Настройки

Укажите год
-

Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

Подробнее
-

Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

Подробнее

Форма поиска

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Укажите год
Укажите год
Применить Всего найдено 1467. Отображено 100.
23-02-2012 дата публикации

method and device for feeding a turbomachine combustion chamber with a regulated flow of fuel

Номер: US20120042657A1
Автор: Celine Marie Anne Issert, Laurent Gilbert Yves Hodinot, Pascal Laurent
Принадлежит: SNECMA SAS

High-pressure fuel is supplied at a controlled rate to a combustion chamber via a position-controlled valve and a variable-restriction stop-and-pressurizing cut-off valve. A value representative of the real mass flow rate of fuel as delivered is calculated by a calculation unit on the basis of information representative of the pressure difference between the inlet and the outlet of the cut-off valve and of the flow section through the cut-off valve, e.g. as represented by the position X of the slide of the cut-off valve. The position-controlled valve has a variable position that is controlled by the calculation unit as a function of the difference between the calculated value representative of the real mass flow rate and a value representative of a desired mass flow rate.

Подробнее
Номер записи: 1
19-04-2012 дата публикации

Distributed small engine fadec

Номер: US20120095661A1
Автор: Kevin P. Roy, Thaddeus J. Zebrowski
Принадлежит: Hamilton Sundstrand Corp

A full authority digital engine controller (FADEC) controls an engine attached to an airframe. The FADEC includes an electronic engine controller (EEC) attached to the engine, an airframe data concentrator (ADC) attached to the airframe, and a digital data bus electrically connecting the ADC to the EEC. The ADC is electrically connected to a plurality of airframe sensors to convert the airframe sensor signals to airframe sensor digital data. The digital bus conducts the airframe sensor digital data to the EEC.

Подробнее
Номер записи: 2
11-04-2013 дата публикации

METHOD FOR SWITCHING OVER A COMBUSTION DEVICE

Номер: US20130086918A1
Автор: BOTHIEN Mirko Ruben, PENNELL Douglas Anthony, ZAJADATZ Martin
Принадлежит: ALSTOM Technology Ltd

An exemplary method for switching over a combustion device from operation with a first premix fuel to a second premix fuel includes reducing and stopping a first premix fuel supply and then starting a second premix fuel supply. In an intermediate phase, after the first premix fuel supply stop and before the second premix fuel supply start, the combustion device is operated with one or more pilot fuels generating diffusion flames. 1. A method for switching over a combustion device from operation with a first premix fuel to a second premix fuel comprising:reducing and stopping a first premix fuel supply;operating the combustion device with at least one pilot fuel that generates diffusion flames; andstarting a second premix fuel supply following generation of the diffusion flames.2. The method according to claim 1 , wherein the pilot fuels include first and second pilot fuels claim 1 , which are fed to the combustion device during operation of the combustion device.3. The method according to claim 2 , wherein in an intermediate phase claim 2 , after the first premix fuel supply stops and before the second premix fuel supply starts claim 2 , the combustion device is operated with the at least one pilot fuel generating only diffusion flames.4. The method according to claim 3 , wherein only the first and second pilot fuels support combustion device operation during the intermediate phase.5. The method according to claim 2 , comprising:injecting the first and the second pilot fuels together with the first premix fuel and the second premix fuels.6. The method according to claim 3 , comprising:starting the first pilot fuel supply before the second pilot fuel supply starts.7. The method according to claim 5 , comprising:starting the first pilot fuel supply before the second pilot fuel supply starts.8. The method according to claim 3 , comprising:terminating the first pilot fuel supply before the second pilot fuel supply terminates.9. The method according to claim 5 , ...

Подробнее
Номер записи: 3
18-04-2013 дата публикации

Method and a device for producing a setpoint signal

Номер: US20130091851A1
Автор: Alexandra Riou, Bruno Robert Gaully, Cedrik Djelassi
Принадлежит: SNECMA SAS

A method and device producing a setpoint signal representing a flow rate of fuel that a metering unit having a slide valve is to supply to a fuel injection system of a combustion chamber in a turbine engine, the position of the valve depending on the setpoint signal. The method: obtains a first signal representing a measurement as delivered by a flow meter of a flow rate of fuel injected into the chamber; evaluates a second signal representing the flow rate of fuel injected into the chamber based on a measurement of the position of the valve; estimates a third signal representative of the measurement delivered by the flow meter by applying a digital model of the flow meter to the second signal; and produces the setpoint signal by adding a compensation signal to the first signal, the compensation signal obtained by subtracting the third signal from the second signal.

Подробнее
Номер записи: 4
25-04-2013 дата публикации

Method for Operating a Gas Turbine

Номер: US20130098054A1
Автор: Guethe Felix, Gumprecht-Liebau Meike, STANKOVIC Dragan
Принадлежит: ALSTOM TECHNOLOGY LTD.

In a method for operating a gas turbine (), a CO2-containing gas is compressed in a compressor (), the compressed gas is used to burn a fuel in at least one subsequent combustion chamber (), and the hot combustion gases are used to drive at least one turbine (). Improved control and performance can be achieved by measuring the species concentration of the gas mixture flowing through the gas turbine () at several points within the gas turbine () by a distributed plurality of species concentration sensors (-), and utilizing the measured concentration values to control the gas turbine () and/or optimize the combustion performance of the gas turbine (). 1. A method for operating a gas turbine , in which turbine a CO-containing gas is compressed in a compressor , the compressed gas is used to burn a fuel in at least one subsequent combustion chamber to form hot combustion gases , and the hot combustion gases are used to drive at least one turbine , the method comprising:measuring the species concentration of the gas mixture flowing through the gas turbine at several points within the gas turbine with a distributed plurality of species concentration sensors; andcontrolling the gas turbine, optimizing the combustion performance of said gas turbine, or both, based on the measured species concentration values.2. A method according to claim 1 , wherein measuring comprises:{'sub': '2', 'measuring at least the Oconcentration with said plurality of species concentration sensors.'}3. A method according to claim 1 , wherein said species concentration sensors comprise ZrOsensors.4. A method according to claim 1 , wherein said species concentration sensors consist of ZrOsensors.5. A method according to claim 1 , in which the gas turbine is a sequential-combustion turbine with two combustors claim 1 , two turbines claim 1 , and flue gas recirculation claim 1 , and in which at least part of the flue gas at an exit of the gas turbine is recirculated and enters the compressor after ...

Подробнее
Номер записи: 5
23-05-2013 дата публикации

Method for operating a combustion device during transient operation

Номер: US20130125547A1
Автор: Douglas Anthony Pennell, Martin Zajadatz, Mirko Ruben Bothien
Принадлежит: Alstom Technology AG

A method and apparatus are disclosed for operating a combustion device during a transient operation. The combustion device is fed with at least a fuel. The transient operation includes a period having a period length (T) during which the fuel is fed in an amount lower that a designated (e.g., critical) amount (Mc). A limit value (L) is defined for the period length (T), and fuel feed is regulated to keep the period length (T) smaller or equal to the limit value (L).

Подробнее
Номер записи: 6
13-06-2013 дата публикации

Method for optimizing the control of a free turbine power package for an aircraft, and control for implementing same

Номер: US20130151112A1
Автор: Jean-Michel Haillot
Принадлежит: Turbomeca SA

A method optimizing fuel-injection control with driving speeds of apparatuses adjusted by controlling a turbine speed according to power, and optimizing control of a free turbine power package of an aircraft, including a low-pressure body, supplying power to apparatuses and linked to a high-pressure body. The method varies the low-pressure body speed to obtain a minimum speed for the high-pressure body, so power supplied by the apparatuses remains constant. Power supplied by the apparatuses is dependent upon the apparatuses driven speed by the low-pressure body, and a speed set point of the low-pressure body is dependent upon a maximum value of minimum speeds of the apparatuses, enabling required power to be optimized, upon a positive or zero incrementation added to the speed set point of the low-pressure body to minimize speed of the high-pressure body to the apparatuses power supply.

Подробнее
Номер записи: 7
11-07-2013 дата публикации

Fuel Flow Control Method and Fuel Flow Control System of Gas Turbine Combustor for Humid Air Gas Turbine

Номер: US20130174571A1
Автор: ABE KAZUKI, KOGANEZAWA Tomomi
Принадлежит: Hitachi, Ltd.

Provided is a fuel flow control method of a gas turbine combustor provided in a humid air gas turbine, by which method NOx generation in the gas turbine combustor is restricted before and after the starting of humidification and combustion stability is made excellent. 1. A fuel flow control method of a gas turbine combustor provided in a humid air gas turbine comprising a compressor , the gas turbine combustor , in which a fuel is burned with the use of a compressed air compressed by the compressor to generate a combustion gas , a turbine driven by a combustion gas generated in the gas turbine combustor , and a humidifier for humidifying a compressed air compressed by the compressor and supplied to the gas turbine combustor , the gas turbine combustor comprising a plurality of combustion sections comprised of a plurality of fuel nozzles for supplying of a fuel and a plurality of air flow passages for supplying of a combustion air , a part of the plurality of combustion sections provided in the gas turbine combustor being formed into a combustion section or sections , which are more excellent in flame holding performance than the remaining combustion sections , in which method fuel ratios of fuels , respectively , supplied to the plurality of combustion sections of the gas turbine combustor are controlled on the basis of deviation between a load command and electric power generation ,the method comprising controlling a fuel flow rate to the combustion sections in the gas turbine combustor through evaluating a moisture content in a combustion air supplied to the gas turbine combustor on the basis of a humidification water quantity and an air temperature after humidification in the humidifier, using a combustion air flow rate supplied to the gas turbine combustor to evaluate a combustion temperature in the combustion sections, and regulating a fuel ratio of a fuel flow rate supplied to the combustion section or sections of excellent flame holding performance and a fuel ...

Подробнее
Номер записи: 8
25-07-2013 дата публикации

Fluid flow control device and method

Номер: US20130186098A1
Автор: Bruce Paradise
Принадлежит: Hamilton Sundstrand Corp

A fluid flow control system includes a fluid inlet, a central chamber, a first nozzle extending from a first side of the central chamber and comprising a first throat, a second nozzle extending from a second side of the central chamber opposite the first side and comprising a second throat, and a flow control shuttle. The flow control shuttle includes a first needle having a first tapered portion positioned within the first throat for controlling flow through the first nozzle and a second needle having a second tapered portion positioned within the second throat for controlling flow through the second nozzle.

Подробнее
Номер записи: 9
22-08-2013 дата публикации

CONTROL OF A FUEL METERING DEVICE FOR TURBOMACHINE

Номер: US20130213053A1
Автор: GAULLY Bruno Robert, MAROT Cécile
Принадлежит: SNECMA

A control of a fuel metering device for a turbine engine as a function of a weight flow rate setpoint includes responding to at least one validity criterion to select a weight flow rate from among: a weight flow rate calculated as a function of a position signal; a weight flow rate calculated as a function of the position signal and of at least one temperature measurement signal; a weight flow rate calculated as a function of the position signal and of at least one permittivity measurement signal; a weight flow rate calculated as a function of the position signal, of at least one temperature measurement signal, and of at least one permittivity measurement signal; and a weight flow rate calculated as a function of a temperature measurement signal, of a permittivity measurement signal, and of a volume flow rate measurement signal. 110-. (canceled)11. A method of controlling a position of a slide of a fuel metering device for a turbine engine as a function of a weight flow rate setpoint , the method comprising:obtaining a position signal coming from a sensor configured to measure a position of the slide;obtaining at least one measurement signal coming from a flow meter configured to measure a fuel flow rate in the flow meter;estimating at least one validity criterion for the at least one measurement signal;determining a fuel weight flow rate through the flow meter; andcontrolling the position of the slide as a function of the determined weight flow rate and of the weight flow rate setpoint;the at least one measurement signal comprises first and second fuel temperature measurement signals, first and second fuel permittivity measurement signals, and first and second fuel volume flow rate measurement signals; and a weight flow rate calculated as a function of the position signal;', 'a weight flow rate calculated as a function of the position signal and of at least one of the temperature measurement signals;', 'a weight flow rate calculated as a function of the position ...

Подробнее
Номер записи: 10
29-08-2013 дата публикации

Methods of Operation of A Gas Turbine With Improved Part Load Emissions Behavior

Номер: US20130219904A1
Автор: Eroglu Adnan, Flohr Peter, Geng Weiqun, Knapp Klaus, Knoepfel Hans Peter
Принадлежит: ALSTOM TECHNOLOGY LTD.

