam streams. The first steam stream drives a first steam turbine and provides the heat required for converting the gaseous methanol stream to the syngas combustion stream. The second steam stream drives a second steam turbine and provides the heat required for evaporating the liquid methanol input stream. A second electrical generator is driven using at least one of the first and second steam turbines.

FUEL SYSTEM AND METHOD OF REDUCING EMISSION

A fuel system includes a fuel deoxygenator for removing oxygen from a liquid fuel. A vaporizer is in fluid communication with the fuel deoxygenator. The vaporizer vaporizes at least a portion of the liquid fuel to produce vaporized fuel. At least a portion of the vaporized fuel pre-mixes with oxidizer to reduce formation of undesirable emissions.

FUEL INJECTOR WITH PURGED INSULATING AIR CAVITY

A fuel injector (30) includes a flow path for fuel air mixture to a combustor (50) extending longitudinally through the fuel injector. The fuel injector may also include a liquid fuel gallery (56) at least partially encircling the flow path. The gallery may include a plurality of fuel spokes (54a- 54e) configured to deliver liquid fuel from the gallery to the flow path. The fuel injector may also include an annular outer housing (47) circumferentially positioned about the gallery to form an insulating air cavity (60) at least partially around the gallery. The outer housing may include at least one purge hole (62a, 62b, 62c) to provide communication between the insulating air cavity and outside the outer housing of the injector.

SYSTEM AND METHOD OF ENERGY PRODUCTION USING PARTIAL OXIDATION OF

SYSTEM AND METHODS FOR ENTRAPPING CARBON DIOXIDE AND GENERATION OF ENERGY IN TURBINE SYSTEMS WITH LOW EMISSION OF

METHOD OF SUPPLYING FUEL TO A TURBO RAMJET ENGINE AND TURBO-RAMJET ENGINE FOR IMPLEMENTING THE METHOD

METHOD AND INSTALLATION FOR ENERGY PRODUCTION OR ELECTRIC DRIVE, ESPECIALLY GAS TURBINE

LIQUID COOLED TURBOCHARGER IMPELLER AND METHOD FOR COOLING AN IMPELLER

A compressor (110) comprising a casing (1) and an impeller (12) with a back side (16) is disclosed. The casing (1) comprises at least one inlet (21, 22, 23) which is connected to a cooling liquid supply and located such as to lead a cooling liquid to the back side (16). Moreover, a turbocharger comprising an inventive compressor (110) is described. Furthermore, a method for cooling an impeller (12) with a back side (16) is disclosed, wherein a cooling liquid is led to the back side (16).

METHOD OF RECYCLING WASTE PLASTIC MATERIAL

In a method for thermal processing of catalytically active waste plastics mixture, the mixture is subjected in a receiving tank to a cracking temperature to undergo a cracking reaction. The mixture is transferred to a mixer pump to produce a reaction mixture which is directed into an outgassing chamber of an intermediate tank to produce an outgassed fraction and a non-outgassed liquid fraction. The outgassed fraction to produce fuel is cooled down, and a first portion of the non-outgassed liquid fraction is returned and subjected again to the cracking temperature in the receiving tank. A second portion of the non-outgassed liquid fraction is conducted in a bypass to the outgassing chamber of the intermediate tank for outgassing while fresh mixture is added. Residual matter settling in the intermediate tank is periodically removed. 1. A method of recycling plastic comprising the steps of:comminuting waste plastic together with an active biocatalyst containing catalytically effective inorganic residue suitable for cracking of waste plastic to form a catalytically active waste plastic mixture and feeding it into a receiving tank;heating the catalytically active waste plastic mixture in the feeding receiving tank to a cracking temperature to undergo a cracking reaction;transferring the catalytically active waste plastic mixture to a mixer pump to produce a reaction mixture;directing the reaction mixture into an outgassing chamber of an intermediate tank to produce an outgassed fraction and a non-outgassed liquid fraction;cooling down the outgassed fraction to produce fuel;returning a first portion of the non-outgassed liquid fraction and subjecting it again to the cracking temperature in the receiving tank;conducting a second portion of the non-outgassed liquid fraction in a bypass to the outgassing chamber of the intermediate tank for outgassing while fresh waste plastic mixture is added; andperiodically removing from the intermediate tank settled residual matter.2. ...

Rich catalytic clean burn for liquid fuel with fuel stabilization unit

A fuel stabilization system (26) comprises a deoxygenator (20) that removes dissolved oxygen from a liquid fuel to allow vaporization of the liquid fuel without the undesirable production of insoluble materials and byproducts. The vaporized fuel is then mixed with oxidizers and reformed in a catalytic reactor (24). The resulting vaporized fuel provides for moderately low temperature sustained combustion with reduced emission of undesirable byproducts.

GAS TURBINE AND METHOD FOR OPERATING SAID GAS TURBINE

MULTI-FUEL ENGINE FOR AN AIRCRAFT

A method is provided for operating an aircraft system (20). During this method, an engine is operated using first fuel provided by a first fuel source (30A). A fuel supply (22) for the engine is switched between the first fuel source (30A) and a second fuel source (30B), where the switching of the fuel supply (22) includes shutting down the engine during aircraft flight. The engine is operated using second fuel provided by the second fuel source (30B).

СПОСОБЫ ПОЛУЧЕНИЯ ВЫСОКОКАЧЕСТВЕННЫХ РЕАКТИВНЫХ ТОПЛИВ НА ОСНОВЕ КЕРОСИНА

SYSTEM UND VERFAHREN ZUR INTEGRIERTEN ÖLBRENNUNG UND KOMBINIERTE ZYKLUSKRAFTWERKE

Process and equipment of fossil fuel power generation with zero carbon emission

Process for producing one or more hydrocarbon products

Fuel reforming apparatus and electric power generating system having the same

Fuel System and Method of Reducing Emission

System for vaporization of liquid fuels for combustion and method of use

SYSTEM FOR VAPORIZATION OF LIQUID FUELS FOR COMBUSTION AND METHOD OF USE

A gas stream with a reduced oxygen concentration relative to ambient air is used to vaporize a liquid fuel or liquified hydrocarbon gas, or is mixed with a vaporized gas, and the reduced oxygen vaporized fuel gas is fed to a combustion device such as a premixed or diffusion combustor. Preferably, the oxygen content of the gas stream is less than the limited oxygen index. By mixing the fuel with a gas stream that has an appropriately reduced oxygen content, auto-ignition prior to the flame front can be avoided. In some embodiements, the reduced oxygen stream is generated from an air separator or taken from the exhaust of the combustion device.

Fuel system and method of reducing emission

METHOD FOR RECOVERING ENERGY GAS FROM A BLAST FURNACE, AND BLAST FURNACE INSTALLATION FOR CARRYING OUT THE METHOD.

POLLUTION?FREE GAS TURBINE SYSTEM

BIO-FUEL COMPOSITION AND METHOD FOR MANUFACTURE OF BIO-FUEL COMPOSITION

The present invention provides a liquid bio-fuel mixture comprising: a liquid condensate product of biomass fast pyrolysis; a bio-diesel component; and an alcohol component. The liquid bio-fuel mixture is macroscopically single phase. The alcohol component is selected from methanol, a C3 to C10 alcohol, and a mixture of two or more different C1 to C10 alcohols.

Gas turbine fuel system comprising fuel oil distribution control system, fuel oil purge system, purging air supply system and fuel nozzle wash system

A plurality of fuel nozzles X1and X2in combustor X are supplied with fuel gas from a fuel gas system and fuel oil from a fuel oil system, respectively. Gas turbine operation is performed with fuel being changed over to either gas or oil. Fuel oil distribution control system A controls oil flowing into a plurality of fuel pipings. When oil is changed over to gas, fuel oil purge system B is supplied with air of an appropriate temperature and pressure from purging air supply system C. This air flows into fuel oil pipings and nozzles X2for purging residual oil therein. Fuel nozzle wash system D is supplied with water by-passing from a wash water tank for compressor washing. This water flows through nozzles X2for washing thereof.

Gas turbine fuel system comprising fuel oil distribution control system, fuel oil purge system, purging air supply system and fuel nozzle wash system

A plurality of fuel nozzles X1 and X2 in combustor X are supplied with fuel gas from a fuel gas system and fuel oil from a fuel oil system, respectively. Gas turbine operation is performed with fuel being changed over to either gas or oil. Fuel oil distribution control system A controls oil flowing into a plurality of fuel pipings. When oil is changed over to gas, fuel oil purge system B is supplied with air of an appropriate temperature and pressure from purging air supply system C. This air flows into fuel oil pipings and nozzles X2 for purging residual oil therein. Fuel nozzle wash system D is supplied with water by-passing from a wash water tank for compressor washing. This water flows through nozzles X2 for washing thereof ...

Micro gas turbine systems and uses thereof

The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine. Lastly, the present disclosure describes features of a fuel capture system that allow the injection of wellhead gas, which typically is a mixture of gaseous and liquid fuels, into ...

Polished turbine fuel

Turbine fuel provided for large-scale land based turbines used by utilities for producing electricity and desalinated water, and for large mobile engines and turbines in marine and remote applications where only liquid fuels are available. Use results in less corrosion, ash formation and emissions (NOx, SOx, CO2 and noxious metals) than firing contaminated heavy crude, refinery residual oils or high sulfur fuel oils. Manufacture is by decontaminating crude oils, non-conventional crudes, and other highly contaminated feeds. Each fuel is produced as a single product of unit operations, not ex-plant blend of various refinery products, yet using an apparatus configuration less complex than conventional crude oil refining. These fuels can be fired by advanced high efficiency turbines of combined cycle power plants having hot flow paths and heat recovery steam generation systems susceptible to corrosion, which systems cannot otherwise risk contaminated heavy crudes or refinery residual oils feeds ...

INTEGRATED PRODUCTION OF HYDROGEN, PETROCHEMICALS, AND POWER

A processing facility is provided. The processing facility includes an asphaltenes and metals (AM) removal system configured to process a feed stream to produce a power generation stream, a hydroprocessing feed stream, and an asphaltenes stream. A power generation system is fed by the power generation feed stream. A hydroprocessing system is configured to process the hydroprocessing feed stream to form a gas stream and a liquid stream. A hydrogen production system is configured to produce hydrogen, carbon monoxide and carbon dioxide from the gas feed stream. A carbon dioxide conversion system is configured to produce synthetic hydrocarbons from the carbon dioxide, and a cracking system is configured to process the liquid feed stream.

Reformed-fuel-burning gas turbine system and method of operating the same

A reformed-fuel-burning gas turbine system is presented that constantly generates good-quality reformed fuel even when heavy fuel has a different composition. The reformed-fuel-burning gas turbine system comprises a heavy oil heater; a water heater; a reformer vessel for mixing high-temperature, high-pressure water with high-temperature, high-pressure heavy oil to cause a hydrothermal reaction and producing reformed fuel from heavy oil; and a gas turbine which operates on the the reformed fuel. The gas turbine system further comprises a detector for detecting the static dielectric constants or solubility of high-temperature, high-pressure heavy oil heated by the heavy oil heater and high-temperature, high-pressure water heated by the water heater; a first temperature regulating valve for adjusting the thermal dose of the heavy oil heater; a second temperature regulating valve for adjusting the thermal dose of the water heater; and a control device for adjusting the first temperature regulating ...

СПОСОБ ВЫРАБОТКИ ЭЛЕКТРОЭНЕРГИИ В ЦИКЛЕ, СОДЕРЖАЩЕМ ГАЗОВУЮ ТУРБИНУ

FIELD: power engineering. SUBSTANCE: according to proposed method power is generated by endothermic catalytic vapour reforming of gaseous hydrocarbon material, tapping gaseous reforming product, combustion at least part of reforming product with compressed air with subsequent expansion of combustion gas product whose stage is coupled with power generation stage. Prior to delivering gaseous hydrocarbon material for endothermic catalytic reforming, hydrocarbon material is subjected to sequential indirect heat exchange with exhaust gas of endothermic catalytic vapour reforming process and exhaust gas of expansion stage. Dimethyl ether is used as hydrocarbon material. Expansion state exhaust gas is supplied for endothermic catalytic vapour reforming to provide indirect heat exchange with gaseous hydrocarbon material. EFFECT: increased efficiency of cycle. 2 cl, 1 dwg УС '‘ с ПЧ с» РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (19) (13) ВИ `” 2 175 724 6 МК’ [ 02 С 3/20 С2 (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 96116682/06, 22.08.1996 (24) Дата начала действия патента: 22.08.1996 (30) Приоритет: 23.08.1995 ОК 0946/95 (43) Дата публикации заявки: 20.11.1998 (46) Дата публикации: 10.11.2001 (71) Заявитель: ХАЛЬДОР ТОПСЕЭ А/С (ОК) (72) Изобретатель: ТОПСЕЭ Хальдор Фредерик Аксель (ОК) (73) Патентообладатель: ХАЛЬДОР ТОПСЕЭ А/С (ОК) (74) Патентный поверенный: (56) Ссылки: СВ 22321721 А, 19.12.1990. СВ 1581334 Квашнин Валерий Павлович А, 10.12.1980. $Ч 535422 А, 29.08.197Г. $9 64512 А, 30.04.1945. ОЕ 2241201 А, 07.03.1974. Ч$ 4202169 А, 13.05.1980. (98) Адрес для переписки: 103064, Москва, ул. Казакова 16, НИИР-Канцелярия, "Патентные поверенные Квашнин, Сапельников и Партнеры", Квашнину В.П. (54) СПОСОБ ВЫРАБОТКИ ЭЛЕКТРОЭНЕРГИИ В ЦИКЛЕ, СОДЕРЖАЩЕМ ГАЗОВУЮ ТУРБИНУ (57) Способ выработки электроэнергии в цикле, содержащем газовую турбину, осуществляется путем эндотермического каталитического парового риформинга газового углеводородного ...

Очищенное турбинное топливо

FIELD: production of fuel.SUBSTANCE: invention relates to decontaminated, ultrapure liquid fuel for turbines operating on gas combustion products, and to methods and device for production of such fuel from crude oil, oil refining residual oil and other types of contaminated liquid material. Fuel having limit content of sulfur is formed by a combination of three streams of liquid hydrocarbons, wherein the rate of each flow coming into the combination is determined from the corresponding sulfur content and the corresponding contribution to the total final sulfur content in the combination, taking into account the flow rate of each of the other two streams and the corresponding sulfur content, and such flows are formed by fractionation of crude oil, either in the presence of added steam, or without it, into three liquid fractions F1, F2 and F3, wherein the output phase, in the form of mass % of crude oil, each fraction, is determined from the content thereof sulfur so that content of sulfur in fraction F1 is less than content of sulfur in fraction F2, which is lower content of sulfur than in fraction F3, then fraction F2 is treated, and two portions of fraction F3, one of which is a portion obtained as a result of solvent separation, treated such that each treated stream has a sulfur content which is less than the sulfur limit in the fuel and maximizes the output fraction of the fraction F1 with respect to the fractions F2 and F3, while increasing portion of medium in the fraction F1, which otherwise could be within range of lighter kerosene substances, to minimize the amount of light distillates in fraction F2, and it remains untreated, and when it is combined with treated fraction F2 and treated portions of fraction F3, then final limit content combination sulfur is not exceeded.EFFECT: invention reduces corrosion action and ash deposition caused by oil-soluble metal traces in fuel.23 cl, 1 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 698 815 C1 (51) МПК B01J 19/00 ( ...

ТОПЛИВНАЯ ФОРСУНКА С ПРОДУВАЕМОЙ ИЗОЛИРУЮЩЕЙ ВОЗДУШНОЙ ПОЛОСТЬЮ

1. Топливная форсунка (30) для двухтопливного газотурбинного двигателя (100), содержащая:поточный проход (42) для топливовоздушной смеси, направляемой в камеру (50) сгорания, который продолжается через топливную форсунку в продольном направлении,канал (56) для жидкого топлива, который охватывает, по меньшей мере, часть поточного прохода, и содержит множество топливных патрубков (54а-54е), предназначенных для доставки жидкого топлива из указанного канала к поточному проходу, икольцевой наружный кожух (47), который окружает указанный канал, образуя изолирующую воздушную полость (60), по меньшей мере, вокруг части указанного канала, и содержит, по меньшей мере, одно отверстие (62а, 62b, 62с) для продувки, обеспечивающее связь между изолирующей воздушной полостью и окружающим наружный кожух форсунки пространством.2. Топливная форсунка по п. 1, отличающаяся тем, что содержит множество отверстий для продувки.3. Топливная форсунка по п. 2, отличающаяся тем, что, по меньшей мере, одно из множества отверстий для продувки расположено вблизи одного из множества топливных патрубков.4. Топливная форсунка по п. 2, отличающаяся тем, что диаметр каждого из множества отверстий для продувки меньше или равен примерно 0,075 дюйма (1,9 мм).5. Топливная форсунка по п. 2, отличающаяся тем, что диаметр, по меньшей мере, одного из множества отверстий для продувки составляет примерно 0,03 (0,76 мм) дюйма.6. Топливная форсунка по п. 2, отличающаяся тем, что, по меньшей мере, одно из множества отверстий для продувки расположено в радиальном направлении наружу от топливного канала.7. Топливная форсунка по п. 2, отличающаяся тем, что множество отверстий для продувки является единственным средством связи между изолирующей воздушной полостью и о РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F02C 7/22 (13) 2014 147 442 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2014147442, 26.04.2013 (71) Заявитель(и): СОУЛАР ТЁРБИНЗ ИНКОРПОРЕЙТЕД (US) ...

СИСТЕМА УПРАВЛЕНИЯ РАБОТОЙ ГАЗОВОЙ ТУРБИНЫ

... 1. Система управления работой газовой турбины, которая приводится в действие с использованием аммиака в качестве топлива, при этом в рабочей области ухудшенной возгораемости, в которой возгораемость аммиака ухудшается по сравнению со временем нормальной работы газовой турбины, доля топлива с более высокой возгораемостью, чем у аммиака, в топливе, которое подается в газовую турбину, увеличивается по сравнению со временем нормальной работы. ! 2. Система по п.1, в которой топливо с более высокой возгораемостью, чем у аммиака, является ископаемым топливом. ! 3. Система по п.1, в которой рабочая область ухудшенной возгораемости является рабочей областью, в которой испарение аммиака является неполным при подаче аммиака в газовую турбину в качестве основного топлива. ! 4. Система по п.1, в которой рабочая область ухудшенной возгораемости является рабочей областью, в которой окружающая температура вокруг части, где сжигается топливо, ниже по сравнению со временем нормальной работы. ! 5. Система ...

Verfahren zur Frequenzstützung beim Betrieb einer Kraftwerksanlage

Fuel reforming apparatus and electric power generating system having the same

A method and a device for the liquefaction of natural gas

Systems and methods for carbon dioxide capture and power generation in low emission turbine systems

Systems, methods, and apparatus are provided for generating power in low emission turbine systems and separating the exhaust into rich CO ...

ZERO EMISSION LIQUID FUEL PRODUCTION BY OXYGEN INJECTION

An enhanced oil recovery method is provided. This method includes; introducing a first essentially pure oxygen stream into a subterranean hydrocarbon-bearing formation traversed by at least one injection well and at least one production well, and initiating and sustaining in-situ combustion in the vicinity of the injection well. This method also includes introducing a second essentially pure oxygen stream and a hydrocarbon-containing fuel gas stream into the combustion device of a power generation system, wherein the combustion device produces an exhaust gas stream comprising water and carbon dioxide. This method also includes separating the exhaust gas stream into a stream of essentially pure water, and a stream of essentially pure carbon dioxide, and introducing at least a portion of the essentially pure carbon dioxide stream into the subterranean hydrocarbon-bearing formation prior to initiating the in-situ combustion. The method may be used on a structure containing a carbonaceous substance ...

RICH CATALYTIC CLEAN BURN FOR LIQUID FUEL WITH FUEL STABILIZATION UNIT

... fuel stabilization system removes dissolved oxygen from a liquid fuel to allow vaporization of the liquid fuel without the undesirable production of insoluble materials and byproducts. The vaporized fuel is then mixed with oxidizers and reformed in the catalytic reactor. The resulting vaporized fuel provides for moderately low temperature sustained combustion with reduced emission of undesirable byproducts.

Power device and igniting method thereof

POLLUTION?FREE GAS TURBINE SYSTEM

PROCEDE ET INSTALLATION DE PRODUCTION D'ENERGIE MOTRICE OU ELECTRIQUE, NOTAMMENT A TURBINE A GAZ

L'INVENTION CONSISTE ESSENTIELLEMENT A UTILISER LA CHALEUR DES FUMEES D'ECHAPPEMENT D'UNE TURBINE A GAZ 1, DANS UNE CHAUDIERE DE RECUPERATION 8, D'UNE PART POUR SOUMETTRE A UNE OPERATION DE REFORMAGE CATALYTIQUE A LA VAPEUR LE COMBUSTIBLE, EN PARTICULIER DU METHANOL, ET D'AUTRE PART POUR ENGENDRER DE LA VAPEUR D'EAU, LE MELANGE COMBUSTIBLE OBTENU AINSI QUE LA VAPEUR D'EAU ETANT INJECTES DANS LA CHAMBRE DE COMBUSTION 4 DE LA TURBINE. LA VAPEUR D'EAU ISSUE DE LA CHAUDIERE DE RECUPERATION PEUT AVANTAGEUSEMENT ETRE DETENDUE DANS UNE TURBINE A CONTREPRESSION 12 AVANT INJECTION DANS LA CHAMBRE. CES DISPOSITIONS PERMETTENT D'AUGMENTER CONSIDERABLEMENT LE RENDEMENT DE LA TURBINE A GAZ. D'AUTRES COMBUSTIBLES QUE LE METHANOL POURRONT ETRE UTILISES.

PROVIDING OXIDATION TO A GAS TURBINE ENGINE

A gas turbine engine includes a compressor for compressing air from an environment; a combustor for receiving the compressed air from the compressor, mixing the compressed air with fuel, and combusting the fuel; a turbine coupled with the compressor for receiving exhaust gas from the combustion and powering the compressor; and an injector coupled with a source of oxidizer for injecting the oxidizer into the combustor. A method for operating a gas turbine engine includes compressing air from an environment; receiving the compressed air at a combustor; mixing the compressed air with fuel; injecting oxidizer into the combustor in addition to the air from the environment; combusting the fuel with the compressed air and the oxidizer; receiving exhaust gas from the combusted fuel; and powering the compression of the air from the environment using the exhaust gas.

METHOD FOR SWITCHING OVER A GAS TURBINE BURNER OPERATION FROM LIQUID TO GAS FUEL AND VICE-VERSA

The method for switching over a gas turbine burner operation from liquid fuel (21) to gas fuel (22, 23) and vice-versa, with the burner (1) comprising nozzles (6) for feeding a premixed gas fuel, nozzles (8) for injecting a pilot gas fuel (23) and nozzles (9) for injecting a liquid fuel (21). According to the method, while the liquid fuel (21) and the premix gas fuel (22) are regulated to switch over from liquid fuel to gas fuel operation or vice-versa, the pilot gas fuel (23) is controlled at a substantially constant flow rate.

Liquid fuel nozzle apparatus with passive protective purge

In a gas turbine having a compressor, a combustor and a turbine, a gaseous fuel supply coupled to provide gaseous fuel to the combustor, a liquid fuel supply coupled to provide liquid fuel to the combustor via nozzle assembly. The nozzle assembly includes a plurality of passageways for flowing a fluid into the combustor, one of the passageways being a fuel passageway conduit interconnect the fuel passageway to one of the plurality of passageways to enable fluid flow therebetween. High pressure air from one of the plurality of passageways is diverted into the fuel passageway via the conduit to protect nozzle from ingestion of hot combustor gases.

Gas turbine fuel system comprising fuel oil distribution control system, fuel oil purge system, purging air supply system and fuel nozzle wash system

A plurality of fuel nozzles X1 and X2 in combustor X are supplied with fuel gas from a fuel gas system and fuel oil from a fuel oil system, respectively. Gas turbine operation is performed with fuel being changed over to either gas or oil. Fuel oil distribution control system A controls oil flowing into a plurality of fuel pipings. When oil is changed over to gas, fuel oil purge system B is supplied with air of an appropriate temperature and pressure from purging air supply system C. This air flows into fuel oil pipings and nozzles X2 for purging residual oil therein. Fuel nozzle wash system D is supplied with water by-passing from a wash water tank for compressor washing. This water flows through nozzles X2 for washing thereof.

ENGINE

A combuster (2) of a gas turbine engine (1) is fed with liquid ammonia and that liquid ammonia is burned to drive a turbine (3). Inside the exhaust passage of the gas turbine engine (1), an NOX selective reduction catalyst (9) is arranged. Inside the intake air which flows into the compressor (4), liquid ammonia is fed. This liquid ammonia is used to cool the intake air. The NOX which is contained in the exhaust gas is reduced by the unburned ammonia which is exhausted into the exhaust passage by the NOX selective reduction catalyst (9).

ENGINE USING HEATED AND TURBO-EXPANDED AMMONIA FUEL

An energy extraction system according to an exemplary embodiment of this disclosure, among other possible things includes an ammonia fuel storage tank assembly that is configured to store a liquid ammonia fuel, a thermal transfer assembly that is configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel, a turbo-expander that is configured to expand the vaporized ammonia based fuel to extract work, and an energy conversion device that is configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output.

REGENERATIVE COOLING AND ADJUSTABLE THROAT FOR ROTATING DETONATION ENGINE

A method for operating a rotating detonation engine, having a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned within the radially outer wall to define an annular detonation chamber having an inlet and an outlet, wherein the method includes flowing liquid phase fuel along at least one wall of the radially inner wall and the radially outer wall in a direction from the outlet toward the inlet to cool the at least one wall and heat the liquid fuel to provide a heated liquid fuel; flowing the heated liquid fuel to a mixer at the inlet to reduce pressure of the heated liquid fuel, flash vaporize the heated liquid fuel and mix flash vaporized fuel with oxidant to produce a vaporized fuel-oxidant mixture; and detonating the mixture in the annular detonation chamber.

Method to quickly increase the power of a power station

Power generation plant operating method The operating method allows a spontaneous increase in the power output of the power generation plant by supplying an additional medium (19) to the power generation process. The additional medium is stored in a container (20) under pressure and is provided by a base material (17), e.g. water, mixed with a fuel (18), e.g. oil or alcohol, for providing an emulsion.

СИСТЕМА УПРАВЛЕНИЯ РАБОТОЙ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ И ТЕПЛОВАЯ ЭЛЕКТРОСТАНЦИЯ, СОДЕРЖАЩАЯ ТАКУЮ СИСТЕМУ

FIELD: engines and pumps. SUBSTANCE: ammonia and fuel with ignitability higher than that of ammonia can be supplied as fuel to gas turbine engine. In working zone of worse ignitability, in which ammonia ignitability deteriorates in comparison to the time of normal operation of gas turbine engine, fuel fraction with ignitability higher than that of ammonia in fuel that is supplied to gas turbine engine is increased in comparison to the time of normal operation. EFFECT: even at use of poor inflammable ammonia as main fuel there can be provided stable start up, operation and shutdown of gas turbine at reduced carbon dioxide emissions. 16 cl, 6 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 471 082 (13) C2 (51) МПК F02C F23R F02C F23R 9/40 3/36 7/26 3/34 (2006.01) (2006.01) (2006.01) (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2011105003/06, 10.07.2009 (24) Дата начала отсчета срока действия патента: 10.07.2009 (73) Патентообладатель(и): ТОЙОТА ДЗИДОСЯ КАБУСИКИ КАЙСЯ (JP) R U Приоритет(ы): (30) Конвенционный приоритет: 11.07.2008 JP 2008-181751 (72) Автор(ы): НАКАМУРА Норихико (JP) (43) Дата публикации заявки: 20.08.2012 Бюл. № 23 2 4 7 1 0 8 2 (45) Опубликовано: 27.12.2012 Бюл. № 36 (56) Список документов, цитированных в отчете о поиске: RU 2221198 C2, 10.01.2004. JP 2075821 A, 15.03.1990. US 2007033919 A1, 15.02.2007. RU 1492862 С, 10.10.1995. ЕР 1614967 A1, 11.01.2006. US 2007289311 A1, 20.12.2007. 2 4 7 1 0 8 2 R U (86) Заявка PCT: JP 2009/062934 (10.07.2009) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 11.02.2011 (87) Публикация заявки РСТ: WO 2010/005120 (14.01.2010) Адрес для переписки: 129090, Москва, ул.Б.Спасская, 25, стр.3, ООО "Юридическая фирма Городисский и Партнеры", пат.пов. А.В.Мицу, рег.№ 364 (54) СИСТЕМА УПРАВЛЕНИЯ РАБОТОЙ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ И ТЕПЛОВАЯ ЭЛЕКТРОСТАНЦИЯ, СОДЕРЖАЩАЯ ТАКУЮ СИСТЕМУ (57) Реферат: Система управления работой газотурбинного ...

ТОПЛИВНАЯ ФОРСУНКА С ПРОДУВАЕМОЙ ИЗОЛИРУЮЩЕЙ ВОЗДУШНОЙ ПОЛОСТЬЮ

FIELD: power industry. SUBSTANCE: fuel nozzle comprises a passage for the in-line fuel mixture directed into the combustion chamber, which extends through the fuel injector in the longitudinal direction. Fuel nozzle is, moreover, may comprise a channel for liquid fuel which covers at least part of stream passage. The channel may comprise a plurality of fuel nozzles formed for delivering liquid fuel from the fuel passage to the inline passage. The fuel injector may also include an annular outer casing which surrounds the said channel, forming an insulating air cavity, at least around a portion of mentioned channel. The outer shell may comprise at least one opening for purging, providing communication between the insulating air space and an annular shroud surrounding space. It is also provided with a method of bi-fuel gas turbine engine operation. EFFECT: invention allows to maintain the temperature of the liquid fuel channel below the temperature of the fuel injector fuel coking. 10 cl, 5 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 623 319 C2 (51) МПК F02C 7/22 (2006.01) F02C 3/24 (2006.01) F02C 9/40 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ 2014147442, 26.04.2013 (24) Дата начала отсчета срока действия патента: 26.04.2013 (72) Автор(ы): ТВАРДОХЛЕБ Кристофер Здзислав (US), ДАКЕРС Джонатан Геррард (US) 23.06.2017 Приоритет(ы): (30) Конвенционный приоритет: (56) Список документов, цитированных в отчете о поиске: US 2010154424 A1, 24.06.2010. US 26.04.2012 US 61/639,013; 22.05.2012 US 13/477,819 R U (73) Патентообладатель(и): СОУЛАР ТЁРБИНЗ ИНКОРПОРЕЙТЕД (US) Дата регистрации: 5404711 A, 11.04.1995. RU 98538 U1, 20.10.2010. (45) Опубликовано: 23.06.2017 Бюл. № 18 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 26.11.2014 (86) Заявка PCT: US 2013/038500 (26.04.2013) 2 6 2 3 3 1 9 (43) Дата публикации заявки: 20.06.2016 Бюл. № 17 2 6 2 3 3 1 9 R U WO 2013/163604 ( ...

Gas turbine for aircraft engine has fuel supply system which exhibits wave-channel in which turbine shaft is swivel mounted and part of fuel supply takes place through shaft alley, which exhibits fuel outlets at its outer circumference

The gas turbine (1) has a compressor (2) with a compressor wheel (3) and a turbine (4) with a turbine shaft (6). The combustion chamber (7) partly surrounds the turbine shaft. The turbine has a fuel supply system (8) which exhibits a shaft alley (9) in which the turbine shaft is swivel mounted. The fuel supply takes place partly through the shaft alley, which has fuel outlets (10) at its outer circumference.

Vorrichtung zum Betrieb von Brennstoffzellen und/oder Verbrennungsmotoren

Vorrichtung zum Betrieb von Brennstoffzellen und/oder Verbrennungsmotoren, dadurch gekennzeichnet, dass als Wasserstofflieferant oder als Treibstoff Hydrazin genutzt wird, wobei in einer Ausführung der Verbrennungsmotor eine Heissgasturbine ist.

FUEL FEED FOR A TURBORAMJET ENGINE

Fuel delivery systems and methods

Increasing combustibility of low BTU natural gas

A system and methods for increasing a combustibility of a low BTU natural gas are provided herein. The method includes increasing the adiabatic flame temperature of the low BTU natural gas using heavy hydrocarbons, wherein the heavy hydrocarbons include compounds with a carbon number of at least two. The method also includes burning the low BTU natural gas in a gas turbine.

Combustion device and gas turbine

This combustion device (C) is provided with a combustor (3) for causing the combustion of fuel ammonia and combustion air within a combustion chamber (N), and the combustor is equipped with a cooling ammonia supply unit (3g) for mixing the fuel ammonia into the combustion air and supplying the mixture to within the combustor.

A PROCESS FOR UPGRADING PYROLYSIS OIL, TREATED PYROLYSIS OIL AND THE USE THEREOF

The present invention relates to a process for upgrading pyrolysis oil comprising heating pyrolysis oil in the absence of added catalyst at 100°C to 200°C temperature and 50 bar to 250 bar pressure, and heating the product of the first heating in the absence of added catalyst at 200°C to 400°C temperature and 50 bar to 250 bar pressure. The present invention also relates to the product obtained by the process according to the invention and to the use of treated pyrolysis oil. The invention further describes methods where the treated pyrolysis oil according to any process of the invention is fed to a power plant for producing electricity; is burned in a boiler for producing heating oil and/or is used as transportation fuel or as a blending component in transportation fuel.