In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (λ) of the operative burners () of the second combustor () is kept below a maximum air ratio (λ) at part load In order to reduce the maximum air ratio (λ), a series of modifications in the operating concept of the gas turbine are carried out individually or in combination. One modification is an opening of the row of variable compressor inlet guide vanes () before engaging the second combustor (). For engaging the second combustor, the row of variable compressor inlet guide vanes () is quickly closed and fuel is introduced in a synchronized manner into the burner () of the second combustor (). A further modification is the deactivating of individual burners () at part load. 1. A method for the low-CO emissions operation of a gas turbine with sequential combustion , wherein the gas turbine includes a first turbine , a second turbine , at least one compressor , a first combustor which is connected downstream to the compressor and the hot gases of which first combustor are admitted to the first turbine , and a second combustor which is connected downstream to the first turbine and the hot gases of which are admitted to the second turbine , the second combustor including operative burners each having an air ratio (λ) , the method comprising:{'sub': 'max', 'maintaining the air ratio (λ) of the operative burners of the second combustor below a maximum air ratio (λ).'}2. The method as claimed in claim 1 , further comprising:{'b': '2', 'shutting off a fuel feed to at least one burner of the second combustor at part load so that, with an unaltered turbine inlet temperature of the second turbine (TIT), an air ratio (λ) of the burners in operation is reduced.'}3. The method as claimed in claim 2 , wherein:the second combustor includes a parting plane; andshutting off a fuel feed to at least one burner of the second combustor at part load comprises first shutting ...

Подробнее
Номер записи: 11
29-08-2013 дата публикации

AUTOMATED TUNING OF GAS TURBINE COMBUSTION SYSTEMS

Номер: US20130219906A1
Автор: Chandler Christopher
Принадлежит: Gas Turbine Efficiency Sweden AB

A system for tuning the operation of a gas turbine is provided based on measuring operational parameters of the turbine and directing adjustment of operational controls for various operational elements of the turbine. A controller is provided for communicating with sensors and controls within the system. The controller receiving operational data from the sensors and comparing the data to stored operational standards to determining if turbine operation conforms to the standards. The controller then communicates selected adjustment in an operational parameter of the turbine. The controller then receives additional operational data from the sensors to determine if an additional adjustment is desired or is adjustment is desired of a further selected operational parameter. 1. A system for tuning the operation of a gas turbine , the turbine having sensors for measuring operational parameters of the turbine , the operational parameters including combustor dynamics , and turbine exhaust emissions , the turbine also having operational controls for adjusting various operational control elements of the turbine , the operational control elements comprising the turbine fuel distribution splits , the inlet fuel temperature , and fuel-air ratio , and a communication link for the sensors and controls , the system comprising: receiving operational data regarding the operational parameters including combustor dynamics and turbine exhaust emissions from the sensors,', 'comparing the operational data to stored operational standards and determining if turbine operation conforms to the operational standards, the operational standards based on operational priorities,', 'communicating with the operational controls to perform a selected adjustment in an operational control element of the turbine,', 'receiving operational data from the sensors upon communicating the selected adjustment to determine if an additional incremental adjustment is desired, and', 'upon completing a series of ...

Подробнее
Номер записи: 12
12-09-2013 дата публикации

Apparatus for Releasing a Flow Cross Section of a Gas Line

Номер: US20130232990A1
Автор: Martin Lenz, Sascha Stoll
Принадлежит: MAN Diesel and Turbo SE

An apparatus is described for the controlled release of a flow cross section of a gas line which is connected to a combustion chamber of a gas engine. The apparatus has a check valve and a flexible device. The flexible device is provided for absorbing a force occurring as a result of a thermal expansion of the check valve.

Подробнее
Номер записи: 13
31-10-2013 дата публикации

Fuel circuit for an aviation turbine engine, the circuit having a fuel pressure regulator valve

Номер: US20130283811A1
Автор: Nicolas Potel, Sébastien Gameiro
Принадлежит: SNECMA SAS

A fuel circuit for an aviation turbine engine, the fuel circuit including: a main fuel line for feeding fuel to a combustion chamber of the engine and including a positive displacement pump; an auxiliary fuel line connected to the main fuel line at a junction situated downstream from the pump and serving to feed fuel to hydraulic actuators to control variable-geometry equipment of the engine, the auxiliary fuel line including electrohydraulic servo-valves upstream from each actuator; and a fuel pressure regulator valve arranged on the main fuel line downstream from the pump.

Подробнее
Номер записи: 14
07-11-2013 дата публикации

AERO COMPRESSION COMBUSTION DRIVE ASSEMBLY CONTROL SYSTEM

Номер: US20130291550A1
Автор: Fuchs Michael J., Weinzierl Steven M.
Принадлежит: ENGINEERED PROPULSION SYSTEMS, INC.

A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member. A control method is further included. 1. A control method for an aero compression combustion drive assembly , the aero compression combustion drive assembly having an engine member , a transmission member and a propeller member , the control system comprising:sensing a pressure parameter in each of a plurality of compression chambers of the engine member;providing the sensed pressure parameter to a control system device;providing a plurality of control programs to the control system device; andthe control system device acting on the sensed pressure parameter to effect a control strategy in the engine member.2. The control method of claim 1 , including implementing the control strategy in the engine member by affecting the operation of at least one fuel injector.3. The control method of claim 2 , including affecting a fuel pulse timing of at least one fuel injector.4. The control method of claim 2 , including affecting a fuel pulse duration of at least one fuel injector.5. The control method of claim 2 , including affecting the operation of at least one turbocharger.6. A control method for an aero compression combustion drive assembly claim 2 , the aero compression combustion drive assembly having an engine member claim 2 , a transmission member and a propeller member claim 2 , the control system comprising:sensing a pressure parameter in each of ...

Подробнее
Номер записи: 15
21-11-2013 дата публикации

GAS TURBINE SYSTEM

Номер: US20130305735A1
Автор: Ahn Chul-Ju
Принадлежит:

Provided is a gas turbine including: a first compressor which compresses air; a mixer which adds the compressed air from the first compressor to fuel and generates a fuel mixture; a combustor which combusts the generated fuel mixture from the mixer; a plurality of flow meters which adjusts an amount of the air or the fuel injected into the mixer; and a control unit which maintains the Wobbe Index of the fuel mixture within a predetermined Wobbe Index rang. 1. A gas turbine system comprising:a first compressor which compresses air;a mixer which adds the compressed air from the first compressor to fuel and generates a fuel mixture;a combustor which combusts the generated fuel mixture from the mixer;a plurality of flow meter which adjust an amount of the air or the fuel injected into the mixer; anda control unit which maintains the Wobbe Index of the fuel mixture within a predetermined Wobbe Index range.2. The gas turbine system of claim 1 , wherein the first compressor compresses the air supplied from an external source.3. The gas turbine system of claim 1 , further comprising a second compressor which compresses the air supplied from an external source claim 1 , and supplies the compressed air from the second compressor to at least one of the combustor and the first compressor.4. The gas turbine system of claim 1 , wherein the plurality of flow meters comprise a fuel flow meter which adjusts an amount of the fuel supplied to the mixer.5. The gas turbine system of claim 4 , further comprising a first sensor unit which measures at least one of a temperature claim 4 , a pressure claim 4 , and a flux of fuel ejected from the fuel flow meter.6. The gas turbine system of claim 1 , further comprising a heat exchanger which heats at least one of the air ejected from the first compressor and the fuel supplied to the mixer.7. The gas turbine system of claim 6 , further comprising a turbine which operates by a combustion gas ejected from the combustor claim 6 ,wherein the heat ...

Подробнее
Номер записи: 16
12-12-2013 дата публикации

Fuel metering valve fail-fixed and back-up control system

Номер: US20130327044A1
Автор: Brad McRoberts, David Tuttle, Greg Lafferty, Gregory Kline, Larry Portolese, Paul W. Futa
Принадлежит: Honeywell International Inc

A system provides “fail fixed” functionality and allows a user to manually manipulate fuel flow to a gas turbine engine in the unlikely event the primary control means is unavailable. The fuel metering unit includes a fuel metering valve, a flow increase valve, and a flow decrease valve. The flow increase valve and flow decrease valves are both in fluid communication with the fuel metering valve and are each adapted to selectively receive fuel flow commands from a primary fuel flow command source and from a secondary fuel flow command source. The flow increase and decrease valves are responsive to the fuel flow commands to selectively control the position of the fuel metering valve.

Подробнее
Номер записи: 17
09-01-2014 дата публикации

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

Номер: US20140007585A1
Автор: Liu Kexin
Принадлежит:

A liquid fuel assist ignition system for providing a fuel/air mixture to a gas turbine in its start-up phase includes a high pressure tank, a vacuum pump connected to the high pressure tank, a liquid fuel inlet connected to the high pressure tank, an air inlet connected to the high pressure tank, and an outlet of the high pressure tank connected to a burner of the gas turbine. 117-. (canceled)18. A liquid fuel assist ignition system for providing a fuel/air mixture to a gas turbine in its start-up phase , comprisinga high pressure tank,a vacuum pump connected to the high pressure tank,a liquid fuel inlet connected to the high pressure tank,an air inlet connected to the high pressure tank, and an outlet of the high pressure tank connected to a burner of the gas turbine.19. The liquid fuel assist ignition system according to claim 18 , wherein the liquid fuel assist ignition system comprises an air pump connected to the air inlet for providing air to the high pressure tank.20. The liquid fuel assist ignition system according to claim 18 , wherein the vacuum pump and/or the liquid fuel inlet and/or the air inlet and/or the outlet and/or the pipes between the vacuum pump claim 18 , the liquid fuel inlet claim 18 , the air inlet and/or the outlet comprise(s) one or more control elements.21. The liquid fuel assist ignition system according to claim 20 , wherein the connection elements comprise switchable valves.22. The liquid fuel assist ignition system according to claim 18 , wherein the liquid fuel inlet comprises a needle like pipe.23. The liquid fuel assist ignition system according to claim 18 , wherein the liquid fuel assist ignition system comprises an external heat source to heat up the high pressure tank.24. The liquid fuel assist ignition system according to claim 23 , wherein the external heat source is an electric heater.25. The liquid fuel assist ignition system according to claim 23 , wherein the external heat source comprises a temperature controller and/or ...

Подробнее
Номер записи: 18
13-03-2014 дата публикации

Fuel metering system electrically servoed metering pump

Номер: US20140072457A1
Автор: Dwayne Michael Benson
Принадлежит: Honeywell International Inc

A fuel metering system for supplying fuel to load includes a variable displacement piston pump having an adjustable hanger that is movable to a plurality of positions. The variable displacement piston pump is configured to receive a drive torque and, upon receipt of the drive torque, to supply fuel to the plurality of loads at a flow rate dependent on the position of the adjustable hanger. A hanger actuator is coupled to receive hanger position commands and is operable, in response thereto, to move the adjustable hanger to the commanded position.

Подробнее
Номер записи: 19
04-01-2018 дата публикации

Metering Valve

Номер: US20180005743A1
Автор: PLUCINSKI Wojciech
Принадлежит:

A metering valve comprising a solenoid having: a coil mounted on a core; and an armature moveable axially with respect to the core and against a return bias in response to a current in the coil; a variable capacitor having a first plate mounted for movement with the armature and a second plate fixed with respect to the core. The metering valve comprises an electronic feedback loop which is used to adjust the current in the coil based on a feedback signal derived from of the capacitance of the variable capacitor. A reference capacitor may be provided having opposing third and fourth plates at a set separation. A valve body may house the solenoid, the variable capacitor and the reference capacitor. 1. A metering valve comprising: a coil mounted on a core; and', 'an armature moveable axially with respect to the core and against a return bias in response to a current in the coil;, 'a solenoid havinga variable capacitor having a first plate mounted for movement with the armature and a second plate fixed with respect to the core; andan electronic feedback loop which is used to adjust the current in the coil based on a feedback signal derived from of the capacitance of the variable capacitor.2. The metering valve as claimed in claim 1 , further comprising:a reference capacitor having third and fourth plates at a set separation; anda valve body which houses the solenoid, the variable capacitor and the reference capacitor.3. The metering valve as claimed in claim 2 , further comprising a controller for controlling the current in the coil and the movement of the armature claim 2 , the controller being responsive to the feedback signal to adjust the current in the coil.4. The metering valve as claimed in claim 2 , wherein the electronic feedback loop is configured to:observe a ratio of the capacitances of the variable and reference capacitors; anduse the ratio of the capacitances to produce a feedback signal corresponding to a displacement of the armature.5. The metering valve ...

Подробнее
Номер записи: 20
21-01-2016 дата публикации

Fuel Cutoff Testing System

Номер: US20160017816A1
Автор: McDonald Darren Gordon, Welsh Bryan Douglas
Принадлежит:

A method and apparatus for controlling operation of an engine in an aircraft. A time when a cutoff speed for the aircraft will be reached at which a flow of fuel is to be stopped is identified. A delay between sending a command to move a switch to an off position and the time at which the engine ceases operation is also identified. The command is sent based on the predicted time and the delay. The command causes the switch to move to the off position moving a fuel control switch for the engine of the aircraft to a shut off position to stop the flow of fuel to the engine.