METHOD TO OPTIMIZE EMISSION CONTROL DUST FOR THE GAS TURBINES AT HEAVY FUEL IS SUPPLIED.

Procédé pour récupérer l'énergie du gaz provenant d'un haut-fourneau, et installation de haut-fourneau pour la réalisation de ce procédé.

L'invention concerne un procédé pour récupérer l'énergie du gaz, provenant d'un haut-fourneau (21), le gaz de haut-fourneau étant à cet effet détendu, après un dépoussiérage grossier et/ou fin (10), dans une turbine de détente (12), qui peut être couplée à un générateur de courant (11), pour être ensuite injecté dans un réseau de gaz de haut-fourneau (13), en vue d'une utilisation ultérieure. Une partie du gaz de haut-fourneau dépoussiéré est déviée, avant sa détente dans la turbine, est éventuellement comprimée (compresseur de gaz de haut-fourneau (16)), et est brûlée en ajoutant, le cas échéant, un combustible de pouvoir calorifique élevé, les fumées étant détendues dans une turbine à gaz chauds (18), qui peut être couplée au générateur de courant, associé à la turbine de détente (12), ou à un générateur de courant propre (19). La température de la partie non déviée du gaz de haut-fourneau est de préférence relevée, avant l'injection du gaz dans la turbine de détente (12), par échange ...

Burning high-sulphur and ash fuels in power plant - by low-temp partial combustion and burning of gaseous product

Procédé d'alimentation en combustible d'un turbo-statoréacteur et turbo-statoréacteur pour la mise en oeuvre du procédé

... a) Procédé d'alimentation en combustible d'un turbo-statoréacteur et turbo-statoréacteur pour la mise en oeuvre du procédé. b) Il est caractérisé en ce qu'on injecte simultanément du kérosène et de l'hydrogène dans la chambre de combustion 11 et dans la plage des nombres de mach inférieurs, la combustion dans la chambre de combustion 11 se fait principalement avec du kérosène et dans l'ensemble de la plage des nombres de mach, et à mesure que le nombre de mach augmente, on déplace le rapport d'alimentation kérosène/hydrogène, en continu vers l'hydrogène. c) L'invention concerne un procédé d'alimentation en combustible d'un turbo-statoréacteur et un turbo-statoréacteur pour la mise en oeuvre du procédé.

AUXILIARY POWER PLANT OPERATING IN BI-FUEL AND USE THEREOF

SYSTEM FOR VAPORIZATION OF LIQUID FUELS FOR COMBUSTION AND METHOD OF USE

A gas stream with a reduced oxygen concentration relative to ambient air is used to vaporize a liquid fuel or liquified hydrocarbon gas, or is mixed with a vaporized gas, and the reduced oxygen vaporized fuel gas is fed to a combustion device such as a premixed or diffusion combustor. Preferably, the oxygen content of the gas stream is less than the limited oxygen index. By mixing the fuel with a gas stream that has an appropriately reduced oxygen content, auto- ignition prior to the flame front can be avoided. In some embodiements, the reduced oxygen stream is generated from an air separator or taken from the exhaust of the combustion device. © KIPO & WIPO 2007 ...

PROVIDING OXIDATION TO A GAS TURBINE ENGINE

A gas turbine engine includes a compressor for compressing air from an environment; a combustor for receiving the compressed air from the compressor, mixing the compressed air with fuel, and combusting the fuel; a turbine coupled with the compressor for receiving exhaust gas from the combustion and powering the compressor; and an injector coupled with a source of oxidizer for injecting the oxidizer into the combustor. A method for operating a gas turbine engine includes compressing air from an environment; receiving the compressed air at a combustor; mixing the compressed air with fuel; injecting oxidizer into the combustor in addition to the air from the environment; combusting the fuel with the compressed air and the oxidizer; receiving exhaust gas from the combusted fuel; and powering the compression of the air from the environment using the exhaust gas.

LIQUID FUEL ASSIST IGNITION SYSTEM OF A GAS TURBINE AND METHOD TO PROVIDE A FUEL/AIR MIXTURE TO A GAS TURBINE

Liquid fuel assist ignition system (1) for providing a fuel -air mixture to a gas turbine in its start-up phase, comprising a high pressure tank (2), a vacuum pump (3) connected to the high pressure tank (2), a liquid fuel inlet (4) connected to the high pressure tank (2), an air inlet (5) connected to the high pressure tank (2) and an outlet (6) of the high pressure tank (2) connected to a burner of the gas turbine (20), and method to provide a fuel/air mixture to a gas turbine (20) in its start-up phase using a liquid fuel assist ignition system (1).

Retrofit equipment for reducing the consumption of fossil fuel by a power plant using solar insolation

Retrofit equipment includes an auxiliary gas turbine unit including an auxiliary compressor for compressing ambient air to produce compressed air, a solar collector that receives the compressed air for heating the same to produce heated compressed air, and an auxiliary turbine coupled to the auxiliary compressor and to an auxiliary generator for expanding the heated compressed air and driving the auxiliary compressor and auxiliary generator thereby producing power and hot exhaust gases. When solar insolation is available, a flow control selectively supplies the hot exhaust gases from the retrofit equipment to a boiler which is part of a conventional fossil fueled power plant. The boiler has heat exchanger coils containing water and receives hot exhaust gases for vaporizing water in the coils and producing steam which is supplied to a steam turbine coupled to a generator for expanding steam produced by the boiler, and driving the generator and producing power and expanded steam. A condenser ...

Power turbine system with fuel injector and condensor

The power turbine system includes two power turbines communicating with an ion transport membrane (ITM) reactor. Heavy liquid fuel is atomized and burned within the reactor to drive the first turbine, with the first turbine producing useful power. Exhaust from the first turbine is recycled back into the reactor. The reactor includes a series of concentric cylindrical ion transport membranes that separate atmospheric and exhaust gases into suitable components for combustion therein, with at least some of the gases being “cracked” to alter their molecular structure for further combustion to power the second turbine. The second turbine drives a compressor to supply air to the reactor. At least one of the ITMs precludes atmospheric nitrogen from the combustion processes, with the resulting exhaust including pure water and carbon dioxide. The carbon dioxide is either recycled into the reactor to facilitate fuel atomization, or compressed for sequestration.

POWER SYSTEM FOR AIRCRAFT PARALLEL HYBRID GAS TURBINE ELECTRIC PROPULSION SYSTEM

A gas turbine engine includes a compressor section having a first compressor and a second compressor and a turbine section having a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. A motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. A power distribution system connects the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit. The power distribution system is configured to provide power from the stored power system to the motor. 1. A gas turbine engine comprising:a compressor section having a first compressor and a second compressor;a turbine section having a first turbine and a second turbine,the first compressor is connected to the first turbine via a first shaft;the second compressor is connected to the second turbine via a second shaft;a motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft; anda power distribution system connecting the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit, wherein the power distribution system is configured to provide power from the stored power system to the motor.2. The gas turbine engine of claim 1 , wherein the power distribution system is isolated within the gas turbine engine.3. The gas turbine engine of claim 1 , wherein the power distribution system is integrated with an aircraft power distribution system.4. The gas turbine engine of claim 3 , wherein the power distribution system is connected to at least one aircraft electric system claim 3 , and is configured to provide operational power to the at least one aircraft electric system.5. The gas turbine engine of claim 1 , wherein the stored power system includes an energy storage unit ...

COMBUSTION DEVICE AND GAS TURBINE

A combustion device burns fuel ammonia with combustion air in a combustion chamber, and includes: a combustor liner which forms the combustion chamber; a burner which is installed at one end of the combustor liner; a deflection member which is provided on a downstream side of the combustor liner in a flow direction of a combustion gas, and is configured to deflect the flow direction of the combustion gas; and at least one ammonia injection hole which is provided between the burner and an outlet of the deflection member and is configured to supply the fuel ammonia into the combustion chamber. 1. A combustion device which burns fuel ammonia with combustion air in a combustion chamber , the combustion device comprising:a combustor liner which forms the combustion chamber;a burner which is installed at one end of the combustor liner;a deflection member which is provided on a downstream side of the combustor liner in a flow direction of a combustion gas, and is configured to deflect the flow direction of the combustion gas; andat least one ammonia injection hole which is provided between the burner and an outlet of the deflection member and is configured to supply the fuel ammonia into the combustion chamber.2. The combustion device according to claim 1 , wherein the at least one ammonia injection hole is provided in a side wall of the combustor liner.3. The combustion device according to claim 1 , wherein:the at least one ammonia injection hole includes a plurality of ammonia injection holes; andthe plurality of ammonia injection holes are provided in the side wall of the combustor liner to be asymmetric around a central axis of the combustion chamber.4. The combustion device according to claim 1 , wherein a high temperature portion in which a temperature is higher than an average temperature in the deflection member is identified in advance claim 1 , and the at least one ammonia injection hole is disposed such that the temperature of the high temperature portion is ...

MICRO GAS TURBINE SYSTEMS AND USES THEREOF

The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine. Lastly, the present disclosure describes features of a fuel capture system that allow the injection of wellhead gas, which typically is a mixture of gaseous and liquid fuels, into the combustion chamber, and also describes methods of incorporating afterburners in the gas turbine engine, such that the gas turbine engine system can use wellhead gas to power equipment and reduce emissions from flaring in oil and gas applications. 117.-. (canceled)18. A method of operating a gas turbine heater , wherein the gas turbine heater comprises a gas turbine comprising i) an air starter; ii) a compressor; iii) a turbine; and iv) a combustion unit configured to receive compressed air for combustion from the compressor , to receive a fuel from a source , to burn the fuel to produce a combustion gas , and to supply the combustion gas to the turbine , wherein the gas turbine is configured to heat an external environment directly or indirectly using combustion gas exhausted from the turbine , the method comprising:operating a fan to pump air through an enclosure of the gas turbine heater such that the air passes from an ambient air inlet of the enclosure to an outlet of the ...

Combustion device and gas turbine engine system

The combustion device includes a combustor that combusts fuel ammonia and combustion air in a combustion chamber, wherein the combustor includes a cooling ammonia supplier that mixes the fuel ammonia into the combustion air and that supplies the fuel ammonia into the combustor.

ADVANCED COMBINED CYCLE SYSTEMS AND METHODS BASED ON METHANOL INDIRECT COMBUSTION

A methanol indirect combustion combined-cycle power generation apparatus and method. A liquid methanol input stream is evaporated to provide a gaseous methanol stream which is converted to syngas that is combusted in a gas turbine assembly to drive a first electrical generator and produce an exhaust gas. Heat from the exhaust gas of the gas turbine assembly is used to produce first and second steam streams. The first steam stream drives a first steam turbine and provides the heat required for converting the gaseous methanol stream to the syngas combustion stream. The second steam stream drives a second steam turbine and provides the heat required for evaporating the liquid methanol input stream. A second electrical generator is driven using at least one of the first and second steam turbines. 1. A methanol indirect combustion combined-cycle power generation apparatus comprising:a) an evaporation apparatus operable to evaporate a liquid methanol input stream to provide a gaseous methanol stream, the evaporation apparatus comprising a liquid inlet for receiving the liquid methanol stream and a gas outlet for discharging the gaseous methanol stream;b) a conversion apparatus connected downstream from the evaporation apparatus and operable to convert the gaseous methanol stream into a syngas combustion stream; the conversion apparatus comprising a gaseous methanol inlet fluidly coupled to the gas outlet of the evaporation apparatus and a syngas combustion stream outlet;c) a gas turbine assembly fluidly coupled to the combustion stream outlet and configured to burn the syngas combustion stream, the gas turbine assembly having an exhaust outlet and being drivingly connectable to a first electric generator;d) a heat recovery steam generator (HRSG) comprising an exhaust inlet fluidly coupled to the exhaust outlet and configured to receive an exhaust gas stream from the gas turbine assembly and to use the heat from the exhaust gas stream to generate steam, the HSRG comprising ...

Combustion device and gas turbine engine system

The combustion device includes: a compressor that compresses combustion air; a combustor that combusts the compressed combustion air and fuel ammonia; and an ammonia injector that injects the fuel ammonia into the combustion air during or before compression of the combustion air by the compressor and cools the combustion air.

Injector of an over-enriched fuel-and-air mixture to the combustion chamber of internal combustion engines

The invention relates to a fuel injector for injecting an over-enriched fuel and air mixture to the combustion chamber of an internal combustion engine, is characterised in that it comprises: 1. A fuel injector for injecting an over-enriched fuel and air mixture to the combustion chamber of an internal combustion engine , characterised in that it comprises{'b': 1', '2', '3', '4, 'a hydrocarbon liquid fuel spray nozzle (), at least one supply of a gaseous carrier (), a fuel mixing and evaporation chamber () and an injector nozzle () to the engine combustion chamber (C.C.),'}configured such that, during operation,{'b': 2', '3', '1', '4, 'liquid fuel is supplied and heated and compressed gaseous carrier () are supplied to the fuel mixing and evaporation chamber () of this injector through the spray nozzle (), where they are mixed and evaporated as a result of elevated temperature, and the mixture of evaporated fuel with a hot gaseous carrier with low oxygen content thus formed reaches the combustion chamber (C.C.), through the outlet (), wherein'}the gaseous carrier is air or, alternatively, flue gas, at elevated pressure and temperature and having a composition that prevents the initiation of flame combustion, andthe gaseous carrier has oxygen content low enough to prevent the initiation of combustion, even under conditions of elevated pressure and temperature.23. The injector according to claim 1 , wherein a gaseous carrier comprising air/oxidant claim 1 , flue gas claim 1 , air and flue gas claim 1 , vapour claim 1 , an addition thereof or a combination of all the components claim 1 , is mixed in the injector chamber () with heated fuel.31323. The injector according to claim 1 , wherein the injection of fuel () into the mixing chamber () is arranged coaxially relative to the symmetry axis of the mixing chamber claim 1 , while the intake of the gaseous carrier () is arranged axially claim 1 , tangentially or radially relative to the lateral surface of the mixing ...

LIQUID BIO-FUELS

Liquid bio-fuels and processes for their production are provided. The liquid bio-fuels can have improved stability, less corrosiveness, and/or an improved heating value. 1. A liquid bio-fuel comprising: 50 to 95 weight percent oxygenated hydrocarbons; 5 to 50 weight percent nonoxygenated hydrocarbons; not more than 15 weight percent water; and not more than 2 ,500 ppmw solids , wherein said liquid bio-fuel has an ignition temperature in the range of 175 to 300° C. and a higher heating value at least 9 ,000 btu/lb.2. The liquid bio-fuel of having a stability parameter of not more than 20 cp/h.3. The liquid bio-fuel of having an oxygen content of not more than 20 weight percent.4. The liquid bio-fuel of having a total acid number of not more 90 mg KOH/g.5. The liquid bio-fuel of having a hard solids content of not more than 1 claim 1 ,000 ppmw.6. The liquid bio-fuel of having a viscosity at 40° C. of not more than 125 cps.7. The liquid bio-fuel of having an aromatic content of at least 40 weight percent based on the total weight of said nonoxygenated hydrocarbons and a phenolic content of not more than 80 weight percent based on the total weight of said oxygenated hydrocarbons.8. The liquid bio-fuel of having a 10% boiling point in the range of 160 to 420° C. claim 1 , a 50% boiling point in the range of 340 to 520° C. claim 1 , and a 90% boiling point in the range of 620 to 940° C.9. The liquid bio-fuel of having a specific gravity in the range of 0.75 to 1.1 claim 1 , a flashpoint in the range of 40 to 120° C. claim 1 , a calcium content of not more than 5 claim 1 ,000 ppmw claim 1 , a potassium content of not more than 5 claim 1 ,000 ppmw claim 1 , and a sodium content of not more than 1 claim 1 ,000.10. The liquid bio-fuel of comprising 75 to 90 weight percent of said oxygenated hydrocarbons; 10 to 25 weight percent of said nonoxygenated hydrocarbons; in the range of 2 to 10 weight percent of said water; and not more than 500 ppmw of said solids claim 1 , wherein ...

LIQUID FUEL COMBUSTOR HAVING AN OXYGEN-DEPLETED GAS (ODG) INJECTION SYSTEM FOR A GAS TURBOMACHINE

A liquid fuel combustor for a gas turbomachine includes a combustor body, a combustor liner arranged in the combustor body defining a combustion chamber extending from a head end to a combustor discharge. The combustor liner is spaced from the combustor body forming a compressor discharge casing (CDC) airflow passage. A nozzle is arranged at the head end of the combustor liner. The nozzle includes a first inlet, a second inlet and an outlet configured and disposed to establish a flame zone. The first inlet is configured to receive a first fluid and the second inlet is configured to receive a second fluid. The second fluid includes a liquid fuel. An oxygen-depleted gas (ODG) injection system is arranged radially outwardly of the nozzle. The ODG injection system is configured and disposed to deliver an oxygen-depleted gas stream into the combustion chamber to vaporize a portion of the second fluid. 1. A liquid fuel combustor for a gas turbomachine comprising:a combustor body;a combustor liner arranged in the combustor body defining a combustion chamber extending from a head end to a combustor discharge, the combustor liner being spaced from the combustor body forming a compressor discharge casing (CDC) airflow passage;at least one nozzle arranged at the head end of the combustor liner, the at least one nozzle including a first inlet, a second inlet and an outlet configured and disposed to establish a flame zone, the first inlet configured to receive a first fluid and the second inlet configured to receive a second fluid, the second fluid including a liquid fuel; andan oxygen-depleted gas (ODG) injection system arranged radially outwardly of the at least one nozzle, the ODG injection system being configured and disposed to deliver an oxygen-depleted gas stream into the combustion chamber to vaporize a portion of the second fluid.2. The liquid fuel combustor according to claim 1 , wherein the ODG injection system includes at least one recirculation member arranged at ...

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.

PROCESS FOR UPGRADING PYROLYSIS OIL, TREATED PYROLYSIS OIL AND THE USE THEREOF

A process for upgrading pyrolysis oil that includes heating pyrolysis oil in the absence of added catalyst at 100° C. to 200° C. temperature and 50 bar to 250 bar pressure, and heating the product of the first heating in the absence of added catalyst at 200° C. to 400° C. temperature and 50 bar to 250 bar pressure. Also, the product obtained by this process and the use of treated pyrolysis oil. Further, methods where the treated pyrolysis oil is fed to a power plant for producing electricity; is burned in a boiler for producing heating oil and/or is used as transportation fuel or as a blending component in transportation fuel. 116-. (canceled)17. A process for upgrading pyrolysis oil , comprising the steps ofa) heating said pyrolysis oil in the absence of added catalyst at 100° C. to 200° C. temperature and 50 bar to 250 bar pressure, andb) heating the product of step a) in the absence of added catalyst at 200° C. to 400° C. temperature and 50 bar to 250 bar pressure.18. The process according to claim 18 , wherein said temperature of step a) preferably is from 100° C. to 150° C.19. The process according to claim 18 , wherein said temperature of step b) preferably is from 300° C. to 350° C.20. The process according to claim 18 , wherein said pressure of step a) and/or step b) preferably is from 150 to 200 bar.21. The process according to claim 18 , wherein step a) and/or step b) are carried out under a gas atmosphere comprising at least one of carbon monoxide claim 18 , hydrogen claim 18 , nitrogen or mixtures thereof claim 18 , preferably carbon monoxide claim 18 , most preferably a mixture of carbon monoxide and hydrogen.22. The process according to claim 18 , wherein said step a) and said step b) are carried out in separate reactors under same or different gas atmosphere.23. The process according to claim 18 , wherein the process further comprises a step ofc) separating a water phase from an intermediate product.24. The process according to claim 18 , wherein the ...

DIFFUSION FLAME BURNER FOR A GAS TURBINE ENGINE

A diffusion flame burner () is provided for a gas turbine engine (). The diffusion flame burner includes concentrically oriented spray cones () staged in a plurality of stages () and attached to a water supply () during a gas mode and attached to an oil supply () during an oil mode. The diffusion flame burner also includes a central spray cone () positioned at a center () of the concentrically oriented spray cones and attached to the water supply during the oil mode. The diffusion flame burner also includes a plurality of concentrically oriented outlets () positioned outside the plurality of concentrically oriented spray cones and attached to a combined water and natural gas supply () during the gas mode. 1. A diffusion flame burner , comprising:a plurality of concentrically oriented spray cones staged in a plurality of stages and attached to a water supply; anda diffusion outlet attached to a fluid supply.2. The diffusion flame burner of claim 1 , wherein the diffusion outlet is a plurality of concentrically oriented outlets positioned outside the plurality of concentrically oriented spray cones.3. The diffusion flame burner of claim 2 , wherein the fluid supply is a combined water and natural gas supply.4. The diffusion flame burner of claim 1 , wherein at least one of the stages is activated based on a parameter of fluid directed from the fluid supply to the diffusion outlet.5. The diffusion flame burner of claim 4 , wherein the parameter is a flow rate of the fluid.6. The diffusion flame burner of claim 4 , wherein the parameter is a viscosity of the fluid.7. The diffusion flame burner of claim 1 , further comprising a gas turbine engine including the diffusion flame burner.8. The diffusion flame burner of claim 1 , wherein the spray cones in each stage have a circumferential uniform arrangement in the diffusion flame burner.9. A diffusion flame burner claim 1 , comprising:a plurality of concentrically oriented spray cones staged in a plurality of stages and ...

SYSTEM AND METHOD FOR POWER PRODUCTION USING PARTIAL OXIDATION

The present disclosure relates to a power production system that is adapted to achieve high efficiency power production using partial oxidation of a solid or liquid fuel to form a partially oxidized stream that comprises a fuel gas. This fuel gas stream can be one or more of quenched, filtered, and cooled before being directed to a combustor of a power production system as the combustion fuel. The partially oxidized stream is combined with a compressed recycle COstream and oxygen. The combustion stream is expanded across a turbine to produce power and passed through a recuperator heat exchanger. The expanded and cooled exhaust stream can be further processed to provide the recycle COstream, which is compressed and passed through one or more recuperator heat exchangers in a manner useful to provide increased efficiency to the combined systems. 1. A process for the production of power using a combination of a partial oxidation (POX) system and a power production system (PPS) , the process comprising:combining a solid or liquid fuel and oxygen in a POX reactor under conditions sufficient to partially oxidize the fuel and form a POX stream comprising a fuel gas at a first temperature;removing from the POX stream comprising the fuel gas at least a portion of any solid components or gaseous components that do not form part of the fuel gas;cooling the POX stream comprising the fuel gas in a POX heat exchanger to a second, lower temperature;purifying the POX stream comprising the fuel gas by removing at least a portion of any liquid water and acid gases therefrom and thus forming a stream of the fuel gas;compressing the stream of the fuel gas to a pressure of about 12 MPa or greater;combusting the stream of the fuel gas in a PPS combustor to form a combustion product stream at a pressure of at least about 10 MPa and a temperature of at least about 800° C.;expanding the combustion product stream across a PPS turbine to generate power and form an expanded PPS combustion ...

Zero Emissions Turbofan [With Aeroderivative Power Generation and Marine Applications]

This is an application for a utility patent for a zero emissions turbine, suitable for use in aerospace, power generation, industrial, and marine applications, that runs on the combustion of liquid hydrogen and liquid oxygen and which is cooled by liquid oxygen. It is unique in that its only emissions will be steam, water vapor, pure oxygen, and ice crystals, with no pollutants or greenhouse gases of any kind. It is also unique in that it uses no air intake, no compressor, and simplified shaft and auxiliary drive systems. It has a unique tank and pump system that runs on electric motors and specialized lubricating systems. These turbines can be designed with powerful and reliable operating specifications with greatly reduced fuel consumption and greatly improved power-to-weight ratios. 1. This is the design of a new type of zero emissions turbine , suitable for use as an aerospace turbine , as an aeroderivative power generation gas turbine , and as a marine turbine , that runs on liquid hydrogen and liquid oxygen fuel and uses a liquid oxygen cooling system , producing an exhaust of steam , water vapor , ice crystals , and pure oxygen.2. This is a unique gas turbine design in that it does not require any air intake or compressor , unlike every other working gas turbine design in the world today. Instead , it creates the pressure used to turn the turbine solely by burning and gasifying its fuel in the combustor. Unlike modern steam turbines , it does not require a massive independent boiler to create steam pressure. As such , it can use greatly simplified shaft and auxiliary drive designs , and can create much more usable power with much less fuel , at any altitude , at any depth in the ocean , in any kind of weather condition , at any foreseeable temperature , and practically irregardless of bird strikes and interference from other airborne objects.3. This design uses a unique system of liquid hydrogen and liquid oxygen fuel pumps and tanks driven by electric motors ...

Microscale distributed energy cogeneration method and system

A microscale energy cogeneration system comprising at least one micro/nano-turbine for converting fuel into mechanical energy and a generator for converting mechanical energy produced by the micro/nano-turbine into electrical energy in the range of 1 to 5 kWh. Compressed air passes through a cold side of a heat exchanger. The compressed cold air and fuel delivered to a combustion chamber drives the turbine. At least one heat exchanger receives high temperature exhaust gas from an exhaust passage downstream from the micro/nano-turbine for heat transfer. The heat exchanger can be used to heat water and/or air of a house. A water heating system can be coupled to the heat exchanger for converting tap water into potable hot water and/or converting cool air into hot air. The portable micro/nano-turbine set can be scaled up by interconnecting several units to a network for balancing out the energy demand of multiple users.

METHOD AND EQUIPMENT FOR COMBUSTION OF AMMONIA

A method for the combustion of ammonia, wherein a first combustion chamber () receives ammonia () and hydrogen () in controlled proportions, and an oxygen-containing gas. Combustion of the ammonia and hydrogen produces NH ions among other combustion products (). A second combustion chamber () receives the combustion products () from the first combustion chamber and receives further ammonia () and further hydrogen () in controlled proportions, wherein combustion produces nitrogen oxides among other combustion products (). A third combustion chamber () receives the nitrogen oxides along with further ammonia and further hydrogen in further controlled proportions along with further oxygen-containing gas, such that the nitrogen oxides are combusted into nitrogen and water. 1. A method for the combustion of ammonia , wherein a first combustion chamber receives ammonia and hydrogen in controlled proportions , and an oxygen-containing gas , wherein combustion of the ammonia and hydrogen produces NH ions among other combustion products , and wherein a second combustion chamber receives the combustion products from the first combustion chamber and receives further ammonia and further hydrogen in controlled proportions , wherein combustion in the second combustion chamber produces nitrogen oxides among other combustion products , and wherein a third combustion chamber receives the combustion products of the second combustion chamber including nitrogen oxides along with further ammonia and further hydrogen in further controlled proportions along with further oxygen-containing gas , such that the nitrogen oxides are combusted into nitrogen and water.2. A method for the combustion of ammonia according to wherein energy from the combustion in the second combustion chamber is recovered by operation of a first turbine by exhaust gases from the second combustion chamber to convert energy released by combustion in the second combustion chamber into mechanical energy.3. A method for ...

System for exhaust mixture condensation and power turbine

The power turbine system includes two power turbines communicating with an ion transport membrane (ITM) reactor. Heavy liquid fuel is atomized and burned within the reactor to drive the first turbine, with the first turbine producing useful power. Exhaust from the first turbine is recycled back into the reactor. The reactor includes a series of concentric cylindrical ion transport membranes that separate atmospheric and exhaust gases into suitable components for combustion therein, with at least some of the gases being “cracked” to alter their molecular structure for further combustion to power the second turbine. The second turbine drives a compressor to supply air to the reactor. At least one of the ITMs precludes atmospheric nitrogen from the combustion processes, with the resulting exhaust including pure water and carbon dioxide. The carbon dioxide is either recycled into the reactor to facilitate fuel atomization, or compressed for sequestration.

POWER TURBINE SYSTEM WITH FUEL INJECTOR AND CONDENSOR

The power turbine system includes two power turbines communicating with an ion transport membrane (ITM) reactor. Heavy liquid fuel is atomized and burned within the reactor to drive the first turbine, with the first turbine producing useful power. Exhaust from the first turbine is recycled back into the reactor. The reactor includes a series of concentric cylindrical ion transport membranes that separate atmospheric and exhaust gases into suitable components for combustion therein, with at least some of the gases being “cracked” to alter their molecular structure for further combustion to power the second turbine. The second turbine drives a compressor to supply air to the reactor. At least one of the ITMs precludes atmospheric nitrogen from the combustion processes, with the resulting exhaust including pure water and carbon dioxide. The carbon dioxide is either recycled into the reactor to facilitate fuel atomization, or compressed for sequestration. 17-. (canceled)8. A power turbine system with integrated fuel line and condenser , comprising:a multi-stage ion transport membrane reactor, the multi-stage ion transport membrane reactor having an elongate fuel evaporation core, a first air delivery passage disposed above the fuel evaporation core, a button cell ion transport membrane disposed between the fuel evaporation core and the first air delivery passage, and a plurality of ion transport membranes spaced from the elongate fuel evaporation core and the first air delivery passage, the membranes defining corresponding working chambers therebetween;a first power turbine communicating with the reactor;a second power turbine communicating with the reactor;an air compressor communicating with the second power turbine and the reactor;a cylindrical fuel partial conversion chamber disposed concentrically about the fuel evaporation core;a gaseous nitrogen output chamber disposed concentrically about the first air delivery passage;a cylindrical fuel complete conversion ...

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.

ENGINE FOR HYPERSONIC AIRCRAFTS WITH SUPERSONIC COMBUSTOR

Described is a propulsion system () for hypersonic aircraft, having an air inlet () of a fluid (), a containment duct () and an exhaust nozzle (). The propulsion system () comprises a bypass duct () for a flow () of fluid (), an air-breathing engine () and a rocket () configured for processing respective flows () of fluid (). The bypass duct (), the air-breathing engine () and the rocket () are operatively associated with each other in such a way as to generate a thermodynamic-fluid interaction in a same portion of space () between the respective flows () processed in an operating configuration of the propulsion system () and wherein the portion of space () is inside the containment duct (). 21333313320130aa. The propulsion system () according to claim 1 , wherein the portion of inner space () comprises a region of a supersonic combustor () of the propulsion system () in which an increase occurs in the enthalpy which can be derived from the conversion of chemical energy of a fuel into thermal energy claim 1 , the region of a supersonic combustor () being located in a radially central position relative to the containment duct of () of the propulsion system () claim 1 , at the exhaust nozzle () with a conversion of the thermal energy into a kinetic energy.3122232223222333aaa. The propulsion system () according to claim 2 , wherein the air-breathing engine () and/or the rocket () are configured for making the thermal energy by a combustion process claim 2 , the air-breathing engine () and the rocket () being configured for conveying the respective processed flows ( claim 2 , ) towards the supersonic combustor ().41231102322110222323404022221aaaaa. The propulsion system () according to has a longitudinal direction of extension (L) relative to which the flow () of fluid () of the rocket () flows in a centred manner claim 1 , the flow () of fluid () of the air-breathing engine () being located in a position radially outside the flow () of the rocket () and the flow () of ...

Polished turbine fuel

Turbine fuel provided for large-scale land based turbines used by utilities for producing electricity and desalinated water, and for large mobile engines and turbines in marine and remote applications where only liquid fuels are available. Use results in less corrosion, ash formation and emissions (NOx, SOx, CO2 and noxious metals) than firing contaminated heavy crude, refinery residual oils or high sulfur fuel oils. Manufacture is by decontaminating crude oils, non-conventional crudes, and other highly contaminated feeds. Each fuel is produced as a single product of unit operations, not ex-plant blend of various refinery products, yet using an apparatus configuration less complex than conventional crude oil refining. These fuels can be fired by advanced high efficiency turbines of combined cycle power plants having hot flow paths and heat recovery steam generation systems susceptible to corrosion, which systems cannot otherwise risk contaminated heavy crudes or refinery residual oils feeds.

System and methods for igniting and operating a gas turbine engine with alternative fuels

A power generation system includes a combustion system, a liquid supply system, and a vapor supply system. The combustion system is configured to generate power by combusting an alternative fuel. The liquid supply system is configured to channel a liquid alternative fuel to the combustion system. The vapor supply system is configured to channel a vapor alternative fuel to the combustion system. The combustion system is ignited by combusting the liquid alternative fuel from the liquid supply system and is operated by combusting the vapor alternative fuel from the vapor supply system.