Подробнее
Номер записи: 21
21-01-2016 дата публикации

METERING DEVICE FOR A FUEL FEED CIRCUIT OF AN ENGINE

Номер: US20160017817A1
Автор: Benezech Philippe Jean, Langford Stephen, Marie, Rene, SAMSON Rafael, SICAIRE Pierre
Принадлежит: TURBOMECA

A metering device for an engine fuel feed circuit, the device including a metering valve, and a pressure regulator device maintaining a constant pressure difference from downstream to upstream across the metering valve, wherein the metering valve includes a seat provided with an inlet orifice and an outlet orifice, a shutter arranged within the seat, and an actuator controlling the position of the shutter, and wherein, between the inlet orifice and the outlet orifice the shutter defines a passage of minimum section that is variable as a function of the position of the shutter along a stroke extending between a bottom abutment and a top abutment and passing via a threshold position. 1. A metering device for an engine fuel feed circuit , the device comprising:a metering valve; anda pressure regulator device maintaining a constant pressure difference from downstream to upstream across the metering valve; a seat provided with an inlet orifice and an outlet orifice;', 'a shutter arranged within the seat; and', 'an actuator controlling the position of the shutter; and, 'wherein the metering valve compriseswherein, between the inlet orifice and the outlet orifice, the shutter defines a passage of minimum section that is variable as a function of the position of the shutter along a stroke extending between a bottom abutment and a top abutment and passing via a threshold position;{'b': '2', 'wherein the shutter is configured in such a manner that, firstly, the minimum section of said passage, and thus the flow rate of fuel passing through the valve, increases linearly as a function of the position coordinate of the shutter between the bottom abutment (b) and the threshold position, and that, secondly, the minimum section of said passage, and thus of the fuel flow rate, increases quadratically or more rapidly, as a function of the position coordinate of the shutter between the threshold position and the top abutment.'}2. A metering device according to claim 1 , wherein the ...

Подробнее
Номер записи: 22
28-01-2016 дата публикации

ECOLOGY FUEL RETURN SYSTEMS

Номер: US20160025015A1
Автор: Carpenter Richard J., Flow Ethan, Gibbons Kevin, JR. Leo J., Reuter Charles E., Ribarov Lubomir A., Veilleux
Принадлежит:

A shut-off valve includes a float and a negative G control component. The float is configured to occlude a tank outlet at a first fluid level and 1 G and unocclude the tank outlet at a second fluid level and 1 G. The negative G control component is operatively connected to the float to limit fluid, e.g. liquid or gas, communication between a tank outlet and an ejector pump during negative G events. An ecology fuel return system includes a tank, an ejector pump, a float, and a negative G control component, as described above. The tank has an inlet and an outlet. The inlet is configured to be in fluid communication with components of an engine. The ejector pump is in fluid communication with the tank outlet and is configured to pump fuel from the tank to a fuel pump inlet of an engine. 1. A shut-off valve comprising:a float configured to occlude a tank outlet at a first fluid level and 1 G and unocclude the tank outlet at a second fluid level and 1 G; anda negative G control component operatively connected to the float to limit fluid communication between a tank outlet and an ejector pump during negative G events.2. A shut-off valve as recited in claim 1 , wherein the negative G control component includes a biasing component claim 1 , wherein the biasing component is configured to apply a biasing force to the float claim 1 , wherein the biasing force is greater than a pre-determined negative G event force and less than the buoyancy force of the float at 1 G.3. A shut-off valve as recited in claim 2 , wherein in an occluded position the biasing force of the biasing component is greater or equal to the buoyancy force of the float at 1 G.4. A shut-off valve as recited in claim 2 , wherein in an unoccluded position the biasing force of the biasing component is less than the buoyancy force of the float at 1 G.5. A shut-off valve as recited in claim 2 , wherein the biasing component includes a spring operatively connected to a top portion of the float.6. A shut-off valve as ...

Подробнее
Номер записи: 23
10-02-2022 дата публикации

Device for controlling gas turbine, gas turbine facility, method for controlling gas turbine, and program for controlling gas turbine

Номер: US20220042466A1
Автор: Tsukasa Ito, Yosuke Fujitomi
Принадлежит: Mitsubishi Power Ltd

A control device includes a load fuel quantity calculation unit, an allowable fuel quantity calculation unit, a flow rate low value selection unit, a basic drive quantity calculation unit, a fuel deviation calculation unit, and a correction unit. The load fuel quantity calculation unit determines a load fuel quantity based on a required output. The allowable fuel quantity calculation unit determines an allowable fuel quantity to protect a gas turbine. The flow rate low value selection unit selects a minimum fuel quantity from among the determined fuel quantities. The basic drive quantity calculation unit determines a basic drive quantity of an air intake quantity regulator. The fuel deviation calculation unit determines a fuel deviation between the allowable fuel quantity and the minimum fuel quantity. The correction value calculation unit determines a correction value corresponding to the fuel deviation which is then used to correct the basic drive quantity.

Подробнее
Номер записи: 24
29-01-2015 дата публикации

SYSTEM FOR PERFORMING STAGING CONTROL OF A MULTI-STAGE COMBUSTOR

Номер: US20150027100A1
Автор: Qin Yong, STEVENSON Andrew
Принадлежит:

A control system is provided for performing staging control of a multi-stage combustor of a gas turbine engine. The fuel is fed to the combustor by a fuel supply system comprising: a plurality of fuel manifolds distributing fuel to respective stages of the combustor, a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds, and an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds. The control system includes a fuel pressure sensor arrangement which senses the fuel pressure at entry to the actuating arrangement, and/or in one or more of the fuel manifolds. The control system further includes a controller which repeatedly: calculates a fuel split between the fuel manifolds based on the sensed fuel pressure(s), and issues a command signal to the actuating arrangement to implement the calculated fuel pressure-based fuel split. 1. A fuel supply system for feeding fuel to a multi-stage combustor of a gas turbine engine , the fuel supply system comprising: a plurality of fuel manifolds which distribute fuel to respective stages of the combustor , a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds , an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds , and a control system for performing staging control of the combustor;wherein the control system includes:a fuel pressure sensor arrangement which senses the fuel pressure at entry to the actuating arrangement, and/or in one or more of the fuel manifolds; anda controller which commands the fuel metering valve to supply fuel to the combustor at a given flow rate, and which repeatedly: calculates a fuel split between the fuel manifolds based on the sensed fuel pressure(s), and issues a command signal to the actuating arrangement to implement the calculated fuel pressure-based fuel split.2. A fuel supply system according to claim 1 , wherein ...

Подробнее
Номер записи: 25
23-01-2020 дата публикации

METERING VALVE ASSEMBLY AND METHOD OF ASSEMBLY THEREOF

Номер: US20200025111A1
Автор: Barnhart David Richard, Cadman John Michael
Принадлежит:

A valve assembly includes a body including an inlet port, an outlet port, and a flow passage extending therebetween. The flow passage includes a plurality of valve seats in a stepped arrangement between the inlet port and the outlet port. The valve assembly further includes a valve stem positioned within the flow passage. The valve stem includes at least one shaft and a poppet disk positioned at one end of the at least one shaft, and at least one reed petal coupled to the at least one shaft. The poppet disk is engageable with a first valve seat of the plurality of valve seats, and the at least one reed petal is engageable with a second valve seat of the plurality of valve seats. 1. A gas turbine engine system comprising:a combustor comprising a fuel nozzle; a body comprising an inlet port, an outlet port, and a flow passage extending therebetween and comprising a plurality of valve seats in a stepped arrangement between said inlet port and said outlet port; and', 'a valve stem positioned within said flow passage and comprising at least one shaft, a poppet disk positioned at one end of said at least one shaft, and at least one reed petal coupled to said at least one shaft, wherein said poppet disk is engageable with a first valve seat of said plurality of valve seats, and said at least one reed petal is engageable with a second valve seat of said plurality of valve seats., 'a valve assembly coupled in flow communication with said fuel nozzle, said valve assembly configured to channel a fluid from a fuel line to said fuel nozzle, said valve assembly comprising2. A system in accordance with claim 1 , wherein said valve stem further comprises a bias member configured to apply a force to said at least one shaft in a closing direction.3. The system in accordance with claim 1 , wherein said at least one reed petal comprises at least one aperture.4. The system in accordance with claim 1 , wherein said poppet disk and said at least one reed petal engages with said respective ...

Подробнее
Номер записи: 26
28-01-2021 дата публикации

FUEL SYSTEMS

Номер: US20210025330A1
Автор: Gibbons Kevin, Reuter Charles E.
Принадлежит: HAMILTON SUNDSTRAND CORPORATION

A fuel system can include a total flow line configured to receive a total flow and a primary flow line connected to the total flow line. The primary flow line can be in fluid communication with one or more primary fuel nozzles of a nozzle assembly. The fuel system can include a secondary flow line connected to the total flow line in parallel with the primary flow line, the secondary flow line in fluid communication with a plurality of secondary flow nozzles of the nozzle assembly. The fuel system can include a flow split system configured to control a flow split between a primary flow of the primary flow line and a secondary flow of the secondary flow line. 1. A fuel system , comprising:a total flow line configured to receive a total flow;a primary flow line connected to the total flow line, the primary flow line in fluid communication with one or more primary fuel nozzles of a nozzle assembly;a secondary flow line connected to the total flow line in parallel with the primary flow line, the secondary flow line in fluid communication with a plurality of secondary flow nozzles of the nozzle assembly; anda flow split system configured to control a flow split between a primary flow of the primary flow line and a secondary flow of the secondary flow line.2. The fuel system of claim 1 , wherein the flow split system is configured to provide non-discrete flow splitting above a minimum flow split or at least a plurality of discreet flow splits above a minimum flow split.3. The fuel system of claim 2 , wherein the flow split system includes a secondary metering valve disposed on the secondary flow line and configured to be positioned to meter flow of the secondary flow line.4. The fuel system of claim 3 , further comprising a torque motor configured to operate the secondary metering valve to position the secondary metering valve to control the secondary flow of the secondary flow line.5. The fuel system of claim 4 , wherein the torque motor is a pressure servo valve ...

Подробнее
Номер записи: 27
28-01-2021 дата публикации

FUEL DELIVERY SYSTEM AND METHOD

Номер: US20210025337A1
Автор: Kojovic Aleksandar, Morenko Oleg, VERHIEL Jeffrey Richard
Принадлежит:

A method of operating a fuel delivery system of an aircraft engine of an aircraft includes operating the aircraft engine in a standby mode by maintaining combustion in a combustor of the aircraft engine by supplying fuel to the combustor via a first set of fuel nozzles of a first fuel manifold while providing a trickle flow of fuel via a second set of fuel nozzles of a second fuel manifold into the combustor during engine operation, the trickle flow being defined as a fuel flow rate selected to prevent flame-out of the combustion while providing one of: substantially no motive power to the aircraft, and no motive power to the aircraft, via the combustion of the trickle flow of fuel. An aircraft gas turbine engine is also described. 1. A method of operating a fuel delivery system of an aircraft engine of an aircraft , comprising operating the aircraft engine in a standby mode by maintaining combustion in a combustor of the aircraft engine by supplying fuel to the combustor via a first set of fuel nozzles of a first fuel manifold while providing a trickle flow of fuel via a second set of fuel nozzles of a second fuel manifold into the combustor during engine operation , the trickle flow being defined as a fuel flow rate selected to prevent flame-out of the combustion while providing one of: substantially no motive power to the aircraft , and no motive power to the aircraft , via the combustion of the trickle flow of fuel.2. The method of claim 1 , wherein the providing the trickle flow includes providing a trickle flow of fuel out of the second fuel manifold via a by-pass across a valve in the second fuel manifold.3. The method of claim 2 , wherein the providing the trickle flow includes providing a trickle flow of fuel out of the second fuel manifold via a by-pass across a valve in each of a plurality of fuel nozzles of the second fuel manifold.4. The method of claim 2 , wherein the providing the trickle flow includes providing a trickle flow of fuel to a location ...

Подробнее
Номер записи: 28
01-02-2018 дата публикации

SYSTEM AND METHOD FOR CONTROL OF GAS TURBINE ENGINE

Номер: US20180030904A1
Автор: MEUNIER Gabriel
Принадлежит:

Systems and methods for regulating fuel flow to a gas turbine engine are provided. Power for the engine is governed using a control structure having an inner control loop and an outer control loop, the outer control loop comprising a feedback controller that outputs a feedback command based on a power error determined as a function of a shaft horsepower, the feedback command used to determine a gas generator speed error, the gas generator speed error used by the inner control loop for outputting a fuel flow command. The shaft horsepower is determined from a torque measurement of the engine using a torque pressure transducer. When a momentary loss of the torque measurement from the torque pressure transducer is detected, power fluctuations due to the loss of torque measurement are limited by maintaining the feedback command from the feedback controller constant during the momentary loss of torque measurement. 1. A method of regulating fuel flow to a gas turbine engine , the method comprising:governing power for the engine using a control structure having an inner control loop and an outer control loop, the outer control loop comprising a feedback controller that outputs a feedback command based on a power error determined as a function of a shaft horsepower, the feedback command used to determine a gas generator speed error, the gas generator speed error used by the inner control loop for outputting a fuel flow command;determining the shaft horsepower from a torque measurement of the engine using a torque pressure transducer;detecting a momentary loss of the torque measurement from the torque pressure transducer; andlimiting power fluctuations due to the loss of torque measurement by maintaining the feedback command from the feedback controller constant during the momentary loss of torque measurement.2. The method of claim 1 , wherein detecting the momentary loss of the torque measurement comprises detecting a drop in a gearbox oil pressure of the engine.3. The ...