METHODS OF PROVIDING HIGHER QUALITY LIQUID KEROSENE BASED-PROPULSION FUELS

By blending a quantity of synthetic cyclo-paraffinic kerosene fuel blending component comprising at least 99.5 mass % of carbon and hydrogen content and at least 50 mass % of cyclo-paraffin into kerosene base fuel, kerosene based-propulsion fuels can be upgraded to higher quality kerosene based-propulsion fuels such as jet fuel or rocket fuel to meet certain specification and/or increase volumetric energy content of the propulsion fuel. 1. A method for upgrading a kerosene fuel to meet Jet A-1 specification or JP-8 specification;{'sup': '3', 'a. providing a quantity of kerosene base fuel having a boiling point in the range of 130° C. to 300° C., at atmospheric pressure, flash point of 38° C. or above measured by ASTM D56, a density at 15° C. of at least 775 kg/mand freezing point of above −47° C.;'}{'sup': '3', 'b. providing a quantity of synthetic cyclo-paraffinic kerosene fuel blending component comprising at least 99.5 mass % of carbon and hydrogen content and at least 50 mass % of cyclo-paraffin, said cyclo-paraffinic kerosene fuel blending component having a boiling point of at most 300° C., at atmospheric pressure, flash point of 38° C., or above, a density at 15° C. of at least 800 kg/m, and freezing point of −60° C. or below; and'}c. blending a quantity of the synthetic cyclo-paraffinic kerosene fuel blending component and the kerosene base fuel in amount sufficient to lower the freezing point of the blended fuel to −47° C. or lower.2. The method of wherein the blended fuel has a density of equal or above 800 kg/m.3. The method of wherein the aromatic content of the blended fuel is less than or equal to 25 vol %4. The method of wherein the amount of the synthetic cyclo-paraffinic kerosene fuel blending component is at least 1 vol. % claim 1 , based on the blended fuel.5. The method of wherein the amount of the synthetic cyclo-paraffinic kerosene fuel blending component is at least 3 vol. % claim 4 , based on the blended fuel.6. The method of wherein the ...

Cooled cooling air taken directly from combustor dome

A gas turbine engine includes a compressor, a turbine, and a combustor. The combustor includes a fuel injector and a vaporizer within the combustor positioned to receive liquid fuel from the fuel injector to vaporize the liquid fuel therein. The gas turbine engine includes an enclosed passage external to the combustor having a wall, a diffuser positioned to direct the air into the passage, causing the air to cool by transferring heat through the wall from the air within the passage to the vaporized fuel within the vaporizer, and a cooled cooling air passageway positioned to receive the air from the passage and direct the air after being cooled to at least one of the turbine and the compressor.

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.

POLISHED TURBINE FUEL

Turbine fuel provided for large-scale land based turbines used by utilities for producing electricity and desalinated water, and for large mobile engines and turbines in marine and remote applications where only liquid fuels are available. Use results in less corrosion, ash formation and emissions (NOx, SOx, CO2 and noxious metals) than firing contaminated heavy crude, refinery residual oils or high sulfur fuel oils. Manufacture is by decontaminating crude oils, non-conventional crudes, and other highly contaminated feeds. Each fuel is produced as a single product of unit operations, not ex-plant blend of various refinery products, yet using an apparatus configuration less complex than conventional crude oil refining. These fuels can be fired by advanced high efficiency turbines of combined cycle power plants having hot flow paths and heat recovery steam generation systems susceptible to corrosion, which systems cannot otherwise risk contaminated heavy crudes or refinery residual oils feeds. 110-. (canceled)11211022033040260370100200300400. A method to convert a contaminated crude oil () comprising sulfur and metals , with or without presence of added feed steams , to a fuel having a sulfur content limit characterized in that the crude is fractionated into three liquid fractions F () , F () , and F ( , ) and at least a portion of fraction F () and a portion fraction F are hydrotreated () wherein fractionating ( , ) and hydrotreating ( , ) conditions are adjusted such that:{'b': 4', '100', '1', '8', '10, 'a. overhead partial condensation of condensable entrained light gases () occurs during fractionation () without added stabilization steps to remove butanes and other lighter components to form a portion of fraction F (, ),'}{'b': 1', '10', '2', '20', '3', '30, 'b. each fraction of crude is determined by its wt. % sulfur content such that sulfur content of fraction F () is less than that of fraction F () which is less than fraction F (),'}{'b': 3', '30, 'c. ...

POLISHED TURBINE FUEL

Turbine fuel provided for large-scale land based turbines used by utilities for producing electricity and desalinated water, and for large mobile engines and turbines in marine and remote applications where only liquid fuels are available. Use results in less corrosion, ash formation and emissions (NOx, SOx, CO2 and noxious metals) than firing contaminated heavy crude, refinery residual oils or high sulfur fuel oils. Manufacture is by decontaminating crude oils, non-conventional crudes, and other highly contaminated feeds. Each fuel is produced as a single product of unit operations, not ex-plant blend of various refinery products, yet using an apparatus configuration less complex than conventional crude oil refining. These fuels can be fired by advanced high efficiency turbines of combined cycle power plants having hot flow paths and heat recovery steam generation systems susceptible to corrosion, which systems cannot otherwise risk contaminated heavy crudes or refinery residual oils feeds. 119-. (canceled)20600. A process to produce a single product liquid fuel () comprising:a. feeding a contaminated hydrocarbonaeous flowing feed (2) selected from the group consisting of one or more of crude oils, refinery residual oils, high sulfur fuel oils, biomass liquids, or hydrocarbon oil slurries containing particles of coke, coal, peat or ash to a basic separation zone which serves as a primary decontaminator,{'b': 10', '20', '30, 'b. separating said liquid feed in said zone into a minimum number of basic segments (, , ) based upon measurement of contaminate levels of effluent streams, not based upon measurement of hydrocarbon composition, temperature range or other non-contaminant related separation criteria,'}{'b': '100', 'claim-text': [{'b': 100', '10, '(i) a reduced contaminate level segment (), which without substantial subsequent treatment, forms a fuel component stream (),'}, {'b': 20', '300', '60, '(ii) a contaminated segment () which is treated () by hydrogen in ...

CRYOGENIC FUEL COMPOSITIONS AND DUAL FUEL AIRCRAFT SYSTEM

Cryogenic fuel compositions including a cryogenic fuel and paraxyelene and a dual fuel aircraft system for an aircraft having at least one turbine engine, including a first fuel system for providing a first fuel from a first fuel tank to the turbine engine and a second fuel system for providing a cryogenic fuel composition and having a second fuel tank storing LNG and fluidly coupled to the turbine engine, an additive tank storing additives and fluidly coupled to the turbine engine and a mixing device configured to create the cryogenic fuel composition. 1. A cryogenic fuel composition , comprising:liquid natural gas (LNG); andparaxylene in an amount sufficient to increase the lubricity of the composition while being soluble in LNG.2. The cryogenic fuel composition of wherein the paraxylene has a concentration in the cryogenic fuel composition above 23 parts per million.3. The cryogenic fuel composition of claim 2 , further comprising at least one additive selected from a group including benzene claim 2 , toluene claim 2 , and meta xylene.4. The cryogenic fuel composition of wherein the additives include a majority of paraxylene and lower concentrations of one of benzene claim 3 , toluene claim 3 , and meta xylene.5. The cryogenic fuel composition of wherein the additives have a concentration in the cryogenic fuel composition up to 120 parts per million.6. A cryogenic fuel composition claim 1 , comprising:a major amount of LNG; anda minor amount of paraxylene having a concentration in the cryogenic fuel composition of 1 to 120 parts per million.7. The cryogenic fuel composition of claim 6 , further comprising concentrations claim 6 , lower than that of the paraxylene claim 6 , of one of benzene claim 6 , toluene claim 6 , and meta xylene.8. A dual fuel aircraft system for an aircraft having at least one turbine engine claim 6 , comprising:a first fuel system for providing a first fuel from a first fuel tank to the turbine engine; anda second fuel system for providing ...

METHOD OF OPTIMIZING THE LIMITATION OF DUST EMISSIONS FOR GAS TURBINES FUELED WITH HEAVY FUEL OIL.

Method for optimizing the limitation of dust emissions from a gas turbine or combustion plant comprising a line for supplying liquid fuel oil, a line for generating fuel oil atomizing air, and a central controller, wherein: a first definition step, starting from a nominal temperature of the fuel oil and a nominal pressure ratio of the atomizing air of the fuel oil, and by controlling the injection of the soot inhibitor, of a nominal operating point corresponding to the maximum permissible level of emitted dust; a second step of controlling a first parameter, taken from the group of the fuel oil temperature and the pressure ratio of the fuel oil atomizing air, in order to reach another operating point; and a third step of controlling the soot inhibitor injection to achieve the maximum permissible level of emitted dust. 2. The method according to claim 1 , wherein the three steps take place under the control of the central controller.3. The method according to claim 2 , wherein after the third step claim 2 , the central controller triggers a new claim 2 , second control step of the second parameter taken from the group of the fuel oil temperature and the atomizing air pressure ratio of the fuel oil.4. The method according to claim 1 , wherein the control of the first parameter is controlled between a minimum value and a maximum value.5. The method according to claim 4 , wherein the control of the temperature of the fuel oil is controlled between 50° C. and 135° C.6. The method according to claim 4 , wherein the pressure ratio of the fuel oil atomizing air is controlled between 1.1 and 1.8.7. A gas turbine or combustion plant comprising:a liquid fuel oil supply line connecting a fuel source to at least one combustion chamber, comprising means for controlling the temperature of the fuel oil, and means for storing and controlling the injection of a soot inhibitor,a line for generating the fuel oil atomizing air, connecting a main compressor to at least one combustion ...

ENGINE CONTROL DEVICE AND METHODS THEREOF

An engine control device may comprise a processor and a memory. The engine control device may be configured to modify a fuel flow based on a density of the fuel proximate a fuel nozzle. The engine control device may include a densimeter embedded in, or disposed proximate, the engine control device. The engine control device may include a temperature sensor embedded in, or disposed proximate, the engine control device. The engine control device may be electrically coupled to a fuel valve and/or configured to modulate the fuel valve based on a density of the fuel at the fuel valve. 1. An engine control device , comprising:a housing;a fluid conduit disposed through the housing, the fluid conduit configured to receive fuel during operation of the engine control device; anda densimeter operably coupled to the fluid conduit, the densimeter being disposed in the housing and configured to determine a density of the fuel.2. The engine control device of claim 1 , wherein the engine control device is configured to control a fuel flow to a fuel nozzle based on measurements from the densimeter.3. The engine control device of claim 1 , further comprising:a temperature sensor operably coupled to the fluid conduit to measure a temperature of the fuel;a processor; and detecting, by the processor, a first temperature of the fuel flowing through the fluid conduit from the temperature sensor;', 'detecting, by the processor, a first density of the fuel at the first temperature from the densimeter;', 'calculating, by the processor, a second density at a second temperature; and', 'modifying, by the processor, a fuel flow to a fuel nozzle of a gas-turbine engine based on the second density., 'a non-transitory computer readable storage medium in electronic communication with the processor, the non-transitory computer readable storage medium having instructions stored thereon that, in response to execution by the processor cause the processor to perform operations comprising4. The engine ...

Methods of operating a gas turbine to inhibit vanadium corrosion

A method of inhibiting vanadic corrosion of a hot part of a gas turbine system is provided. The method includes introducing, in the combustor, a first oxide comprising magnesium oxide (MgO) and at least one second oxide from among Al 2 O 3 , Fe 2 O 3 , TiO 2 and SiO 2 . A ratio “m” of a number of moles of MgO to a number of moles of V 2 O 5 and a ratio “a” of a total number of moles of the at least one second oxide to the number of moles of V 2 O 5 satisfy two conditions based on a firing temperature of the expansion turbine, an average density of one or more double oxides formed by a reaction between MgO and the at least one second oxide, and an average Knoop hardness of the one or more double oxides formed by the reaction between MgO and the at least one second oxide.

Micro gas turbine systems and uses thereof

The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine. Lastly, the present disclosure describes features of a fuel capture system that allow the injection of wellhead gas, which typically is a mixture of gaseous and liquid fuels, into the combustion chamber, and also describes methods of incorporating afterburners in the gas turbine engine, such that the gas turbine engine system can use wellhead gas to power equipment and reduce emissions from flaring in oil and gas applications.

BIO-FUEL COMPOSITION AND METHOD FOR MANUFACTURE OF BIO-FUEL COMPOSITION

The present invention provides a liquid bio-fuel mixture comprising: a liquid condensate product of bio-mass fast pyrolysis; a bio-diesel component; and an alcohol component. The liquid bio-fuel mixture is macroscopically single phase. The alcohol component is selected from methanol, a Cto Calcohol, and a mixture of two or more different Cto Calcohols. 2. A liquid bio-fuel mixture according to wherein the liquid is macroscopically single phase at room temperature (e.g. 20-25° C.).3. A liquid bio-fuel mixture according to wherein the liquid condensate product of biomass pyrolysis is itself macroscopically single phase.4. A liquid bio-fuel mixture according to wherein the liquid product of biomass pyrolysis contains at least 10 wt % water.5. A liquid bio-fuel mixture according to wherein the liquid condensate produce of biomass pyrolysis contains at most 40 wt % water.6. A liquid bio-fuel mixture according to wherein the mixture consists essentially of:from 5 wt % to 50 wt % of the liquid condensate product of biomass fast pyrolysis;from 5 wt % to 50 wt % of the bio-diesel component;from 30 wt % to 90 wt % of the alcohol component; andfrom 0 wt % to 60 wt % of optional additional components.8. A liquid bio-fuel mixture according to wherein the liquid bio-fuel mixture further comprises 20 wt % or less claim 7 , with respect to the total weight of the bio-fuel mixture claim 7 , of additional components and impurities.9. A liquid bio-fuel mixture according to wherein claim 1 , where the bio-fuel mixture includes 40 wt % or less of the alcohol component with respect to the total weight of the bio-fuel mixture claim 1 , the alcohol component is a Cor higher alcohol claim 1 , or a mixture of different alcohols comprising predominantly Cor higher alcohols.10. A liquid bio-fuel mixture according to wherein claim 1 , where the bio-fuel mixture comprises 45 wt % or less of the alcohol component with respect to the total weight of the bio-fuel mixture claim 1 , the alcohol ...

POLISHED TURBINE FUEL

Turbine fuel provided for large-scale land based turbines used by utilities for producing electricity and desalinated water, and for large mobile engines and turbines in marine and remote applications where only liquid fuels are available. Use results in less corrosion, ash formation and emissions (NOx, SOx, CO2 and noxious metals) than firing contaminated heavy crude, refinery residual oils or high sulfur fuel oils. Manufacture is by decontaminating crude oils, non-conventional crudes, and other highly contaminated feeds. Each fuel is produced as a single product of unit operations, not ex-plant blend of various refinery products, yet using an apparatus configuration less complex than conventional crude oil refining. These fuels can be fired by advanced high efficiency turbines of combined cycle power plants having hot flow paths and heat recovery steam generation systems susceptible to corrosion, which systems cannot otherwise risk contaminated heavy crudes or refinery residual oils feeds. 121.-. (canceled)22100110220330123. A fractionator () having upper , middle and lower zones for separating crude oil feed characterized in that such fractionator does not achieve fractionation efficiency for precise target cuts based on temperature , hydrocarbon composition or other non-contaminant related separation criteria but achieves feed separation to respective fractions F () , F () and F () based on contaminate levels of target fractions F , F and F , either as one cut for each such fraction or multiple cuts combined to form each such fraction , which fractionator has , when processing the same crude for a comparative to conventional crude oil distillations processing such same crude , a higher temperature profile in the upper zone which:a. avoids excessive vapor condensation and flooding experienced in the upper sections of conventional crude oil distillation caused by sub-cooling and related pressure change upsets leading to condensation of stripping steam and ...

BIOFUEL PRODUCT AND METHOD FOR THE PRODUCTION THEREOF

The invention relates to a method for producing a biofuel from an aqueous mixture of carbonised biomass obtained by means of a method for the hydrothermal carbonisation of biomass, characterised in that it comprises: (a) grinding the aqueous mixture of carbonised biomass until a maximum size of less than 500 micrometres of the particles contained in the mixture is obtained; (b) applying a method for the physical separation of inorganic substances; and (c) reducing the moisture content until a water content of between 25 and 55 wt. % is reached. The invention also relates to the biofuel obtained by said method, and to the use thereof in various applications. 110-. (canceled)11. Process for obtaining a biofuel from an aqueous mixture of carbonised biomass obtained in a process for hydrothermal carbonisation of the biomass , characterised in that it comprises:(a) grinding the aqueous mixture of carbonised biomass, wherein the mixture has a carbon content of at least 60% and a content of volatile substances of between 50 and 70%, percentages which are expressed on a dry base and without ashes, until a maximum size of particles of less than 500 micrometers contained in the mixture is obtained;(b) applying a process for the physical separation of inorganic substances;(c) reducing the moisture content until a water content of between 25 and 55 wt. % is reached.12. Process according to claim 11 , characterised in that it comprises a pre-treatment to the aqueous mixture of carbonised biomass claim 11 , wherein said pre-treatment in turn comprises:(a) a first grinding of the aqueous mixture of carbonised biomass until a mean size of less than 5 mm of particles is obtained;(b) a first separation of inorganic substances;(c) a first dehydration step until a water content of less than 50 wt. %. is obtained.13. Process according to claim 11 , characterised in that it comprises an additional step of mixing and metering in at least one chemical dispersant in a percentage less than 3 ...

Increasing Combustibility of Low BTU Natural Gas

A system and methods for increasing a combustibility of a low BTU natural gas are provided herein. The method includes increasing the adiabatic flame temperature of the low BTU natural gas using heavy hydrocarbons, wherein the heavy hydrocarbons include compounds with a carbon number of at least two. The method also includes burning the low BTU natural gas in a gas turbine. 1. A method for increasing a combustibility of a low BTU natural gas , comprising:increasing an adiabatic flame temperature of the low BTU natural gas using heavy hydrocarbons, wherein the heavy hydrocarbons comprise compounds with a carbon number of at least two; andburning the low BTU natural gas in a gas turbine.2. The method of claim 1 , comprising increasing the adiabatic flame temperature of the low BTU natural gas by spiking the low BTU natural gas with the heavy hydrocarbons.4. The method of claim 3 , wherein recovering the portion of the heavy hydrocarbons from the carbon dioxide removal process comprises cryogenically separating carbon dioxide from the low BTU natural gas via a controlled freeze zone (CFZ) process.5. The method of claim 1 , comprising:generating hydrogen from the heavy hydrocarbons via a pressure swing reforming process; andfeeding the hydrogen into the gas turbine, wherein the hydrogen increases the adiabatic flame temperature of the low BTU natural gas within the gas turbine.6. The method of claim 1 , comprising increasing the adiabatic flame temperature of the low BTU natural gas by spiking the low BTU natural gas with hydrogen.7. The method of claim 1 , comprising:removing hydrogen sulfide from the low BTU natural gas;generating hydrogen from the hydrogen sulfide; andspiking the low BTU natural gas with the hydrogen by feeding the hydrogen into the gas turbine.8. The method of claim 7 , comprising generating the hydrogen from the hydrogen sulfide via thermolysis or electrolysis claim 7 , or any combination thereof.9. The method of claim 7 , comprising removing the ...

Multistaged Lean Prevaporizing Premixing Fuel Injector

A multistaged lean prevaporizing premixing fuel injector apparatus is provided. The fuel injector may be utilized with a turbogenerator. Preheated combustion air from the turbogenerator's recuperator may be utilized by the fuel injector to prevaporize liquid fuel. The injector may provide for premixing of multiple fuel streams and include multiple stages with a flow distributor plate separating adjacent stages. The injector may include multiple stages, with a pilot tube located in a final stage splitting the fuel stream into a premixed pilot stream and a premixed final fuel and air mixture stream. 1. A multistaged lean prevaporizing premixing fuel injector apparatus for mixing multiple fuels , comprising:a preliminary prevaporizing premixing chamber having a central longitudinal axis and having an inlet end, and having a preliminary air inlet for introducing air into the preliminary prevaporizing premixing chamber;a final prevaporizing premixing chamber communicated with and downstream of the preliminary prevaporizing premixing chamber, and having a final air inlet for introducing air into the final prevaporizing premixing chamber, the final prevaporizing premixing chamber having an outlet end;a liquid fuel nozzle arranged to project a spray of a liquid first fuel into the preliminary prevaporizing premixing chamber;a second fuel inlet communicated with the preliminary prevaporizing premixing chamber for introducing a second fuel into the preliminary prevaporizing premixing chamber;a common air supply passage for communicating a common combustion air source to both the preliminary air inlet and the final air inlet at substantially the same temperature; anda final flow distributor located upstream of the final prevaporizing premixing chamber for distributing a fuel-air mixture of the first and second fuels and air across a cross-section of the final prevaporizing premixing chamber.2. The fuel injector apparatus of claim 1 , further comprising:an intermediate ...

ENGINE USING HEATED AND TURBO-EXPANDED AMMONIA FUEL

An energy extraction system according to an exemplary embodiment of this disclosure, among other possible things includes an ammonia fuel storage tank assembly that is configured to store a liquid ammonia fuel, a thermal transfer assembly that is configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel, a turbo-expander that is configured to expand the vaporized ammonia based fuel to extract work, and an energy conversion device that is configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output. 1. An energy extraction system , comprising:an ammonia fuel storage tank assembly configured to store a liquid ammonia fuel;a thermal transfer assembly configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel;a turbo-expander configured to expand the vaporized ammonia based fuel to extract work; andan energy conversion device configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output.2. The energy extraction system as recited in claim 1 , further comprising a liquid pump configured to increase a pressure of the liquid ammonia fuel to a pressure greater than a pressure of the liquid ammonia fuel in the ammonia fuel storage tank.3. The energy extraction system as recited in claim 1 , wherein the ammonia fuel storage tank assembly is configured to store the liquid ammonia fuel under a temperature and pressure that is different than an ambient temperature and pressure.4. The energy extraction system as recited in claim 1 , whereinthe energy conversion device includes a combustor, andthe vaporized ammonia based fuel is mixed with air and ignited in the combustor to generate a high energy exhaust gas flow that is expanded through a turbine.5. The energy extraction system as recited in claim 4 , wherein the turbo-expander is coupled to drive a compressor in flow communication with the combustor claim 4 , the compressor pressurizing air to be ...

POWER TURBINE SYSTEM

The power turbine system includes two power turbines communicating with an ion transport membrane (ITM) reactor. Heavy liquid fuel is atomized and burned within the reactor to drive the first turbine, with the first turbine producing useful power. Exhaust from the first turbine is recycled back into the reactor. The reactor includes a series of concentric cylindrical ion transport membranes that separate atmospheric and exhaust gases into suitable components for combustion therein, with at least some of the gases being “cracked” to alter their molecular structure for further combustion to power the second turbine. The second turbine drives a compressor to supply air to the reactor. At least one of the ITMs precludes atmospheric nitrogen from the combustion processes, with the resulting exhaust including pure water and carbon dioxide. The carbon dioxide is either recycled into the reactor to facilitate fuel atomization, or compressed for sequestration. 1. A power turbine system , comprising:a multi-stage ion transport membrane reactor, the multi-stage ion transport membrane reactor having a plurality of mutually concentric cylindrical ion transport membranes therein, the membranes defining corresponding working chambers therebetween, and a centrally disposed button cell ion transport membrane; andat least one power turbine communicating with the reactor.2. The power turbine system according to claim 1 , further comprising:{'sub': 2', '2, 'a first power turbine communicating with the reactor, the first power turbine being driven by a first exhaust product produced by combustion of a heavy liquid fuel within the reactor, the first exhaust product including carbon dioxide (CO) and water (HO);'}{'sub': 2', '2, 'a second power turbine communicating with the reactor, the second power turbine being driven by a second exhaust product comprising a synthetic gas produced within the reactor, the second exhaust product including carbon dioxide (CO) and water (HO); and'}an air ...

BASELOAD EFFICIENCY IMPROVEMENT BY USING CHILLED WATER IN EVAPORATIVE COOLER IN LNG APPLICATION

A heat exchange circuit in a gas turbine includes an evaporative cooling medium circuit circulating an exchange medium, and a cooling source containing fuel. The cooling source is coupled with a supply line in a heat exchange relationship with the evaporative cooling medium circuit. The exchange medium is cooled by the fuel in the supply line, and the evaporative cooling medium circuit directs the cooled exchange medium through the evaporative cooler. The fuel is heated by the evaporative cooling medium circuit, and the supply line directs the heated fuel to the one or more combustors of the gas turbine. The cooler turbine inlet air results in increased baseload output. 1. A heat exchange circuit in a gas turbine , the gas turbine including a compressor , one or more combustors , a turbine , and an evaporative cooler that conditions air input to the one or more combustors , the heat exchange circuit comprising:an evaporative cooling medium circuit circulating an exchange medium; anda cooling source containing fuel, the cooling source being coupled with a supply line in a heat exchange relationship with the evaporative cooling medium circuit,wherein the exchange medium is cooled by the fuel in the supply line, the evaporative cooling medium circuit directing the cooled exchange medium through the evaporative cooler, and wherein the fuel is heated by the evaporative cooling medium circuit, the supply line directing the heated fuel to the one or more combustors of the gas turbine.2. A heat exchange circuit according to claim 1 , wherein the exchange medium is water at ambient temperature.3. A heat exchange circuit according to claim 2 , wherein the evaporative cooling medium circuit comprises a pump to circulate the water.4. A heat exchange circuit according to claim 1 , wherein the fuel comprises liquefied natural gas.5. A heat exchange circuit according to claim 4 , wherein the cooling source comprises a supply of liquefied natural gas stored under pressure in a ...

Hydrogen Hybrid Cycle System

A hydrogen hybrid cycle system configured to convert heat into mechanical work by burning a H2 and an O2. The hydrogen hybrid cycle system comprises a H2 source, an O2 source, a combustion chamber, a first steam injected gas turbine, a load, a heat recovery steam generator and a water pump. The H2 source provides the H2 to the combustion chamber. The O2 source provides the O2 to the combustion chamber. The combustion chamber burns portions of the H2 and the O2. The hydrogen hybrid cycle system burns the H2 and the O2 at or near stoichiometry in the combustion chamber. The hydrogen hybrid cycle system cools the combustion chamber with at least one of a cooling steam and a water. 1. A hydrogen hybrid cycle system configured to convert heat into mechanical work by burning a H2 and an O2 , wherein:said hydrogen hybrid cycle system comprises a H2 source, an O2 source, a combustion chamber, a first steam injected gas turbine, a load, a heat recovery steam generator and a water pump;said H2 source provides said H2 to said combustion chamber;said O2 source provides said O2 to said combustion chamber;said combustion chamber burns portions of said H2 and said O2;said hydrogen hybrid cycle system burns said H2 and said O2 at or near stoichiometry in said combustion chamber;said hydrogen hybrid cycle system cools said combustion chamber with at least one of a cooling steam and a water;said combustion chamber creates a generated steam;said generated steam turns said first steam injected gas turbine; andsaid first steam injected gas turbine is coupled said load.2. The hydrogen hybrid cycle system from claim 1 , wherein:said H2 source comprises liquid hydrogen or hydrogen stored in gaseous phase under high pressure or at ambient pressure;said H2 is stored in a containment selected among cylinders, geological storage, indirect form, or as a byproduct of industrial process;said hydrogen hybrid cycle system further comprises a hydrogen pump;said hydrogen pump is configured to deliver ...

Fuel nozzle assembly with removable components

A fuel nozzle assembly ( 10 ) is presented for a gas turbine engine ( 12 ). The fuel nozzle assembly ( 10 ) includes a rocket unit ( 14 ) and a swirler ( 16 ) with an aft end ( 18 ) in threaded engagement with a forward end ( 20 ) of the rocket unit ( 14 ). The fuel nozzle assembly ( 10 ) may include an oil tip ( 36 ) including a clocking feature with a mechanical constraint to orient the oil tip ( 36 ) at a predetermined angular orientation ( 42 ) relative to the swirler ( 16 ). The fuel nozzle assembly ( 10 ) may include one or more gas stage inlets ( 13, 15 ), one or more oil stage inlets ( 17, 19 ), and a flexible hose ( 26 ) to direct the oil to a plurality of rocket units ( 14 ).

GASIFICATION APPARATUS, CONTROL DEVICE, INTEGRATED GASIFICATION COMBINED CYCLE, AND CONTROL METHOD

A gasification apparatus for gasifying a carbonaceous feedstock to produce raw syngas includes a gasifier in which the raw syngas flows, a heat exchanger provided inside the gasifier downstream to exchange heat with the raw syngas, a hanger pipe through which a part of water supplied from a water supply passage flows to support a load of the heat exchanger, a heat exchanger inflow passage configured to cause the water flowing out from the hanger pipe to flow to an inflow side of the heat exchanger, a bypass passage branching from the water supply passage to cause a remaining of the water supplied to the hanger pipe, a bypass valve provided in the bypass passage, and a control device configured to control, depending on a gasifier load, an opening degree of the bypass valve to adjust the water supplied to the hanger pipe and the bypass passage. 1. A gasification apparatus for gasifying a carbonaceous feedstock to produce raw syngas , the gasification apparatus comprising:a gasifier in which the raw syngas flows;a heat exchanger provided inside the gasifier on a downstream side where the raw syngas flows to exchange heat with the raw syngas;a hanger pipe through which at least a part of water supplied from a water supply passage flows, the hanger pipe being configured to support a load of the heat exchanger;a heat exchanger inflow passage configured to cause the water flowing out from the hanger pipe to flow to an inflow side of the heat exchanger;a bypass passage branching from the water supply passage to cause a remaining of the water supplied to the hanger pipe to flow through the heat exchanger inflow passage;a bypass valve provided in the bypass passage; anda control device configured to control, depending on a gasifier load that is a load in the gasifier, an opening degree of the bypass valve to adjust an amount of the water supplied to the hanger pipe and the bypass passage.2. The gasification apparatus according to claim 1 , whereinthe control device is ...

Recovering base oil from contaminated invert emulsion fluid for making new oil-/synthetic-based fluids

Base oil can be recovered from contaminated O/SBF by combining a chemical process with a mechanical process. The chemical treatment includes adding a demulsifier, an anionic surfactant, a non-ionic surfactant and/or a mutual solvent to the contaminated O/SBF in an amount effective to separate the base oil from the contaminated O/SBF fluid followed by mechanical separation of oil from water, and optionally from any solids present. The recovered base oil (i.e. conventional drilling fluid, conductive drilling fluid and constant rheology drilling fluid, etc.) may then be reformulated to make a new OBM of the same type from which the base oil was recovered, or as a fuel for engines.

SYSTEM AND METHOD FOR COMBUSTING LIQUID FUEL IN A GAS TURBINE COMBUSTOR

A combustion system includes a head end comprising a liquid fuel cartridge. The liquid fuel cartridge has liquid fuel injection ports and is configured to produce combustion products via a diffusion flame. A liner is configured to deliver the combustion products from the head end to an aft frame, and an injector having an outlet is located along the liner between the head end and the aft frame. The injector outlet delivers a stream of oxidant inwardly into the liner, such that a mixedness and a velocity of the combustion products are increased prior to the combustion products reaching the aft frame. A method of producing combustion products having characteristics of a premixed flame in a liquid fuel combustion system is also provided herein. 1. A combustion system comprising:a head end comprising a liquid fuel cartridge having a plurality of liquid fuel injection ports and being configured to produce combustion products via a diffusion flame;a liner configured to deliver the combustion products from the head end to an aft frame; andan injector having an outlet located along the liner between the head end and the aft frame;wherein the injector outlet delivers a stream of oxidant into the liner, such that a mixedness and a velocity of the combustion products are increased prior to the combustion products reaching the aft frame.2. The combustion system of claim 1 , further comprising: a cap separating the head end from the liner; and wherein liquid fuel cartridge comprises a cartridge tip claim 1 , the cartridge tip extending through and downstream of the cap.3. The combustion system of claim 2 , further comprising a bundled tube fuel nozzle including an array of mixing tubes claim 2 , each tube having an inlet end through which air is directed and an outlet end disposed through the cap; the bundled tube fuel nozzle being radially outward of the liquid fuel cartridge.4. The combustion system of claim 3 , wherein the cartridge tip extends axially downstream of the ...

FUEL ADDITIVE INJECTION SYSTEM AND METHODS FOR INHIBITING COKE FORMATION

A turbine engine comprising includes at least one combustor, a liquid fuel supply system, and a fuel additive injection system. The combustor is configured to combust liquid fuel. The liquid fuel supply system is configured to channel liquid fuel through at least one fuel line to the at least one combustor. The fuel additive injection system is coupled in fluid communication with the liquid fuel supply system. The fuel additive injection system includes a recirculation circuit configured to recirculate at least a portion of liquid fuel to the liquid fuel supply system. The fuel additive injection system is configured to channel chemical additive through the recirculation circuit for mixing with the at least a portion of liquid fuel to generate an additive fuel mixture configured to inhibit coke formation in the liquid fuel supply system. 1. A liquid fuel supply system comprising:a stop valve;a liquid fuel pump coupled downstream and in fluid communication with said stop valve, said liquid fuel pump configured to channel liquid through said liquid fuel supply system downstream of said stop valve;a control valve coupled downstream and in fluid communication with said liquid fuel pump; anda fuel additive injection system comprising a recirculation circuit configured to recirculate at least a portion of liquid fuel to said liquid fuel supply system, said recirculation circuit comprising a first fluid line coupled in flow communication with said control valve and a second fluid line coupled in fluid communication with and between said stop valve and said liquid fuel pump, said fuel additive injection system channels chemical additive through said recirculation circuit for mixing with the at least a portion of liquid fuel to generate an additive fuel mixture configured to inhibit coke formation in said liquid fuel supply system.2. The liquid fuel supply system in accordance with claim 1 , wherein said fuel additive injection system further comprises:a chemical additive ...