Подробнее
Номер записи: 29
31-01-2019 дата публикации

Determination of a fuel delivery fault in a gas turbine engine

Номер: US20190032576A1
Автор: Andrew Rimell, Carl L. MULDAL, Stephen P. King
Принадлежит: Rolls Royce PLC

A method of determining a fuel delivery fault in a gas turbine engine is provided, the engine having a combustor, a combustor fuel system for delivering fuel to the combustor, and a turbine which is driven by hot gas from the combustor. The method includes comparing a measured turbine gas temperature profile against a predicted turbine gas temperature profile. The method further includes comparing a measured combustor instability against a predicted combustor instability. The method further includes indicating that a fuel delivery fault in the combustor fuel system has been detected when both the measured turbine gas temperature profile and the measured combustor instability differ from their predicted values by more than respective predetermined thresholds.

Подробнее
Номер записи: 30
04-02-2021 дата публикации

GAS TURBINE HEATER AND DUAL FUEL GAS TURBINE ENGINE

Номер: US20210033024A1
Автор: Ethier Jason How-Ring, Lakov German, Wang Ivan
Принадлежит: Dynamo Micropower Corporation

This disclosure teaches a gas turbine heater that can be used in either portable or stationary applications. In one embodiment, a gas turbine heater includes a gas turbine engine that generates hot exhaust gas, an air blower that draws an amount of air flow from ambient, a mixing plenum that allows the gas turbine exhaust and ambient air flow to mix together to create warm air, and an outlet that delivers the warm air to the customer. In another embodiment, a gas turbine heater includes a gas turbine engine that generates hot exhaust gas, an air blower that draws an amount of air flow from ambient, an air-to-air heat exchanger that transfers heat from the gas turbine exhaust to the ambient air flow to create warm air, and an outlet that delivers the warm air to the customer. 1. A direct-fired gas turbine heater comprising: a compressor that receives cold air at a compressor inlet and delivers compressed air at a compressor outlet;', 'a fuel manifold that receives combustible fuel at a fuel manifold inlet and delivers fuel at a fuel manifold outlet;', 'a combustor whose air inlet receives compressed air from the compressor outlet and whose fuel inlet receives fuel from the fuel manifold outlet, and whose igniter combusts the mixture of air and fuel inside the combustor, and delivers hot gas at a combustor outlet;', 'a turbine whose air inlet receives hot gas from the combustor outlet, and extracts energy from the hot gas as the hot gas flows through the turbine, and delivers hot gas at a turbine outlet;', 'a shaft that connects the compressor and turbine, such that the energy extracted by the turbine is used to drive the compressor;, 'a gas turbine engine comprisinga main air blower that receives cold air from ambient at a main air blower inlet and delivers cold air at a main air blower outlet;a mixing plenum having a cold air inlet that receives cold air from the main air blower outlet, a hot gas inlet that receives hot gas from the turbine, and a heater outlet that ...

Подробнее
Номер записи: 31
11-02-2016 дата публикации

Pressure Sensor Noise Filter Prior to Surge Detection for a Gas Turbine Engine

Номер: US20160040604A1
Автор: BREHM Andrew, HRACH Michael
Принадлежит:

A filter algorithm for a dual channel electronic engine control system according to one disclosed non-limiting embodiment of the present disclosure includes a division function that divides a measured pressure rate of change of one of a FADEC channel A and FADEC channel B by an average pressure of the FADEC channel A and the FADEC channel B to obtain a resultant value; a first comparator function to bound a proper high resultant value from the division function; a second comparator function to bound a proper low resultant value from the division function; and an OR gate in communication with the first comparator and the second comparator such that if an output from either the first comparator function and the second comparator function is true, that one of the FADEC channel A and the FADEC channel B is filtered out for a time period. 1. A filter algorithm for a dual channel electronic engine control system comprising:a division function that divides a measured pressure rate of change of one of a FADEC channel A and FADEC channel B by an average pressure of said FADEC channel A and said FADEC channel B to obtain a resultant value;a first comparator function to bound a proper high resultant value from said division function;a second comparator function to bound a proper low resultant value from said division function; andan OR gate in communication with said first comparator and said second comparator such that if an output from either said first comparator function and said second comparator function is true, that one of said FADEC channel A and said FADEC channel B is filtered out for a time period.2. The assembly as recited in claim 1 , wherein said measured pressure rate of change is measured by a digital pressure sensor on each of said FADEC channel A and said FADEC channel B.3. The assembly as recited in claim 1 , wherein said digital pressure sensor on each of said FADEC channel A and said FADEC channel B is in communication with a fan section of a gas turbine ...

Подробнее
Номер записи: 32
09-02-2017 дата публикации

FREE GAS TURBINE WITH CONSTANT TEMPERATURE-CORRECTED GAS GENERATOR SPEED

Номер: US20170037785A1
Автор: BELLEVILLE Francois, MORGAN KEITH
Принадлежит:

A method of controlling a speed of a gas turbine engine, the gas turbine engine including a high pressure spool and a low pressure spool rotating independently from one another, including determining a temperature-corrected rotational speed of the high pressure spool based on an actual rotational speed of the high pressure spool and on an air temperature measured outside of the gas turbine engine; controlling the rotation of the high pressure spool to maintain the temperature-corrected rotational speed of the high pressure spool at least substantially constant throughout a range of a power demand on the gas turbine engine; and controlling a rotational speed of the low pressure spool independently of the rotation of the high pressure spool. 1. A method of controlling a speed of a gas turbine engine , the gas turbine engine including a high pressure spool and a low pressure spool rotating independently from one another , the method comprising:determining a temperature-corrected rotational speed of the high pressure spool based on an actual rotational speed of the high pressure spool and on an air temperature measured outside of the gas turbine engine;controlling the rotation of the high pressure spool to maintain the temperature-corrected rotational speed of the high pressure spool at least substantially constant throughout a range of a power demand on the gas turbine engine; andcontrolling a rotational speed of the low pressure spool independently of the rotation of the high pressure spool.2. The method as defined in claim 1 , wherein the temperature-corrected rotational speed of the high pressure spool is calculated as Ng/√{square root over (θ)} claim 1 , where Ng is the actual rotational speed of the high pressure spool and θ is the air temperature measured outside of the gas turbine engine.3. The method as defined in claim 1 , wherein the temperature-corrected rotational speed of the high pressure spool is maintained at least substantially constant by modulating ...

Подробнее
Номер записи: 33
08-02-2018 дата публикации

SYSTEM AND METHOD FOR AN ENGINE CONTROLLER BASED ON ACCELERATION POWER

Номер: US20180038287A1
Автор: CHAREST Alexandre, LAMARRE Sylvain, MEUNIER Gabriel
Принадлежит:

Systems and methods for controlling an gas turbine engine are provided. The method comprises receiving a requested engine speed and obtaining a shaft inertia of the engine, a steady state fuel flow for the requested engine speed, and a relationship between fuel flow and acceleration power generated by the fuel flow. A required fuel flow to obtain the requested engine speed is determined as a function of the requested engine speed, the shaft inertia of the engine, the steady state fuel flow for the requested engine speed, and the relationship between fuel flow and acceleration power generated by the fuel flow. A command to a fuel flow metering valve is output in accordance with the required fuel flow. 1. A system for controlling a gas turbine engine , the system comprising:an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command; and receiving a requested engine speed;', 'obtaining a shaft inertia of the engine, a steady state fuel flow for the requested engine speed, and a relationship between fuel flow and acceleration power generated by the fuel flow; and', 'determining the required fuel flow to obtain the requested engine speed as a function of the requested engine speed, the shaft inertia of the engine, the steady state fuel flow for the requested engine speed, and the relationship between fuel flow and acceleration power generated by the fuel flow., 'a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow, the controller comprising a feedforward controller configured for2. The system of claim 1 , wherein the controller is further configured to limit acceleration of the gas turbine engine by applying a rate limit to the requested engine speed.3. The system of claim 1 , wherein the controller comprises a feedback controller configured to adjust the required fuel flow based on an acceleration ...

Подробнее
Номер записи: 34
08-02-2018 дата публикации

SYSTEM AND METHOD FOR AN ENGINE CONTROLLER BASED ON INVERSE DYNAMICS OF THE ENGINE

Номер: US20180038288A1
Автор: MEUNIER Gabriel, PEDRAMI Reza
Принадлежит:

Systems and methods for controlling a gas turbine engine are provided. The system comprises an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command and a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow. The controller comprises a feedforward controller configured for receiving a requested engine speed, obtaining a steady-state fuel flow for the requested engine speed as a function of the requested engine speed, the steady-state fuel flow, and the relationship between fuel flow and gas generator speed, and determining the required fuel flow to obtain the requested engine speed and the relationship between fuel flow and gas generator speed. 1. A system for controlling a gas turbine engine of an aircraft , the system comprising:an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command; and receiving a requested engine speed;', 'obtaining a steady-state fuel flow for the requested engine speed as a function of the requested engine speed, the steady-state fuel flow, and the relationship between fuel flow and gas generator speed; and', 'determining the required fuel flow to obtain the requested engine speed and the relationship between fuel flow and gas generator speed., 'a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow, the controller comprising a feedforward controller configured for2. The system of claim 1 , wherein the controller is further configured to limit acceleration of the gas turbine engine by applying a rate limit to the requested engine speed.3. The system of claim 1 , wherein the controller comprises a feedback controller configured to adjust the required fuel flow based on an acceleration error.4. The system ...

Подробнее
Номер записи: 35
16-02-2017 дата публикации

Fuel meter protected from icing

Номер: US20170044993A1
Автор: Anne Marie Cecile Barreau, Jean-Marie Brocard, Pierre Charles Mouton, Regis Michel Paul Deldalle
Принадлежит: SNECMA SAS

A fuel metering unit including a movable element including at least one fuel passage section opening upstream towards a fuel supply conduit and opening downstream towards a conduit of use through a metering slot with a flared profile having a narrow passage section flaring as far as a wide passage section, the movable element being able to be moved with respect to a fixed element between a low flow rate position in which the metering slot is for a large part obstructed and a high flow rate position in which the metering slot is for a large part exposed, the metering slot being made in the fixed element or in the movable element and its obstruction being obtained by covering the slot with a wall of the movable element or of the fixed element.

Подробнее
Номер записи: 36
15-02-2018 дата публикации

METERING VALVE ASSEMBLY AND METHOD OF ASSEMBLY THEREOF

Номер: US20180045121A1
Автор: Barnhart David Richard, Cadman John Michael
Принадлежит:

A valve assembly includes a body including an inlet port, an outlet port, and a flow passage extending therebetween. The flow passage includes a plurality of valve seats in a stepped arrangement between the inlet port and the outlet port. The valve assembly further includes a valve stem positioned within the flow passage. The valve stem includes at least one shaft and a poppet disk positioned at one end of the at least one shaft, and at least one reed petal coupled to the at least one shaft. The poppet disk is engageable with a first valve seat of the plurality of valve seats, and the at least one reed petal is engageable with a second valve seat of the plurality of valve seats. 1. A valve assembly comprising:a body comprising an inlet port, an outlet port, and a flow passage extending therebetween and comprising a plurality of valve seats in a stepped arrangement between said inlet port and said outlet port; anda valve stem positioned within said flow passage and comprising at least one shaft, a poppet disk positioned at one end of said at least one shaft, and at least one reed petal coupled to said at least one shaft, wherein said poppet disk is engageable with a first valve seat of said plurality of valve seats, and said at least one reed petal is engageable with a second valve seat of said plurality of valve seats.2. The valve assembly in accordance with claim 1 , wherein said valve stem further comprises a bias member configured to apply a force to said at least one shaft in a closing direction.3. The valve assembly in accordance with claim 1 , wherein said poppet disk and said at least one reed petal engages with said respective valve seat of said plurality of valve seats in a closed valve position.4. The valve assembly in accordance with claim 1 , wherein said valve stem is configured to progressively unseat from said body during valve opening.5. The valve assembly in accordance with claim 1 , wherein said at least one reed petal comprises at least one ...

Подробнее
Номер записи: 37
08-05-2014 дата публикации

FUEL METERING VALVE SYSTEM

Номер: US20140123654A1
Автор: Feinstein Michael, Kemmerer Alan James
Принадлежит: GENERAL ELECTRIC COMPANPY

A fuel metering valve system for use with a flow of fuel in a gas turbine engine may include a number of orifice plate lines, a number of differently sized orifice plates, and a number of orifice plate line valves. One of the orifice plate line valves opens and closes one of the orifice plates on the orifice plate lines. 1. A fuel metering valve system for use with a flow of fuel in a gas turbine engine , comprising:a plurality of orifice plate lines;a plurality of differently sized orifice plates; anda plurality of orifice plate line valves;wherein one of the plurality of orifice plate line valves opens and closes one of the plurality of orifice plates on the plurality of orifice plate lines.2. The fuel metering valve system of claim 1 , further comprising an inlet manifold in communication with the plurality of orifice plate lines.3. The fuel metering valve system of claim 1 , further comprising an upstream pressure-temperature sensor upstream of the plurality of orifice plate lines.4. The fuel metering valve system of claim 1 , further comprising an outlet manifold in communication with the plurality of orifice plate lines.5. The fuel metering valve system of claim 1 , further comprising a downstream pressure-temperature sensor downstream of the plurality of orifice plate lines.6. The fuel metering valve system of claim 1 , wherein the plurality of differently sized orifice plates comprises a parallel arrangement.7. The fuel metering valve system of claim 1 , wherein the plurality of orifice plate line valves comprises a plurality of solenoid valves.8. The fuel metering valve system of claim 1 , wherein the plurality of orifice plate line valves comprises a plurality of on and off valves.9. The fuel metering valve system of claim 1 , further comprising a flow controller in communication with the plurality of orifice plate line valves.10. The fuel metering valve system of claim 1 , wherein a first of the plurality of differently sized orifice plates comprises a ...