COMBUSTION DEVICE AND GAS TURBINE ENGINE SYSTEM

A combustion device burns fuel ammonia in a combustion chamber using compressed combustion air, and includes a combustion air cooling unit which is configured to cool the combustion air by heat exchange with the fuel ammonia during or before a compression process. 1. A combustion device which burns fuel ammonia in a combustion chamber using compressed combustion air , the combustion device comprising:a combustion air cooling unit which is configured to cool the combustion air by heat exchange with the fuel ammonia during or before a compression process.2. The combustion device according to claim 1 , further comprising:a low pressure compressor which is configured to compress the combustion air; anda high pressure compressor which is configured to further compress the combustion air compressed by the low pressure compressor,wherein the combustion air cooling unit is an intercooler which is configured to cool the combustion air which is discharged from the low pressure compressor and is to be supplied to the high pressure compressor by heat exchange with the fuel ammonia.3. The combustion device according to claim 2 , wherein the intercooler includes:an ammonia cooling unit which is configured to cool the combustion air by heat exchange with the fuel ammonia; anda water cooling unit which is disposed on an upstream side of the ammonia cooling unit in a flow direction of the combustion air and is configured to cool the combustion air by heat exchange with water.4. The combustion device according to claim 1 , wherein the combustion air cooling unit is configured to vaporize the liquefied fuel ammonia by heat exchange with the combustion air and to supply the vaporized fuel ammonia to the combustion chamber.5. The combustion device according to claim 1 , further comprising a distribution mechanism which is configured to distribute a part of the fuel ammonia claim 1 , which is to be supplied to the combustion chamber claim 1 , to the combustion air cooling unit.6. The ...

Cryogenic fuel composition and dual fuel aircraft system

Solid-liquid mixed powder internal combustion engine

一种固液混合式粉末内燃机由风扇、机身、粉末箱、油箱、燃烧室、蓄电池、发电机、消声器、散热器、水箱、控制箱组成。通过智能化微型计算机控制，设备性能稳定、操作方便，输出扭矩大、功效高。本固液混合式粉末内燃机采用生物质粉末与生物质油混合燃烧方式提供动力，可替代使用化石能源的内燃机，为可再生清洁燃料取代化石能源创造了新的途径。

Oil fuel-fired combined power generation facility and method thereof

A light portion is extracted from feed oil by a separation system. The light portion is then subject to a hydrotreatment to obtain impurity-removed fuel oil which is stored in an intermediate tank. A residue of the feed oil after extraction of the light portion is gasified to obtain syngas (H2 gas+CO gas) which is used as basic fuel for power generation in a power generation system. The fuel oil is fed to the power generation system as auxiliary fuel for supplementing the power generation based on the syngas. The power generation system includes a plurality of gas turbines and generators. The number of the gas turbines to be driven by the fuel oil is controlled to adjust the power generation amount depending on demand.

Fuel oxygen conversion unit with a fuel/gas separator

A fuel oxygen conversion unit includes a contactor defining a liquid fuel inlet, a stripping gas inlet and a fuel/gas mixture outlet. The fuel oxygen conversion unit also includes a fuel/gas separator defining a fuel/gas mixture inlet in flow communication with the fuel/gas mixture outlet of the contactor, an axial direction, and a radial direction. The fuel/gas separator includes a separator assembly including a core including a gas-permeable section extending along the axial direction and defining a maximum diameter, the maximum diameter of the gas-permeable section being substantially constant along the axial direction; and a stationary casing, the fuel/gas separator defining a fuel/gas chamber in fluid communication with the fuel/gas mixture inlet at a location inward of the stationary casing and outward of the gas-permeable section of the separator assembly along the radial direction.

Engine

将液态氨供给到燃气轮机发动机(1)的燃烧器(2)，通过使该液态氨燃烧来驱动涡轮(3)。在燃气轮机发动机(1)的排气通路内配置NO X 选择还原催化剂(9)。将液态氨供给到流入压缩机(4)的进入空气中，利用该液态氨来冷却进入空气，并且利用被排出到排气通路内的未燃烧的氨使排气中所含的NO X 在NO X 选择还原催化剂(9)中还原。

BIOFUEL PRODUCT AND OBTAINING PROCESS

Producto biocombustible y proceso de obtención.#La presente invención se refiere a un proceso para la obtención de un biocombustible a partir de una mezcla acuosa de biomasa carbonizada obtenida en un proceso de carbonización hidrotermal de biomasa, caracterizado porque comprende: (a) moler la mezcla acuosa de biomasa carbonizada hasta obtener un tamaño máximo de las partículas contenidas en la mezcla inferior a 500 micrómetros; (b) aplicar un proceso de separación física de inorgánicos; y (c) reducir el contenido de humedad hasta alcanzar un contenido de agua comprendido entre un 25% y un 55% en peso. Es asimismo objeto de la invención el biocombustible obtenido a partir de dicho proceso, así como su uso en distintas aplicaciones. Biofuel product and process for obtaining. # The present invention relates to a process for obtaining a biofuel from an aqueous mixture of carbonized biomass obtained in a process of hydrothermal carbonization of biomass, characterized in that it comprises: (a) grinding the aqueous mixture of carbonized biomass to obtain a maximum size of the particles contained in the mixture of less than 500 micrometers; (b) apply a physical inorganic separation process; and (c) reduce the moisture content until reaching a water content between 25% and 55% by weight. The object of the invention is also the biofuel obtained from said process, as well as its use in different applications.

Exhaust gas treatment system containing volatile organic compounds

本発明は、ガスタービンを用いて揮発性有機化合物含有ガスを処理するシステムにおいて、揮発性有機化合物含有ガスによる発電機部品のダメージを防止するため、揮発性有機化合物含有排ガス濃縮装置をガスタービン装置の圧縮機吐出側と燃焼器の間に設置するよう構成し、濃縮装置の吸着材から揮発性有機化合物を離脱するのに必要な熱は、圧縮機の断熱圧縮による圧縮の過程で昇温した空気を用いる。揮発性有機化合物含有ガスは圧縮機の吐出側からタービンシステムに取り込まれるため発電機等の圧縮機吸気側に連なる機器にもれることはなく、これらの機器にダメージを与えない。 The present invention relates to a gas turbine apparatus in which a volatile organic compound-containing exhaust gas concentrating device is used in a system for processing a volatile organic compound-containing gas using a gas turbine in order to prevent damage to generator parts due to the volatile organic compound-containing gas. The heat required to remove volatile organic compounds from the adsorbent of the concentrator increased in the process of compression by adiabatic compression of the compressor. Use air. Since the volatile organic compound-containing gas is taken into the turbine system from the discharge side of the compressor, it does not leak to equipment connected to the compressor intake side, such as a generator, and does not damage these equipment.

System for vaporization of liquid fuels for combustion and method of use

대기에 대해 산소 농도가 낮은 가스 스트림이 액체 연료 또는 액화 탄화수소 가스를 기화시키기 위해 사용되거나, 기화 가스와 혼합되며, 저산소 기화 연료 가스는 예비혼합 또는 확산 연소기와 같은 연소 장치에 공급된다. 가스 스트림의 산소 농도는 한계 산소 지수 미만이 바람직하다. 연료를 적절하게 낮은 산소 함량을 갖는 가스 스트림과 혼합함으로써, 화염 전방 이전의 자동 점화가 방지될 수 있다. 일부 실시예에서는, 저산소 스트림이 공기 분리기로부터 발생되거나, 연소 장치의 배기로부터 취해진다. A gas stream with a low oxygen concentration to the atmosphere is used to vaporize the liquid fuel or the liquefied hydrocarbon gas, or is mixed with the vaporization gas, and the low oxygen vaporization fuel gas is supplied to a combustion device such as a premix or diffusion combustor. The oxygen concentration of the gas stream is preferably below the limit oxygen index. By mixing the fuel with a gas stream with an appropriately low oxygen content, automatic ignition before flame forward can be prevented. In some embodiments, a low oxygen stream is generated from the air separator or taken from the exhaust of the combustion device.

Fuel injector with purged insulating air cavity

一种燃料喷射器(30)，其包括纵向延伸通过所述燃料喷射器的用于使燃料空气混合物流至燃烧室(50)的流路。所述燃料喷射器还可包括至少部分地环绕所述流路的液态燃料通道(56)。所述通道可包括构造成将液态燃料从所述通道传送至所述流路的多个燃料支路(54a-54e)。所述燃料喷射器还可包括环形外壳(47)，所述环形外壳围绕所述通道周向地设置以形成至少部分地围绕所述通道的隔离空气腔(60)。所述外壳可包括至少一个吹扫孔(62a，62b，62c)以提供所述隔离空气腔与所述喷射器的所述外壳的外部之间的连通。

Systems and methods for power generation using partial oxidation

본 발명은 연료 가스를 포함하는 부분적으로 산화된 스트림을 형성하기 위해 고체 또는 연료의 부분 산화를 이용하여 고효율의 동력 생산을 구현하도록 조정되는 동력 생산 시스템에 관한 것이다. 이러한 연료 가스 스트림은 연소 연료로서 동력 생산 시스템의 연소기로 안내되기 전에 급랭되고, 여과되며, 냉각되는 것의 하나 또는 그 이상에 해당될 수 있다. 상기 부분 산화된 스트림은 압축된 재순환 CO 2 스트림 및 산소와 결합된다. 상기 연소 스트림은 동력을 생성하도록 터빈에 걸쳐 팽창되고, 레큐퍼레이터 열교환기로 통과된다. 상기 팽창되고 냉각된 배출 스트림은 상기 재순환 CO 2 스트림을 제공하도록 더 처리될 수 있으며, 이는 상기 결합된 시스템들에 대해 증가된 효율을 제공하기에 유용한 방식으로 압축되고, 하나 또는 그 이상의 레큐퍼레이터 열교환기들로 통과된다. The present invention relates to a power production system adapted to achieve high efficiency power production using partial oxidation of solids or fuel to form a partially oxidized stream comprising fuel gas. This fuel gas stream may be one or more of quenched, filtered and cooled before being directed to the combustor of the power production system as combustion fuel. The partially oxidized stream is combined with a compressed recycle CO 2 stream and oxygen. The combustion stream is expanded across the turbine to generate power and passed to a recuperator heat exchanger. The expanded and cooled effluent stream may be further processed to provide the recycle C0 2 stream, which is compressed in a manner useful to provide increased efficiency for the combined systems, and one or more recuperators. passed through the heat exchangers.

System and method for power production using partial oxidation

The present disclosure relates to a power production system that is adapted to achieve high efficiency power production using partial oxidation of a solid or liquid fuel to form a partially oxidized stream that comprises a fuel gas. This fuel gas stream can be one or more of quenched, filtered, and cooled before being directed to a combustor of a power production system as the combustion fuel. The partially oxidized stream is combined with a compressed recycle CO 2 stream and oxygen. The combustion stream is expanded across a turbine to produce power and passed through a recuperator heat exchanger. The expanded and cooled exhaust stream can be further processed to provide the recycle CO 2 stream, which is compressed and passed through one or more recuperator heat exchangers in a manner useful to provide increased efficiency to the combined systems.

Polished turbine fuel

所提供的涡轮机燃料适于由公用设施用于生产电力和淡化水的大规模基于陆地的涡轮机，并且适用于仅有液体燃料可用时船舶和远程应用中的大型移动式引擎和涡轮机。与燃烧受污染的重质原油、炼油厂残油或高硫燃油相比，使用导致减少的腐蚀、灰烬形成和排放(NOx、Sox、CO 2 和有害金属)。制造是通过将原油、非常规原油和其它高度污染的液体，诸如炼油厂残油和高硫燃油，去污染。使用比常规原油精炼更简单的装置配置，每种燃料作为单元操作的单一产物生产，而不是各种炼油厂产物的工厂前混合物。这些燃料可以由具有热流路径和易受腐蚀的热回收蒸汽发生系统的联合循环发电厂的先进高效涡轮机系统燃烧，否则该系统不能使用受污染的重质原油或炼油厂残油。

System and method for power production using partial oxidation

The invention describes a power production system that is adapted to achieve high efficiency power production using partial oxidation of a solid or liquid fuel to form a partially oxidized stream that comprises a fuel gas. This fuel gas stream can be one or more of quenched, filtered, and cooled before being directed to a combustor of a power production system as the combustion fuel. The partially oxidized stream is combined with a compressed recycle CO2 stream and oxygen. The combustion stream is expanded across a turbine to produce power and passed through a recuperator heat exchanger. The expanded and cooled exhaust stream can be further processed to provide the recycle CO2 stream, which is compressed and passed through one or more recuperator heat exchangers in a manner useful to provide increased efficiency to the combined systems.

METHOD FOR OPERATING A GAS TURBINE INVOLVING THE COMBUSTION OF VANADIUM CONTAMINATED LIQUID FUEL

L'invention a pour objet un procédé d'exploitation d'une turbine à gaz impliquant la combustion d'un combustible liquide contaminé au vanadium, le procédé étant caractérisé en ce qu'il comprend : A) une étape d'introduction dans le système de combustion d'un premier oxyde qui est l'oxyde de magnésium et d'au moins un second oxyde choisi parmi Al2O3, Fe2O3, TiO2 et SiO2, le rapport m du nombre de moles de MgO au nombre de moles de V2O5 et le rapport a du nombre total de mole de second(s) oxyde(s) au nombre de moles de V2O5 satisfaisant aux deux conditions : a + 3 < m < 15, et (ii) [1/(1 + K)] (m - 2) ≤ a ≤ [10/(10 + K)] (m - 2) K étant défini par la relation : K= MV * HK * e(-0,0056*T), où : - T désigne la température de flamme de la turbine à gaz, en Kelvin, - MV et HK désignent respectivement: la masse volumique moyenne, définie à la température ambiante, et la dureté Knoop moyenne, définie par la norme ASTM E384 et mesurée à la température ambiante, des oxydes doubles formés par la réaction entre l'oxyde de magnésium et le(s) second(s) oxyde(s), et B) au moins une étape de nettoyage de la pièce chaude à l'aide d'un agent nettoyant comprenant un liquide vecteur et au moins un matériau décapant spécifique qui est en suspension dans ledit liquide vecteur. The invention relates to a method of operating a gas turbine involving the combustion of a liquid fuel contaminated with vanadium, the method being characterized in that it comprises: A) a step of introduction into the system for combusting a first oxide which is magnesium oxide and at least one second oxide selected from Al2O3, Fe2O3, TiO2 and SiO2, the ratio m of the number of moles of MgO to the number of moles of V2O5 and the ratio a of the total number of moles of second oxide (s) to the number of moles of V2O5 satisfying the two conditions: a + 3 <m <15, and (ii) [1 / (1 + K)] (m - 2) ≤ a ≤ [10 / (10 + K)] (m - 2) K being defined by the relation: K = ...

LIQUID FUEL SUPPLY SYSTEMS FOR A COMBUSTION SYSTEM, IN PARTICULAR A GAS TURBINE, COMPRISING A DEVICE FOR GENERATING AN EMULSION AND FOR DISTRIBUTING THE FLOW OF EMULSION

Système d'alimentation en combustible liquide (12) pour un système à combustion (14), notamment d'une turbine à gaz, comprenant au moins un réservoir de stockage (16) de combustible liquide apte à alimenter au moins un injecteur (34) relié à une chambre de combustion (32) du système à combustion (14), ledit système d'alimentation (12) comprenant une première section de tuyauterie (18) disposée en aval du réservoir (16) et une deuxième section de tuyauterie (20) disposée en aval de la première section de tuyauterie (18) et en amont dudit injecteur (34), ladite première section de tuyauterie (18) comprenant au moins un moyen de mise sous pression (22), et au moins un point d'injection ou entrée (24) d'un produit hydrosoluble, et la deuxième section de tuyauterie (20) comprenant un dispositif (26) de mélange et de répartition de débit configuré pour créer une émulsion et répartir le débit d'émulsion vers au moins un conduit (28) relié audit injecteur (34). La deuxième section de tuyauterie comprend un dispositif de mélange et de répartition de débit et le régime en amont dudit dispositif est configuré pour créer une émulsion et répartir le débit d'émulsion vers au moins un conduit relié audit injecteur. Liquid fuel supply system (12) for a combustion system (14), in particular a gas turbine, comprising at least one liquid fuel storage tank (16) able to supply at least one injector (34) connected to a combustion chamber (32) of the combustion system (14), said supply system (12) comprising a first section of pipe (18) disposed downstream of the tank (16) and a second section of pipe (20 ) disposed downstream of the first pipe section (18) and upstream of said injector (34), said first pipe section (18) comprising at least one pressurizing means (22), and at least one point of injection or inlet (24) of a water-soluble product, and the second section of piping (20) comprising a mixing and flow distribution device (26) configured to create an ...

GAS TURBINE COMPARTMENT COMPRISING A HOT AIR LEAK DETECTION DEVICE AND METHOD OF DETECTING HOT AIR LEAK DETECTION

Reduced pollution power generation system and gas generator therefore

Pollution-free or low pollution, efficient, large scale electrical power generation systems, using thermal energy from combustion of hydrocarbon fuel are described herein. The pollutant-free hydrocarbon fuel is combusted in a gas generator with pure oxygen or substantially pure oxygen that is free of nitrogen. Water is also injected into the gas generator. The gas generator discharges high enthalpy steam and carbon dioxide which can then be utilized in a variety of applications, including driving turbines for power generation. The steam can be recycled into the gas generator or discharged for various uses. The carbon dioxide can be collected for industrial use or discharged.

GAS TURBINE COMPARTMENT COMPRISING A HOT AIR LEAK DETECTION DEVICE AND METHOD OF DETECTING HOT AIR LEAK DETECTION

Compartiment de turbine à gaz comprenant une turbine à gaz apte à être alimentée alternativement par un combustible liquide et par un combustible gazeux, et comprenant un compresseur (13) comportant un arbre de rotor (14), une chambre de combustion (16) et apte à recevoir l'air comprimé par le compresseur et une turbine (17) entraînée par des gaz chauds à haute énergie provenant de la chambre de combustion, ledit compartiment de turbine à gaz comprenant un dispositif (22) de détection de fuites d'air chaud dans le compartiment de turbine (10). Le dispositif (22) de détection de fuites d'air chaud dans le compartiment de turbine (10) calcule une valeur de température attendue dans le compartiment de turbine (10) et détecte une fuite d'air chaud en fonction de ladite valeur de température attendue dans le compartiment de turbine. Gas turbine compartment comprising a gas turbine capable of being fed alternately with a liquid fuel and with a gaseous fuel, and comprising a compressor (13) comprising a rotor shaft (14), a combustion chamber (16) and suitable receiving compressed air by the compressor and a turbine (17) driven by high energy hot gases from the combustion chamber, said gas turbine compartment including a hot air leak detection device (22) in the turbine compartment (10). The hot air leak detection device (22) in the turbine compartment (10) calculates an expected temperature value in the turbine compartment (10) and detects a hot air leak according to said temperature value. expected in the turbine compartment.

PROCESS FOR IMPLEMENTING BI-METALLIC ADDITIVES FOR INHIBITING VANADO CORROSION IN GAS TURBINES

Patent FR2299756B1

Multiple fuel power station uses synthetic and conventional fuels to supply turbine or thermal engine

The multi-fuel power station includes either a gas turbine or a combustion engine running on multiple fuels, powering an alternator to generate electricity from the cheapest fuel available at a particular time. The electric power station comprises at least one dual fuel thermal engine (D). This may be a gas turbine or a combustion engine which is able to be fuelled by one or several fuels (C). These are selected according to price. The output from this turbine or engine is applied to an electrical generator (E), producing a power of between 1 and 10 MW. The fuels used may be synthetic fuels (A) or conventional fuels (B). The synthetic fuels may be formed by a pyrolysis and gasification of industrial or agro-chemical waste. The waste may include old tyres, oils, plastic materials sludge and/or biomass. The conventional fuels may be derived from refining petroleum.

System for vaporization of liquid fuels for combustion and method of use

Gas turbine fuel system comprising fuel oil distribution control system, fuel oil purge system, purging air supply system, and fuel nozzle wash system

Plurality of fuel nozzles X1 and X2 in combustor X are supplied with fuel gas from fuel gas system and fuel oil from fuel oil system, respectively. Gas turbine operation is done with fuel being changed over to either gas or oil. Fuel oil distribution control system A controls oil flowing into plurality of fuel pipings. When oil is changed over to gas, fuel oil purge system B is supplied with air of appropriate temperature and pressure from purging air supply system C. This air flows into fuel oil pipings and nozzles X2 for purging residual oil therein. Fuel nozzle wash system D is supplied with water by-passing from wash water tank for compressor washing. This water flows through nozzles X2 for washing thereof.

Injector of an over-enriched fuel-and-air mixture to the combustion chamber of internal combustion engines

A fuel injector for injecting an over-enriched fuel and air mixture to the combustion chamber of an internal combustion engine includes a spray nozzle, a gaseous carrier, a fuel mixing and evaporation chamber and an injector nozzle. During operation, both a liquid fuel and the gaseous carrier are supplied to the fuel mixing and evaporation chamber of the injector through the spray nozzle, where they are mixed and evaporated as a result of elevated temperature, and the mixture reaches the combustion chamber. The gaseous carrier is air or, flue gas, at elevated pressure and temperature and having a composition that prevents the initiation of flame combustion, and the gaseous carrier has an oxygen content low enough to prevent the initiation of combustion, even under conditions of elevated pressure and temperature.

Increasing combustibility of low btu natural gas

A system and methods for increasing a combustibility of a low BTU natural gas are provided herein. The method includes increasing the adiabatic flame temperature of the low BTU natural gas using heavy hydrocarbons, wherein the heavy hydrocarbons include compounds with a carbon number of at least two. The method also includes burning the low BTU natural gas in a gas turbine.

Engine

A combuster (2) of a gas turbine engine (1) is fed with liquid ammonia and that liquid ammonia is burned to drive a turbine (3). Inside the exhaust passage of the gas turbine engine (1), an NO x selective reduction catalyst (9) is arranged. Inside the intake air which flows into the compressor (4), liquid ammonia is fed. This liquid ammonia is used to cool the intake air. The NO x which is contained in the exhaust gas is reduced by the unburned ammonia which is exhausted into the exhaust passage by the NO x selective reduction catalyst (9).

System and apparatus for delivering fuel to a turbine engine

Engine

将液态氨供给到燃气轮机发动机(1)的燃烧器(2)，通过使该液态氨燃烧来驱动涡轮(3)。在燃气轮机发动机(1)的排气通路内配置NO X 选择还原催化剂(9)。将液态氨供给到流入压缩机(4)的进入空气中，利用该液态氨来冷却进入空气，并且利用被排出到排气通路内的未燃烧的氨使排气中所含的NO X 在NO X 选择还原催化剂(9)中还原。

Combustion apparatus and gas turbine

本发明的燃烧装置(C)使燃料用氨和燃烧用空气在燃烧室(N)内燃烧，且具备：形成燃烧室的燃烧器衬套(3a)；安装于燃烧器衬套的一端的喷烧器(3c)；在燃烧气体的流动方向上设于比燃烧器衬套靠下游侧且使燃烧气体的流动方向偏向的偏向部件(3g)；以及设于喷烧器与偏向部件的出口之间且将燃料用氨供给至燃烧室的内部的至少一个氨喷射孔(3b)。

Eductor fuel purging system for a turbomachine

A system includes a fuel premixer configured to distribute a fuel to a combustor and a purge system (40) configured to purge the fuel from the fuel premixer. The purge system (40) includes a discharge line (50) configured to receive a flow of a purge mixture (70) from the fuel premixer. The purge system (40) includes an orifice (72) coupled to the discharge line (50) and an eductor (46) having an interior (76), an opening (56), and an outlet (78). The orifice (72) is configured to constrict the flow of the purge mixture (70). The interior (76) is fluidly coupled to the orifice (72), to the opening (56), and to the outlet (78). The purge mixture (70) is configured to flow through the interior (76) from the orifice (72) to the outlet (78), the flow of the purge mixture (70) through the orifice (72) is configured to draw coolant (79) into interior (76) of the eductor (46) through the opening (56), and the coolant (79) drawn through the opening (56) is configured to mix with the purge mixture (70).

Electricity generation method and device using combustion of fossil fuels and having zero-carbon emission

A electricity generation method and device using combustion of fossil fuels and having zero-carbon emission provide a complete technical solution of carbon capture and storage (CCS): electricity is generated by carrying out oxygen-enriched combustion of coal and other fossil fuels in an electricity plant at a carbon dioxide sequestration location, and the produced carbon dioxide is introduced, in an onsite manner, into a saline aquifer at the carbon dioxide sequestration location, and the generated electricity is outputted outside. By means of the method, the whole transportation process comprising loading, long-distance transportation and unloading of coal is omitted, so that the difficulty and cost for implementing the complete CCS technical solution are greatly reduced, the feasibility of the CCS technical solution is improved, the implementation of the large-scale carbon capture and storage during electricity generation based on combustion of coal and other fossil fuels is facilitated, electricity is generated by means of combustion of the fossil fuels while zero-carbon emission is achieved, a technical path is added for breaking through difficulties in CCS, so as to finally implement large-scale comprehensive utilization of a great quantity of coal, oil, gas and other fossil fuels and a large quantity of saline aquifer geological resources.

For starting the method for land-based gas turbine engine

本发明涉及一种用于起动固定式燃气轮机（10）的方法，所述固定式燃气轮机具有至少一个燃烧室（14），所述燃烧室的燃烧器包括引燃燃烧器和主燃烧器并且通过所述引燃燃烧器和主燃烧器将不同的燃料类型引入到燃烧室（14）中以用于燃烧，其中在燃气轮机（10）的转子（18）从停机加速直至额定转速期间执行下述步骤：将第一燃料类型的燃料输送给引燃燃烧器；以及将第一燃料类型的燃料输送给主燃烧器。为了提供在燃料供给系统中需要相对小的供给压力并且在起动期间避免危害机器的燃烧振动的方法而提出，在达到额定转速之前将第二燃料类型的燃料输送给燃烧器。

Processing fuel and water

Fuel is oxidized with air in a pressurized reaction chamber containing water. Water, fuel, or both may be communicated into the reaction chamber in a gaseous state, a liquid state, or both. For example, a liquid mixture that includes the water and/or the fuel can be evaporated to form a gas mixture, and the gas mixture can be communicated into the reaction chamber. Additionally or alternatively, the liquid mixture that includes the water and/or the fuel can be communicated into the reaction chamber and evaporated in the reaction chamber. The water and the fuel may be communicated into the reaction chamber separately or in combination.

Combustion device and gas turbine

Aircraft propulsion system with inter-turbine combustor

提供了一种飞行器推进系统和计算系统。推进系统包括低压(LP)线轴和具有高压(HP)线轴的核心发动机。框架以串行流动布置定位在HP涡轮和LP涡轮之间。框架包括涡轮间燃烧器，该涡轮间燃烧器包括形成进入推进系统的核心流动路径的出口开口的支柱。第一燃料系统被构造为使液体燃料流到燃烧区段以产生第一燃烧气体。第二燃料系统被构造为经由涡轮间燃烧器使气态燃料流到核心流动路径以产生第二燃烧气体。推进系统形成1.5至5.7之间的核心发动机与具有LP线轴的涡轮间燃烧器的额定功率输出比。

Power generation system with reduced pollution and gas generator therefor

(57)【要約】 汚染がないか、または低汚染で、効率的な大規模な電力発生システムであって、炭化水素燃料の燃焼による熱エネルギーを使用する。汚染のない炭化水素燃料がガス発生機内で純粋酸素または窒素を含まない実質的に純粋酸素と燃焼される。また、水がガス発生機内に導入される。ガス発生機は、動力発生のための駆動タービンを有し、各種の分野で利用される高エンタルピーの蒸気と二酸化炭素を放出する。蒸気はガス発生機内で循環されるか、または各種の用途のために放出される。二酸化炭素は、産業上の用途のために集められるか、または放出される。

A kind of conventional submarine AIP system and working method

一种常规潜艇AIP系统及工作方法，该系统包括天然气供应系统、氧气供应系统和二氧化碳跨临界跨流态动力循环系统；本发明还公开了该系统的工作方法，液化天然气和液氧分别经过低温泵加压之后进入冷却系统放出冷量并汽化，然后温度和压力合适的天然气和氧气进入燃烧室中做富氧燃烧，为二氧化碳跨临界跨流态动力循环系统提供热能；二氧化碳跨临界跨流态动力循环运行时汽轮机对外输出机械功，带动发电机输出电能；本发明采用热值大、密度小的液化天然气，可储存的燃料量增加；二氧化碳跨临界跨流态动力循环系统的效率远远超过同条件下现有的热能动力系统，经济性优良；相较于现有AIP系统，本发明大大提高潜艇的水下续航力，减小了暴露率，增加了隐蔽性。

A kind of underwater turbine jet engine

本发明公开了一种水下涡轮喷气发动机，包括：壳体及设置于壳体内的推进剂贮存室、燃烧室及混合室；推进剂贮存室内设置有液氧贮存器和煤油贮存器，液氧贮存器和煤油贮存器均与燃烧室连通，燃烧室与混合室通过燃气管道连通，混合室用于混合高温燃气与水产生水蒸汽混合物，并向后喷出实现推进。通过自身携带的液氧作为助燃，保证了在水下没有空气的情况下依然能够稳定燃烧，设置燃烧室的结构，令液氧和煤油在其内燃烧形成高温燃气，将高温燃气和水导入混合室，产生大量水蒸气，通过将燃气和水蒸气的体积膨胀的共同作用，将二者的混合器向后喷出，实现推进。该设计能够稳定的在全水环境下工作，对周围空气含量等一般制约水下喷气的因素要求较低。

Gas turbine system

A gas turbine system 1 is provided with: an ammonia tank 14; a combustor 13 that is connected to the ammonia tank 14 and that has a combustion chamber 13a; a suction flow channel 41 that is connected to the combustor 13; a compressor 11a that is provided to the suction flow channel 41; a decomposition gas reservoir 17 that is connected to the combustor 13; and an ammonia decomposition catalyst 16 that is provided to a bleed air flow channel 43 connected to the compressor 11a, is provided between the combustor 13 and the compressor 11a in the suction flow channel 41, or is provided in a space connecting the combustion chamber 13a and the suction flow channel 41 in the combustor 13, and that is connected to the ammonia tank 14 and the decomposition gas reservoir 17.

Purging system and purging method for turbine fracturing device group, and turbine fracturing device group

Provided are a purging system (200) for a turbine fracturing device group and a turbine fracturing device group comprising the purging system (200), and also provided is a purging method of the purging system (200). The turbine fracturing device group comprises a plurality of gas turbines (110), and each gas turbine (110) comprises a plurality of fuel supply pipelines (111). The purging system (200) comprises: a first air compressor (210) and a purging pipeline (220), wherein the purging pipeline (220) is communicated with the first air compressor (210) and the plurality of fuel supply pipelines (111) of each gas turbine (110) in the turbine fracturing device group; the first air compressor (210) is configured to supply compressed air to at least some fuel supply pipelines (111), which are stopped from supplying fuel, for purging, in a state that at least some fuel supply pipelines (111) in the plurality of fuel supply pipelines (111) are stopped from supplying the fuel. The purging system can simultaneously purge fuel pipelines and nozzles of a plurality of gas turbines, such that the maintenance by the purging system is more centralized and convenient, and workloads of on-site personnel are reduced.

SYSTEM AND METHOD FOR ENERGY PRODUCTION WITH INTEGRATED HYDROGEN PRODUCTION

В настоящей заявке описаны системы и способы, эффективные для производства энергии. В частности, цикл выработки энергии, в котором в качестве рабочей текучей среды используется CO, может выполняться с одновременным производством водорода. Достоинством такого решения является улавливание, по существу, всего углерода, возникающего при сжигании топлива в установках выработки энергии и производства водорода, в форме диоксида углерода. Кроме того, получаемый водород (дополнительно смешанный с азотом, полученным в установке разделения воздуха) может быть подан в качестве топлива в установку с газовой турбиной комбинированного цикла для дополнительного получения энергии без каких-либо выбросов COв атмосферу. This application describes systems and methods that are efficient for energy production. In particular, a power generation cycle in which CO is used as a working fluid can be performed while simultaneously producing hydrogen. This has the advantage of capturing essentially all of the carbon from fuel combustion in power generation and hydrogen production units in the form of carbon dioxide. In addition, the produced hydrogen (additionally mixed with nitrogen from the air separation unit) can be fed as fuel to the combined cycle gas turbine unit for additional energy production without any CO emissions.

Fuel delivery system and apparatus

Fuel and its manufacturing method

Power turbine system

The power turbine system includes two power turbines communicating with an ion transport membrane (ITM) reactor. Heavy liquid fuel is atomized and burned within the reactor to drive the first turbine, with the first turbine producing useful power. Exhaust from the first turbine is recycled back into the reactor. The reactor includes a series of concentric cylindrical ion transport membranes that separate atmospheric and exhaust gases into suitable components for combustion therein, with at least some of the gases being “cracked” to alter their molecular structure for further combustion to power the second turbine. The second turbine drives a compressor to supply air to the reactor. At least one of the ITMs precludes atmospheric nitrogen from the combustion processes, with the resulting exhaust including pure water and carbon dioxide. The carbon dioxide is either recycled into the reactor to facilitate fuel atomization, or compressed for sequestration.