Подробнее
Номер записи: 38
03-03-2022 дата публикации

ENGINE ASSEMBLY AND METHOD OF OPERATION

Номер: US20220065176A1
Автор: SCHOBER Peter
Принадлежит:

A power plant assembly, including a turbine for driving at least one rotor shaft; a combustion chamber for generating drive energy for the turbine; at least one electric machine which is coupled to the rotor shaft and can be operated both in a generator mode and in a motor mode; and at least one energy storage system which is connected to the electric machine and can store energy generated by the electric machine when the electric machine is in generator mode. A set of control electronics of the power plant assembly is configured to operate the combustion chamber using a lean fuel-air mixture and, for this purpose, to selectively operate the at least one electric machine in generator mode or in motor mode, depending on the power to be applied by the power plant assembly.

Подробнее
Номер записи: 39
15-05-2014 дата публикации

GAS TURBINE PLANT WITH EXHAUST GAS RECIRCULATION AND ALSO METHOD FOR OPERATING SUCH A PLANT

Номер: US20140130507A1
Автор: Schulz Steffen, Wettstein Hans, WIRSUM Manfred
Принадлежит: ALSTOM TECHNOLOGY LTD.

A gas turbine plant is provided with exhaust gas recirculation and includes a main gas turbine having a main compressor and main turbine driving a main generator, and a combustion chamber, with an outlet connected to the inlet of the main gas turbine, has a fuel feed, and via the recuperator's high-pressure side obtains combustion air from the main gas turbine's compressor outlet. The outlet of the main turbine and the inlet of the main compressor are connected via the recuperator's low-pressure side and a cooler for exhaust gas recirculation. On the recuperator's low-pressure side, a charging unit, with a compressor and a turbine is arranged, and draws in air via an air intake and by the outlet of its compressor is connected to the recuperator's low-pressure side outlet and by the inlet of its turbine is connected to a surplus-gas extraction line on the recuperator's low-pressure side. 1. A method for operating a gas turbine plant in a partially closed , charged gas turbine cycle , the method comprising:combusting fuel in a combustion chamber, feeding a gaseous compressed operating medium which contains combustion air;expanding the operating medium, which contains hot combustion gases, in a main turbine of a main gas turbine, thereby performing work;extracting heat from the operating medium in a subsequent recuperator and in a cooler;compressing the operating medium in a compressor of the main gas turbine, and heat is fed to the compressed operating medium in the recuperator before re-entry into the combustion chamber;extracting on the low-pressure side of the recuperator a partial flow of the operating medium at an extraction point which is at a suitable first temperature level, and further expanded in a turbine of a charging unit; drawing in and compressing air by a compressor of the charging unit; andfeeding the air to the operating medium on a low-pressure side of the recuperator.2. The method as claimed in claim 1 , wherein COis separated from recirculated ...

Подробнее
Номер записи: 40
04-03-2021 дата публикации

METHODS AND SYSTEMS FOR STARTING A GAS TURBINE ENGINE

Номер: US20210062729A1
Автор: DURAND Sean
Принадлежит:

Methods and systems of starting a gas turbine engine are provided. During startup, a fuel pressure associated with a primary fuel supply of the gas turbine engine is monitored. A low-pressure event for the primary fuel supply is detected when the fuel pressure falls below a predetermined threshold. Responsive to detecting the low pressure event, an electric backup boost pump is activated by an engine controller to provide fuel to the gas turbine engine. 1. A method of starting a gas turbine engine , comprising:monitoring, during startup, a fuel pressure associated with a primary fuel supply of the gas turbine engine;detecting a low-pressure event for the primary fuel supply when the fuel pressure falls below a predetermined threshold; andresponsive to detecting the low pressure event, activating, by an engine controller, an electric backup boost pump to provide fuel to the gas turbine engine.2. The method of claim 1 , wherein monitoring the fuel pressure is performed responsive to detecting a flameout event for the gas turbine engine.3. The method of claim 2 , further comprising arming the electric backup boost pump responsive to detecting the flameout event and prior to detecting the low pressure event.4. The method of claim 1 , wherein detecting the low pressure event comprises:comparing a plurality of first pressure readings to the predetermined pressure threshold; anddetecting the low pressure event when at least two of the plurality of first pressure readings are below the predetermined pressure threshold.5. The method of claim 1 , further comprisingdeactivating the electric backup boost bump after a predetermined time delay;detecting one or more subsequent low pressure events for the primary fuel supply; andresponsive to detecting the one or more subsequent low pressure events, reactivating, by the engine controller, the electric backup boost pump to provide fuel to the gas turbine engine.6. The method of claim 1 , further comprising:obtaining a request to ...

Подробнее
Номер записи: 41
28-02-2019 дата публикации

GAS TURBOMACHINE FUEL SYSTEM, CONTROL SYSTEM AND RELATED GAS TURBOMACHINE

Номер: US20190063328A1
Автор: Keeney David Scott
Принадлежит:

Various embodiments include gas turbomachine (GT) fuel systems, related control systems and GTs. In some cases, the GT fuel system includes: a plurality of combustion chambers circumferentially disposed around a gas turbine; a set of fuel nozzles directly mounted to each of the plurality of combustion chambers; a set of conduits coupled with each of the set of fuel nozzles at a first end of each of the conduits; and a set of liquid fuel check valves coupled with a second end of each of the set of conduits, the set of liquid fuel check valves being positioned radially offset and axially offset from the set of fuel nozzles. 1. A gas turbomachine fuel system comprising:a plurality of combustion chambers circumferentially disposed around a gas turbine;a set of fuel nozzles directly mounted to each of the plurality of combustion chambers;a set of conduits coupled with each of the set of fuel nozzles at a first end of each of the conduits; anda set of liquid fuel check valves coupled with a second end of each of the set of conduits, the set of liquid fuel check valves being positioned radially offset and axially offset from the set of fuel nozzles.2. The gas turbomachine fuel system of claim 1 , wherein the set of liquid fuel check valves are circumferentially disposed around the gas turbine.3. The gas turbomachine fuel system of claim 1 , wherein the set of fuel nozzles are located adjacent each of the plurality of combustion chambers.4. The gas turbomachine fuel system of claim 3 , wherein the set of liquid fuel check valves are located at a greater axial distance and a greater radial distance from each combustion chamber than the set of fuel nozzles.5. The gas turbomachine fuel system of claim 1 , wherein the set of conduits spans an axial-radial path between the set of fuel nozzles and the set of liquid fuel check valves.6. The gas turbomachine fuel system of claim 1 , wherein a distance of the radial offset between the set of liquid fuel check valves and the set of ...

Подробнее
Номер записи: 42
28-02-2019 дата публикации

METHOD FOR SELECTION OF OPTIMAL ENGINE OPERATING CONDITIONS FOR GENERATING LINEARIZED MODELS FOR ON-BOARD CONTROL AND ESTIMATION

Номер: US20190063333A1
Автор: BENGEA SORIN, SIMMONS JEFFREY C.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A system for generating a base point database for use by a full authority digital engine control (FADEC) to control a gas turbine engine includes a memory configured to store a model of the gas turbine engine. The system also includes a model generation processor coupled to the memory and designed to perform an initial simulation of the gas turbine engine using the model to determine ranges of sensitivity of desired engine parameters throughout an operating envelope, divide the operating envelope into a multiple regions based on the ranges of sensitivity of the desired engine parameters, select multiple combinations of base points within each of the multiple regions, perform an additional simulation of the gas turbine engine to determine an accuracy of interpolation between each of the multiple combinations of base points for each of the multiple regions, and select final base points from the multiple combinations of base points based on the accuracy. 1. A system for generating a base point database for use by a full authority digital engine control (FADEC) to control a gas turbine engine during flight , the system comprising:a memory configured to store a model of the gas turbine engine; and perform an initial simulation of the gas turbine engine using the model to determine ranges of sensitivity of desired engine parameters throughout an operating envelope,', 'divide the operating envelope into a multiple regions based on the ranges of sensitivity of the desired engine parameters,', 'select multiple combinations of base points within each of the multiple regions,', 'perform an additional simulation of the gas turbine engine to determine an accuracy of interpolation between each of the multiple combinations of base points for each of the multiple regions, and', 'select final base points from the multiple combinations of base points based on the accuracy., 'a model generation processor coupled to the memory and configured to2. The system of claim 1 , wherein the ...

Подробнее
Номер записи: 43
29-05-2014 дата публикации

System and method to control a gas turbine subject to fuel composition variation

Номер: US20140144153A1
Автор: Timothy Andrew Healy
Принадлежит: General Electric Co

A system and method control a gas turbine subject to fuel composition variation. The method includes operating a first effector to control the gas turbine based on fuel composition. The method also includes operating a second effector to maintain operation of the first effector within a first boundary limit, the second effector operation being initiated when the operating the first effector reaches a second boundary limit within the first boundary limit.

Подробнее
Номер записи: 44
08-03-2018 дата публикации

FUEL METERING UNIT FOR TURBINE ENGINE

Номер: US20180066591A1
Автор: OZZELLO Guylain, ROLLAND Pascal
Принадлежит:

The invention relates to a fuel metering and distribution unit () which comprises in particular a slide valve () and a set of slots () configured with geometries, dimensions and positions such that: 1. A fuel metering and distribution unit , capable of controlling the fuel feed of a start-up injection ramp and of a main injection ramp in a combustion chamber of a turbine engine , a movable slide valve,', 'a feed port for the fuel flow rate to be distributed at least between the start-upstart-up injection ramp and the main injection ramp,', 'a first outlet port feeding the start-upstart-up ramp through a flow area on a span of the slide valve,', 'a regulator regulating the pressure differential between this outlet port and the feed port, so as to obtain, at the flow area, a metered total flow rate that is a function of a control current,', 'a second outlet port feeding the main ramp,, 'including a multi-outlet metering device comprising in a sleevewherein the second outlet port is fed through a set of slots, said set of slots being situated on a span of the slide valve other than that where said flow area of the outlet port feeding the start-upstart-up ramp is situated, and being fed by the first outlet port feeding the start-upstart-up ramp, the second outlet port thus being able to receive a portion of the total metered flow rate,said set of slots being more or less open depending on the position of the slide valve, so that the flow area defined by said set of slots varies and the distribution of flow rate between the start-upstart-up ramp and the main ramp varies as a function of the control current, in a first range of displacement of the slide valve, the flow area which feeds the first outlet port of the start-upstart-up ramp is progressively opened with the displacement of the slide valve, while the area of the set of slots which feeds the second outlet port of the main ramp is closed,', 'then, in a second range of displacement of the slide valve, the area of ...

Подробнее
Номер записи: 45
27-02-2020 дата публикации

Piezoelectric Ring Bender Servo Valve Assembly For Aircraft Flight Control Actuation And Fuel Control Systems

Номер: US20200063883A1
Автор: Yuan Michael
Принадлежит:

A piezoelectric ring bender servo valve assembly reduces mechanical wear by removing mechanical components used in prior art servo valves. The assembly does not use torque motor, flapper, and feedback spring. In this manner, no moving parts are required, which reduces maintenance and costs. A pair of piezoelectric ring benders mount adjacently to a pair of nozzles. The piezoelectric ring benders independently regulate the flow of fluid through the nozzles by moving between an open position to enable flowage, and a closed position to restrict flowage. A linear position sensing device measures and provides feedback about the spool position to a valve controller. The valve controller allows the spool valve to move until valve position achieves command position and the force on the spool valve is in equilibrium with pressure difference across spool valve. An H-bridge operable to switch the polarity of a differential pressure applied across to a load. 1. A piezoelectric ring bender servo valve assembly , the assembly comprising:a valve housing, the valve housing being defined by a passageway, the passageway being operable to carry a fluid;a pair of nozzles, the nozzles being in communication with the fluid, the nozzles terminating at a pair of orifices;a pair of piezoelectric bendable members disposed adjacent to the nozzles, the piezoelectric bendable members being operable to bend to an open position away from the nozzles to enable flowage of the fluid through the nozzles, the piezoelectric bendable members being operable to return to a closed position towards the nozzles to at least partially restrict flow through the nozzles;a spool valve operationally connected to the piezoelectric bendable members, the spool valve being disposed in at least one spool position to regulate flow of the fluid through the passageway, the piezoelectric bendable members controlling operation of the spool position;a variable restrictor operatively connected to the nozzles, the variable ...

Подробнее
Номер записи: 46
11-03-2021 дата публикации

Controller and method

Номер: US20210071590A1
Автор: Ghenadie Bulat, Jadeed Beita
Принадлежит: SIEMENS AG

A controller for a gas turbine is arranged to supply a load L. The gas turbine includes a fuel supply arranged to supply fuel at a fuel flow rate FF to a combustor, wherein the fuel supply includes a first fuel supply and a second fuel supply. The controller is arranged to determine one or more ratios R of one or more combustor operating parameters COP respectively at the load L to respective reference combustor operating parameters COPR at a reference load LR. The controller is further arranged to control a proportion P of the fuel flow rate FF supplied via the first fuel supply based, at least in part, on the determined one or more ratios R. A gas turbine with the controller and a method controls the gas turbine.

Подробнее
Номер записи: 47
19-03-2015 дата публикации

Method and system for augmenting the detection reliability of secondary flame detectors in a gas turbine

Номер: US20150075170A1
Автор: Alston Ilford Scipio, Dale J. Davis, Jean-Marc Carre, Sanji Ekanayake, William McEntagart
Принадлежит: General Electric Co

Systems and methods for operating a gas turbine combustion system by generating a flame detection signal are provided. A set of modeled parameters expected when there is a flame in a secondary combustion zone is calculated. A set of measured gas turbine parameters is measured. A flame validation signal based on the set of measured parameters and the set of modeled parameters is generated. The systems include a subsystem that calculates a set of modeled parameters expected when there is a flame in the secondary combustion zone and a subsystem that measures a set of measured parameters. A subsystem generates a flame validation signal based on the set of measured parameters and the set of modeled parameters.

Подробнее
Номер записи: 48
05-06-2014 дата публикации

SYSTEM AND METHOD FOR OPERATING A GAS TURBINE IN A TURNDOWN MODE

Номер: US20140150438A1
Автор: Arnold Robert Walter, Ellis George Allen, Findlay Chad Ernest, Mariani Michael John, Thatcher Jonathan Carl
Принадлежит: GENERAL ELECTRIC COMPANY

A system for operating a thermal power plant during off-peak demand intervals includes a gas turbine having a compressor, a combustor connected to a fuel control system, a turbine and a sensor configured to sense ambient conditions around the gas turbine. The fuel control system and the sensor are in communication with a controller. The controller is configured to receive a user input that corresponds to a value for an operational boundary condition of the thermal power plant and to monitor ambient conditions through the sensor. The controller is further configured to generate a predicted emissions level value for the gas turbine based on the monitored ambient conditions and to generate a command signal to adjust at least one operational parameter of the gas turbine based at least in part on the predicted emissions level value and the value of the operational boundary condition of the thermal power plant. 1. A system for operating a gas turbine of a thermal power plant during turndown intervals , the system comprising:a. a gas turbine having a compressor, at least one combustor downstream from the compressor and a turbine downstream from the combustor, the combustor being connected to a fuel supply control system; andb. a sensor disposed within the thermal power plant; i. receive a user input corresponding to a value for an operational boundary condition of the thermal power plant;', 'ii. monitor ambient conditions using the sensor;', 'iii. generate a predicted emissions level value for the gas turbine based on the monitored ambient conditions; and', 'iv. generate a command signal to adjust at least one operational parameter of the gas turbine, the command signal being based at least in part on the predicted emissions level value and the value of the operational boundary condition of the thermal power plant., 'c. a controller in communication with the sensor and the fuel supply control system, the controller being configured to2. The system as in claim 1 , wherein ...

Подробнее
Номер записи: 49
07-03-2019 дата публикации

Integrated fuel pump and control preservation system

Номер: US20190072041A1
Автор: Brian Cabello, Michael Meagher, Steven S. Sperling
Принадлежит: United Technologies Corp

A portable fuel preservation system is disclosed. The portable fuel preservation system may comprise a switch box configured to be coupled to an integrated fuel pump and control of a gas turbine engine. The switch box may comprise a circuit configured to cause a metering valve and a solenoid valve of the integrated fuel pump and control to open. A driver may be configured to inject preservation fluid into the integrated fuel pump and control.

Подробнее
Номер записи: 50
18-03-2021 дата публикации

GAS TURBINE ENGINE

Номер: US20210079807A1
Автор: BRADBROOK Stephen J.
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine comprising: a combustor configured to initiate combustion; and a turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes; wherein at least one of the passageways is provided with a restrictor which defines a temporary gas washed surface for the stator vane ring and is configured to be ablated upon initiation of combustion to reveal an operational gas washed surface of the stator vane ring. A method of starting a gas turbine engine is also described. 1. A gas turbine engine comprising:a combustor configured to initiate combustion; anda turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes;wherein at least one of the passageways is provided with a restrictor which defines a temporary gas washed surface for the stator vane ring and is configured to be ablated upon initiation of combustion to reveal an operational gas washed surface of the stator vane ring.2. The gas turbine engine of claim 1 , wherein the passageway comprises circumferentially extending endwalls between adjacent vanes; and wherein the restrictor is provided on an operational gas washed surface of the endwalls.3. The gas turbine engine of claim 1 , wherein the restrictor is a coating provided on the endwalls claim 1 , and wherein the coating at least partially covers an operational gas washed surface of the endwalls.4. The gas turbine engine of claim 3 , wherein the coating is formed from tin or an alloy of lead and tin.5. The gas turbine engine of claim 1 , wherein the restrictor is provided on the operational gas washed surface of a vane delimiting the passageway.6. The gas turbine engine of claim 5 , wherein the restrictor is a coating provided on a vane delimiting the passageway and wherein the coating at least partially covers the operational gas washed surface of the respective vane.7. The gas turbine engine of claim 6 , wherein the coating completely covers the operational gas washed surface ...

Подробнее
Номер записи: 51
12-06-2014 дата публикации

FUEL CONTROL MODULE

Номер: US20140157780A1
Автор: Landrum Gregory Lee, Stratton Darren Matthew
Принадлежит: Solar Turbines Incorporated

A fuel control module for a gas turbine engine and method of installation. The fuel control module includes a first frame unit, a second frame unit, a fuel path, and a fuel controller components. The first frame unit and the second frame unit include features for installation in multiple installations and/or multiple configurations. 1. A fuel control module for a gas turbine engine , the fuel control module comprising:a primary fuel shut-off valve;a main fuel control valve;a first frame unit, the first frame unit including a first base, a first inner side, and a first outer side, the first inner side and the first outer side joined to opposite sides of the first base and extending perpendicularly from the first base in the same direction, the first base having a first centerline normal to both the first inner side and the first outer side, the first frame unit further including a fuel inlet fluidly aligned with the first centerline and located distal to the first inner side; anda second frame unit, the second frame unit including a second base, a second inner side, and a second outer side, the second inner side and the second outer side joined to opposite sides of the second base and extending perpendicularly from the second base in the same direction, the second inner side configured to align and couple with the first inner side, the second base having a second centerline normal to both the second inner side and the second outer side, the second frame unit further including a fuel outlet configured to deliver fuel to the gas turbine engine and located distal to the second inner side.2. The fuel control module of claim 1 , further comprising:an upstream fuel interface fixed to the first frame unit and fluidly aligned with the first centerline; anda downstream fuel interface fixed to the second frame unit and fluidly aligned with the second centerline, the downstream fuel interface configured to be detachably coupled to the upstream fuel interface.3. The fuel control ...

Подробнее
Номер записи: 52
12-06-2014 дата публикации

Split fuel control module

Номер: US20140157784A1
Автор: Darren Matthew Stratton, Gregory Lee Landrum
Принадлежит: Solar Turbines Inc

A split fuel control module for a gas turbine engine and method of installation. The split fuel control module includes a first frame unit, a second frame unit, a segmented fuel path, and a distributed fuel controller. The first frame unit and the second frame unit are joined together at a frame unit interface. The segmented fuel path includes an upstream fuel interface fixed to the first frame unit and a downstream fuel interface fixed to the second frame unit and detachably coupled to the upstream fuel interface at the frame unit interface. A first portion of the distributed fuel controller is fixed to the first frame unit, and a second portion of the distributed fuel controller is fixed to the second frame unit.

Подробнее
Номер записи: 53
12-06-2014 дата публикации

CONTROLLING COMBUSTION SYSTEM WITH FUEL CHEMICAL INDUCTION TIME

Номер: US20140157786A1
Автор: Washam Roy Marshall
Принадлежит: GENERAL ELECTRIC COMPANY

A gas turbine system includes a gas turbine including a combustor for combusting a fuel and a control assembly configured to control at least one of a fuel system and the combusting of the combustor based on providing values corresponding to at least one of fuel characteristics and combustor characteristics to a fuel induction time transfer function. 1. A gas turbine system , comprising:a gas turbine including a combustor for combusting a fuel; anda control assembly configured to control at least one of a fuel system and the combustor based on providing at least one of fuel characteristic values and combustor characteristic values to a fuel induction time transfer function.2. The gas turbine system of claim 1 , wherein control assembly is configured to calculate the fuel induction time transfer function based on pre-defined ranges of fuel characteristic values and combustor characteristic values.3. The gas turbine system of claim 2 , wherein the control assembly is configured to receive the pre-defined ranges of the fuel characteristic values and the combustor characteristic values from at least one of a user input and an external device connected to the control assembly.4. The gas turbine system of claim 1 , wherein the control assembly is configured to measure fuel characteristics and combustor characteristics and to control at least one of the fuel system and the combustor based on a fuel induction time value resulting from providing at least one of measured fuel characteristic values and measured combustor characteristic values to the fuel induction time transfer function.5. The gas turbine system of claim 1 , wherein the control assembly is configured to control at least one of the fuel system and the combustor based on providing a fuel induction time value generated by the fuel induction time transfer function to a gas turbine control model claim 1 , and to generate at least one of fuel system control signals and combustor control signals based on outputs ...

Подробнее
Номер записи: 54
23-03-2017 дата публикации

GAS TURBINE ACTIVE COMBUSTION INSTABILITY CONTROL SYSTEM

Номер: US20170082035A1
Автор: Geiger David
Принадлежит:

A turbine active combustion instability control system comprising a primary passage to a combustor of a turbine; a combustor pressure sensor configured to measure dynamic pressure within the combustor; a pilot valve metering fuel flow through a pilot passage to the combustor and comprising a valve seat defining a throat in the pilot passage and a valve plug movable to control fuel flow through the throat, the pilot valve having an inlet passage with a contoured surface to accelerate gas flow through the throat to at least Mach 1; a dynamic linear motor actuator connected to the valve plug and configured to actuate the valve plug at a high frequency; and a controller configured to provide a control signal to the actuator as a function of input from the combustor pressure sensor. 1. A gas turbine active combustion instability control system comprising:a primary fuel flow passage to a combustor of a combustion turbine;a combustor pressure sensor configured to measure a dynamic pressure within said combustor;a pilot fuel flow passage to said combustor; a pilot metering valve body having a valve seat defining a throat in said pilot flow passage between said upstream side and said downstream side;', 'a pilot metering valve plug movable relative to said pilot metering valve body from an open position to a closed seated position to control fuel flow through said throat from said upstream side to said downstream side;', 'said pilot metering valve body having an inlet passage on said upstream side of said throat, said inlet passage having a contoured surface generally angled to narrow toward said throat and to accelerate gas flow through said throat to at least Mach 1;', 'said pilot metering valve body having an outlet passage on said downstream side of said throat;, 'a pilot control valve configured to meter fuel flow through said pilot flow passage to said combustor from an upstream side to a downstream side, said pilot control valve comprisinga dynamic linear motor ...

Подробнее
Номер записи: 55
31-03-2022 дата публикации

Gas Turbine and Method for Adjusting Flow Rate of Fuel Supplied Thereto

Номер: US20220099033A1
Автор: HAGITA Tatsuya, KARISHUKU Mitsuhiro, KATO Masaya, NAITO Keita, TANIMURA Satoshi
Принадлежит:

A gas turbine including a fuel gas supply system to supply fuel gas via a fuel piping to a gas turbine combustor, a pressure control valve installed halfway along the fuel piping, a flow control valve installed in the fuel piping at downstream of the pressure control valve, and a control device configured that in a case where a flow rate change occurs in the fuel gas flowing through the fuel gas supply system, along with a tendency of change in an opening degree of the pressure control valve or a pressure P1 at upstream of the pressure control valve, a command value of the flow rate of the fuel gas that is determined based on a demand value of a gas turbine load is adjusted so that the change is suppressed in the opening degree of the pressure control valve or the pressure P1. 1. A gas turbine comprising:a fuel gas supply system configured to supply fuel gas from a fuel supply equipment via a fuel piping to a gas turbine combustor;a pressure control valve installed halfway along the fuel piping to control pressure of the fuel gas;a flow control valve installed in the fuel piping at a downstream side of the pressure control valve to control a flow rate of the fuel gas; and{'b': ['1', '1'], '#text': 'a control device configured that in a case where a flow rate change occurs in the fuel gas flowing through the fuel gas supply system, along with a tendency of change in an opening degree of the pressure control valve or a pressure P at an upstream side of the pressure control valve, a command value of the flow rate of the fuel gas that is determined based on a demand value of a gas turbine load is adjusted so that the change is suppressed in the opening degree of the pressure control valve or the pressure P at the upstream side of the pressure control valve.'}2. The gas turbine according to claim 1 ,wherein a fuel gas extraction line to other equipment and a fuel gas return line from the other equipment are connected to upstream of the fuel gas supply system, and ...

Подробнее
Номер записи: 56
19-06-2014 дата публикации

ACTIVE CONTROL FUEL NOZZLE SYSTEM

Номер: US20140165576A1
Автор: Antoniono Carolyn, Chen Wei, LIPINSKI John, McManus Keith
Принадлежит: GENERAL ELECTRIC COMPANY

It is desirable for a gas turbine system to operate in a wide range operating conditions. However, under certain conditions there exist dynamic boundaries that limit a combustor from reaching its designated condition. Perturbation devices formed of electromagnetic plates can be incorporated into fuel nozzles of the combustor to influence the dynamics so that the range of operating conditions can be widened. The perturbation devices vibrate according to the perturbation signals provided from a dynamics controller. The vibration characteristics of the perturbation devices can be controlled by controlling the attributes of the perturbation signals. The vibrations influence the dynamics of fluid—fuel, oxidant, or both—flowing past the perturbation devices within the fuel nozzles. 1. A perturbation device for use in a fuel nozzle of a combustor of a gas turbine system , the perturbation device comprising:a plurality of flexible plates including first and second flexible plates, both the first and second flexible plates being electromagnetic plates,wherein the first and second flexible plates are respectively structured to receive first and second perturbation signals and generate corresponding first and second magnetic fluxes,wherein the first and second flexible plates are physically disposed relative to each other such that one or both of the first and second flexible plates vibrate due to an interaction between the first and second magnetic fluxes, andwherein the first flexible plate is structured to receive an AC signal as the first perturbation signal and generate a corresponding AC magnetic flux as the first magnetic flux.2. The perturbation device of claim 1 , wherein one of the first and second flexible plates is structured to be stationary and the other of the first and second flexible plates is structured to vibrate due to the interaction between the first and second magnetic fluxes.3. The perturbation device of claim 1 , wherein the second flexible plate is ...

Подробнее
Номер записи: 57
19-06-2014 дата публикации

High Pressure Turbine Speed Calculation from Fuel System Hydraulic Pressures

Номер: US20140165579A1
Автор: Selstad Tyler J.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

The speed of a high-pressure turbine of a gas turbine engine may be determined using known centrifugal pump affinity relationships for a fuel pressure apparatus, fuel pressure apparatus input and output pressures, and gear ratios for a mechanical linkage between the high-pressure turbine and the fuel pressure apparatus. The technique avoids wear-related variations in gas pressure based measurements and also applies to fuel pressure apparatus using both single pump and multiple pump configurations. 1. A method of determining a speed of a high pressure turbine in a gas turbine engine , the method comprising:providing a nominal output fuel pressure of a fuel pressure apparatus when the high pressure turbine is operating at a nominal speed;determining a first fuel pressure at an input of the fuel pressure apparatus that supplies fuel to a combustion chamber of the gas turbine engine;determining a second fuel pressure at an output of the fuel pressure apparatus; andcalculating the speed of the high pressure turbine as a quadratic relationship of the first fuel pressure of the fuel pressure apparatus and the second fuel pressure of the fuel pressure apparatus.2. The method of claim 1 , wherein the fuel pressure apparatus is a single stage centrifugal pump.3. The method of claim 2 , further comprising calculating a shaft speed of the single stage centrifugal pump claim 2 , wherein calculating the speed of the high pressure turbine is a function of the shaft speed and a gear ratio of a gear box coupling the high pressure turbine and the single stage centrifugal pump.4. The method of claim 1 , wherein the fuel pressure apparatus is a multiple stage pump including a plurality of centrifugal pumps.5. The method of claim 4 , further comprising driving each stage of the multiple stage pump at a common speed proportional to a gear ratio of a gear box coupling the high pressure turbine and the multiple stage pump.6. A system for determining a speed of a high pressure turbine in a ...

Подробнее
Номер записи: 58
19-06-2014 дата публикации

FUEL ROUTING SYSTEM OF A GAS TURBINE ENGINE AND METHOD OF ROUTING FUEL

Номер: US20140165580A1
Автор: Shinkle William Randolph, Simmons James Arthur
Принадлежит: GENERAL ELECTRIC COMPANY

A fuel routing system of a gas turbine engine includes a primary fuel circuit in communication with a fuel source and a fuel distribution manifold. Also included is a secondary fuel circuit extending from the primary fuel circuit to a plurality of fuel nozzles configured to direct fuel to a plurality of combustor chambers. Further included is a main fuel flow control valve disposed in the primary fuel circuit for restricting a fuel flow to the fuel distribution manifold upon removal of an electrical load operably coupled to the gas turbine engine. Yet further included is a plurality of check valves disposed between the secondary fuel circuit and the primary fuel circuit for restricting the fuel flow between the secondary fuel circuit and the primary fuel circuit. 1. A fuel routing system of a gas turbine engine comprising:a primary fuel circuit feeding a fuel distribution manifold which directs fuel to a combustor chamber;a secondary fuel circuit extending from the primary fuel circuit to a plurality of fuel nozzles configured to direct fuel to the combustor chamber;a main fuel flow control valve disposed in the primary fuel circuit for restricting a fuel flow to the fuel distribution manifold upon removal of an electrical load operably coupled to the gas turbine engine; anda plurality of check valves located between the secondary fuel circuit and the primary fuel circuit for restricting the fuel flow from the secondary fuel circuit to the primary fuel circuit.2. The fuel routing system of claim 1 , wherein the secondary fuel circuit comprises a plurality of fuel lines each in communication with one of the plurality of fuel nozzles.3. The fuel routing system of claim 1 , wherein the plurality of fuel nozzles comprises a portion of a total number of fuel nozzles of the gas turbine engine.4. The fuel routing system of claim 3 , wherein the portion of the total number of fuel nozzles is a subset of the total number of fuel nozzles.5. The fuel routing system of claim 1 ...

Подробнее
Номер записи: 59
25-03-2021 дата публикации

SYSTEMS AND METHODS FOR STARTING A GAS TURBINE ENGINE

Номер: US20210087972A1
Автор: Sabau Ioan, Turcotte Jasmin
Принадлежит:

Methods and systems for starting an aircraft gas turbine engine are described. The method comprises, in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up; in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; and in a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine. 1. A method for starting an aircraft gas turbine engine , the method comprising:in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up;in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; andin a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine.2. The method of claim 1 , wherein the second phase is initiated when light-up is detected claim 1 , and the third phase is initiated when the conditions for light-around are met.3. The method of claim 1 , further comprising claim 1 , in a fourth phase of the startup claim 1 , modifying a fourth set of engine control parameters to transition to a closed loop fuel control.4. The method of claim 3 , wherein the fourth phase is initiated when complete ignition is detected.5. The method of claim 1 , wherein modifying the first set of engine control parameters comprises applying an adaptive fuel flow logic as a function of a first set of operating parameters.6. The method of claim 5 , wherein modifying the first set of engine control parameters further comprises transitioning variable geometry mechanisms (VGMs) of the engine from a windmilling position to an ignition position and setting an ignition frequency based on a second set of operating parameters.7. The method of claim 1 , wherein ...

Подробнее
Номер записи: 60
25-03-2021 дата публикации

FUEL METERING CIRCUIT AND METHOD WITH COMPENSATION FOR FUEL-DENSITY VARIABILITY

Номер: US20210087980A1
Автор: JOUDAREFF Arnaud Bernard Clement Thomas, Pora Loïc
Принадлежит: SAFRAN AIRCRAFT ENGINES

A fuel metering circuit for a turbomachine includes: a meter; a pump; a control valve configured to return an excess flow of fuel delivered to the meter towards the pump on the basis of a fuel pressure differential at the terminals of the meter; a diaphragm; and a volumetric flow meter. The diaphragm and the volumetric flow meter are mounted parallel to the meter, downstream of the control valve, in order to determine a density of the fuel flowing in the metering circuit. 1. A fuel metering circuit for a turbomachine comprising:a metering device;a pump configured to circulate a fuel flow rate toward the metering device;a regulating valve configured to return an excess fuel flow rate delivered to the metering device toward the pump according to a difference in fuel pressure at terminals of the metering device;a diaphragm; anda volume flow meter configured to determine a volume flow rate of fuel passing through the diaphragm,wherein the diaphragm and the volume flow meter are mounted in parallel with the metering device in a bypass duct, downstream of the regulating valve, in order to determine a density of the fuel circulating in the metering circuit.2. The metering circuit according to claim 1 , wherein the volume flow meter is mounted upstream or downstream of the diaphragm.3. The metering circuit according to claim 1 , further comprising an electronic card configured to receive information from the volume flow meter on the volume flow rate of the fuel and adjust a metering device monitoring setpoint by taking into account the fuel density thus determined.4. The metering circuit according to claim 1 , wherein the pump comprises a volumetric pump.5. A turbomachine comprising a fuel metering circuit according to .6. A fuel metering method implemented in a fuel metering circuit according to claim 1 , the method comprising:determining the difference in fuel pressure at the terminals of the metering device;measuring the volume flow rate of the fuel using the volume flow ...

Подробнее
Номер записи: 61
31-03-2016 дата публикации

METHOD OF STOPPING A ROTORCRAFT ENGINE IN OVERSPEED, AND A SYSTEM AND A ROTORCRAFT ASSOCIATED THEREWITH

Номер: US20160090187A1
Автор: Certain Bernard
Принадлежит:

A method of stopping an engine of a rotorcraft in overspeed, the engine comprising a gas generator and a power assembly. When the engine is in operation, a relationship is established giving a limit derivative that varies as a function of the speed of rotation of the power assembly. The speed of rotation, referred to as the “current speed”, reached by the power assembly is measured and the time derivative of the speed of rotation is determined and referred to as the “current derivative”. The engine is stopped automatically when the limit derivative corresponding to the current speed as determined by the relationship is less than or equal to the current derivative. 12. A method of stopping an engine of a rotorcraft in overspeed , the rotorcraft including at least one engine , the engine comprising a gas generator and a power assembly , the power assembly having at least one power turbine set in rotation by gas coming from the gas generator , the power assembly having at least one power shaft constrained to rotate with the power turbine , the power assembly being rotatable about a longitudinal axis at a speed referred to as the “speed of rotation (N)”;wherein:prior to a flight, a relationship is determined that provides a time derivative of the speed of rotation referred to as a time “limit derivative”, over at least one range of speeds of rotation, the limit derivative according to the relationship being a function of the speed of rotation and varying as a function of the speed of rotation; and wherein the speed of rotation reached by the power assembly is measured, and referred to as the “current” speed;', 'the time derivative of the speed of rotation is determined, and referred to as the “current” derivative; and', 'when the current speed is located in a said range specified by the relationship, the engine is stopped automatically when the limit derivative corresponding to the current speed in application of the relationship is less than or equal to the current ...

Подробнее
Номер записи: 62
30-03-2017 дата публикации

TRANSIENT EMISSION TEMPERATURE CONTROL OF TURBINE SYSTEMS

Номер: US20170089267A1
Автор: Arthanari Akilez Krishnamurthy, Harper James
Принадлежит:

In one embodiment, a system is provided. The system includes a turbine control system, comprising a processor. The processor is configured to receive an input for transitioning between a normal load path (NLP) of a turbine system and a cold load path (CLP) of the turbine system. The processor is additionally configured to determine a carbon monoxide (CO) setpoint based on the input. The processor is further configured to apply a temperature control based on the CO setpoint, wherein the normal load path comprises higher emissions temperatures as compared to the cold load path. 1. A system comprising:a turbine control system, comprising a processor configured to:receive an input for transitioning between a normal load path (NLP) of a turbine system and a cold load path (CLP) of the turbine system;determine a carbon monoxide (CO) setpoint based on the input; andapply a temperature control based on the CO setpoint, wherein the normal load path comprises higher emissions temperatures as compared to the cold load path.2. The system of claim 1 , wherein the processor is configured to determine the CO setpoint by setting a CO target temperature to a factor above a predicted CO level or above a regulatory CO level.3. The system of claim 2 , wherein the factor comprises between 0.08 and 1.2.4. The system of claim 2 , wherein the processor is configured to maintain the CO target temperature for a time period.5. The system of claim 4 , wherein the processor is configured to lower the CO target temperature after expiration of the time period.6. The system of claim 1 , wherein the processor is configured to determine the CO setpoint by adding a bias to a CO controller.7. The system of claim 1 , wherein the processor is configured to determine the CO setpoint by determining an exhaust temperature of an exhaust exiting the turbine system.8. The system of claim 1 , wherein the processor is configured to determine if the turbine system is operating at the cold load path claim 1 , and ...

Подробнее
Номер записи: 63
01-04-2021 дата публикации

GAS TURBINE ENGINE

Номер: US20210095602A1
Автор: Brown David, CALDERON Jorge
Принадлежит:

A gas turbine engine for an aircraft. The engine comprising: an engine core comprising a turbine, a compressor, a fan located upstream of the compressor and comprising a plurality of fan blades, and a core shaft connecting the turbine to the compressor; a gearbox which receives an input from the core shaft and outputs drive, via a driveshaft, to the fan so as to drive the fan at a lower rotational speed than the turbine, the drive shaft and core shaft forming a shaft system. The shaft system provides: a first portion which extends forward from a first thrust bearing to the fan, the first thrust bearing supporting the shaft system and being located between the turbine and the gearbox, and a second portion extending rearward from the first thrust bearing to the turbine, such that in the event of a shaft break within the second portion of the shaft system, said shaft break dividing the shaft system into a front portion axially located by the first thrust bearing and a rear portion no longer axially located by the first thrust bearing, the rear portion is free to move axially rearwardly under a gas load; and wherein the engine further comprises a shaft break detector, configured to detect a shaft break in the shaft system. 1. A gas turbine engine for an aircraft comprising:an engine core comprising a turbine, a compressor, a fan located upstream of the compressor and comprising a plurality of fan blades, and a core shaft connecting the turbine to the compressor; a first portion which extends forward from a first thrust bearing to the fan, the first thrust bearing supporting the shaft system and being located between the turbine and the gearbox, and', 'a second portion extending rearward from the first thrust bearing to the turbine, such that in the event of a shaft break within the second portion of the shaft system, said shaft break dividing the shaft system into a front portion axially located by the first thrust bearing and a rear portion no longer axially located by ...

Подробнее
Номер записи: 64
28-03-2019 дата публикации

ELECTRONIC FUEL CONTROL FOR GAS TURBINE ENGINES

Номер: US20190093569A1
Автор: PROCIW Lev Alexander, Ryon Jason A.
Принадлежит:

A fuel injector for a gas turbine engine includes a feed arm defining a conduit extending between an inlet end and an outlet end and a plunger. The plunger is disposed within the conduit and is movable between a plunger first position and a plunger second position. A flow area defined between the plunger and the feed arm is smaller in the plunger first position than in the plunger second position to bias fuel flow through the fuel injector. Fuel systems, gas turbine engines, and methods of controlling fuel flow in gas turbine engine fuel systems are also described. 1. A fuel injector for a gas turbine engine , comprising:a feed arm defining a conduit extending an inlet end and an outlet end; anda plunger disposed within the conduit and movable between a plunger first position and a plunger second position,wherein the plunger and conduit define between one another a flow area that is smaller in the plunger second position than in the plunger first position.2. The fuel injector as recited in claim 1 , further comprising an electrical actuator operably connected to the plunger and arranged to move the plunger relative to the feed arm.3. The fuel injector as recited in claim 2 , wherein the electrical actuator is appurtenant to the fuel injector.4. The fuel injector as recited in claim 2 , wherein the electrical actuator is severable from the fuel injector.5. The fuel injector as recited in claim 2 , further comprising a rotary drive coupling the electrical actuator to the plunger and arranged to rotate the plunger relative to the feed arm.6. The fuel injector as recited in claim 2 , wherein the electrical actuator includes a solenoid claim 2 , a rotary motor claim 2 , or a stepper motor.7. The fuel injector as recited in claim 1 , wherein the feed arm has female threads engagable with the plunger.8. The fuel injector as recited in claim 7 , wherein the plunger has male threads engagable with the female threads of the feed arm.9. The fuel injector as recited in claim 7 ...

Подробнее
Номер записи: 65
05-04-2018 дата публикации

SYSTEM AND METHOD FOR MODEL BASED TURBINE SHAFT POWER PREDICTOR

Номер: US20180097463A1
Автор: Minto Karl Dean, Pobbati Omprakash, UNNIKRISHNAN Sunil
Принадлежит:

In an embodiment, a control system includes a processor. The processor is configured to receive signals from one or more sensors disposed in a gas turbine system, wherein the gas turbine system comprises a shaft mechanically coupled to an electric generator. The processor is further configured to predict a derived mechanical power for the shaft based on the signals. The processor is additionally configured to derive a power adjustment by executing at least one model. The processor is also configured to derive a corrected mechanical power by applying the power adjustment to the derived mechanical power; and to control the gas turbine system based on the corrected mechanical power. 1. A control system , comprising: receive signals from one or more sensors disposed in a gas turbine system, wherein the gas turbine system comprises a shaft mechanically coupled to an electric generator;', 'predict a derived mechanical power for the shaft based on the signals;, 'a processor, wherein the processor is configured to derive a corrected mechanical power by applying the power adjustment to the derived mechanical power; and', 'control the gas turbine system based on the corrected mechanical power, wherein the processor is configured to predict the derived mechanical power by executing a turbine model using the signals as input to the turbine model, wherein the processor is configured to derive the power adjustment by executing the turbine model to predict the derived mechanical power and to provide the derived mechanical power as input to a shaft model, wherein the shaft model derives a speed prediction for the shaft based on the derived mechanical power and on an instantaneous wattage measurement of electrical power produced by the electric generator., 'derive a power adjustment by executing at least one model;'}2. The system of claim 1 , wherein the turbine model comprises a thermodynamic model claim 1 , a fluid model claim 1 , a low cycle fatigue (LCF) life prediction model ...

Подробнее
Номер записи: 66
23-04-2015 дата публикации

GAS TURBINE WITH SEQUENTIAL COMBUSTION ARRANGEMENT

Номер: US20150107259A1
Автор: Eroglu Adnan, HOFFMANN Juergen
Принадлежит:

The present disclosure refers to a method for operating a gas turbine with sequential combustors having a first-burner, a first combustion chamber, and a second combustor arranged sequentially in a fluid flow connection. To minimize emissions and combustion stability problems during transient changes when the fuel flow to a second combustor is initiated the method includes the steps of increasing the second fuel flow to a minimum flow, and reducing the first fuel flow to the first-burner of the same sequential combustor and/or the fuel flow to at least one other sequential combustor of the sequential combustor arrangement in order keep the total fuel mass flow to the gas turbine substantially constant. Besides the method a gas turbine with a fuel distribution system configured to carry out such a method is disclosed. 1. A method for operating a gas turbine having at least a compressor , a sequential combustor arrangement with a plurality of sequential combustors , and a turbine downstream of the sequential combustor arrangement , each sequential combustor having a first-burner , a first combustion chamber , and a second combustor arranged sequentially in a fluid flow connection , the method comprising:compressing the inlet gas in the compressor,admixing a first fuel in the first-burners of the sequential combustor,burning the mixture of first fuel and compressed gas in the first combustion chamber to obtain first combustion products,wherein at low relative load no further fuel is injected into the sequential combustor downstream of the first-burner, and at high relative load a second fuel is injected into the sequential combustor downstream of the first combustion chamber, andburning the mixture of first combustion products, and the second fuel to obtain second combustor combustion products, and expanding the combustion products in the turbine,wherein during part load operation of the gas turbine when initiating fuel admittance of the second fuel the second fuel ...

Подробнее
Номер записи: 67
08-04-2021 дата публикации

ELECTRIC PUMP ASSISTED FUEL SYSTEM

Номер: US20210102517A1
Автор: Bayles Robert A., Mastrocola Naison E., Miles Gary L., Peters Jesse C., Reuter Charles E., Stoicescu Adrian L., Susca Ryan
Принадлежит:

A fuel system for an engine including a first flow line, an electrically driven startup pump in fluid communication with the first flow line to provide a startup flow, a main flow line, a main pump in fluid communication with the main flow line to provide a main flow, and a switching valve connected to the first flow line and the main flow line, the switching valve configured to select between the first flow line and the main flow line to output either the startup flow or the main flow. 1. A fuel system for an engine , comprising:a first flow line;an electrically driven startup pump in fluid communication with the first flow line to provide a startup flow;a main flow line;a main pump in fluid communication with the main flow line to provide a main flow; anda switching valve connected to the first flow line and the main flow line, the switching valve configured to select between the first flow line and the main flow line to output either the startup flow or the main flow.2. The fuel system of claim 1 , further comprising an electric motor configured to drive the electrically driven startup pump.3. The fuel system of claim 1 , wherein the electrically driven startup pump is a gear pump claim 1 , a centrifugal pump claim 1 , or a regenerative pump.4. The fuel system of claim 1 , further comprising a pressure regulating valve in fluid communication with the electrically driving startup pump and configured for switching between a first position and a second position.5. The fuel system of claim 1 , wherein the switching valve is configured to switch between a first position wherein the switching valve selects the first flow line to pass the startup flow and a second position wherein the switching valve selects the main flow line as a function of pressure differential between the main flow and the startup flow.6. The fuel system of claim 1 , wherein when the startup flow is at a higher pressure than the main flow claim 1 , the switching valve is biased to the first ...

Подробнее
Номер записи: 68
13-04-2017 дата публикации

EXCHANGEABLE ORIFICE BINARY VALVE

Номер: US20170102719A1
Автор: Feinstein Michael, Halusic, III Edward John, Kemmerer Alan James
Принадлежит:

A system includes a fluid valve metering system which regulates a flow of a fluid within a gas turbine engine. The fluid valve metering system includes an inlet manifold, an outlet manifold in fluid communication with the inlet manifold, and multiple fluid conduits extending between the inlet manifold and the outlet manifold. Each respective fluid conduit of the multiple fluid conduits includes a respective fluid conduit valve of the multiple fluid conduit valves. Each fluid conduit valve regulates fluid the flow of the fluid through the respective fluid conduit. The fluid valve metering system also includes multiple differently sized orifices and a controller. The controller is coupled to the fluid valve metering system and programmed to monitor a usage of each orifice of multiple differently sized orifices, of each fluid conduit valve of multiple fluid conduit valves, or a combination thereof. 1. A system , comprising: an inlet manifold;', 'an outlet manifold in fluid communication with the inlet manifold;', 'a plurality of fluid conduits extending between the inlet manifold and the outlet manifold, wherein each respective fluid conduit of the plurality of fluid conduits comprises a respective fluid conduit valve of a plurality of fluid conduit valves configured to regulate the flow of the fluid through the respective fluid conduit; and', 'a plurality of differently sized orifices, and, 'a fluid valve metering system configured to regulate a flow of a fluid within a gas turbine engine, comprisinga controller coupled to the fluid valve metering system and programmed to monitor a usage of each orifice of the plurality of differently sized orifices, of each fluid conduit valve of the plurality of fluid conduit valves, or a combination thereof.2. The system of claim 1 , wherein the controller is programmed to open and close each orifice plate line valve of the plurality of orifice plate line valves to regulate the flow of the fluid through the fluid valve metering ...

Подробнее
Номер записи: 69
19-04-2018 дата публикации

Systems and methods for predicting fuel circuit leaks

Номер: US20180106197A1
Автор: Akilez Krishnamurthy Arthanari, James Harper
Принадлежит: General Electric Co

A system includes a combustor assembly which receives a fuel-oxidant mixture. The system includes a control valve which controls a fuel flow into the combustor assembly. The system includes one or more sensors which measure one or more properties. The system includes a controller communicatively coupled to the one or more sensors and the control valve. The controller receives data from the one or more sensors indicative of operating conditions of the combustor assembly. The controller determines a predicted fuel flow for a first fuel line of a plurality of fuel lines based in part on the data received from the one or more sensors. The controller calculates a difference between a commanded fuel flow and the predicted fuel flow. The controller adjusts an operation of the control valve associated with a gas turbine engine when the difference is greater than a threshold.

Подробнее
Номер записи: 70
10-07-2014 дата публикации

FUEL CONTROL METHOD AND FUEL CONTROL APPARATUS FOR GAS TURBINE AND GAS TURBINE

Номер: US20140190176A1
Автор: Akamatsu Shinji, Kishi Makoto, Nakamura Shinsuke, Nakamura Sosuke, Saito Akihiko, SONODA Takashi, TANIMURA Satoshi
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced. Because fuel is supplied from the main nozzles of all groups and burned in the entire area of the combustor upon ignition, it is possible to easily propagate a flame to all the other adjacent main nozzle groups, thereby improving the ignition characteristics of the whole gas turbine. 15-. (canceled)6. A fuel control method for a gas turbine being formed of at least two groups of pluralities of main nozzles for supplying fuel , the fuel control method for a gas turbine comprising:during ignition and acceleration but before loading of the gas turbine, supplying fuel from the main nozzles of all groups upon ignition of the combustor but before loading of the gas turbine, and after the ignition of the combustor, while keeping supply of the fuel from the main nozzles of at least one group excluding all groups, stopping supply of the fuel from the main nozzles of other group(s) during acceleration of the gas turbine.7. The fuel control method for a gas turbine according to claim 6 , wherein the main nozzles of the group that supply fuel during acceleration of the gas turbine are adjacently arranged to each other.8. The fuel control method for a gas turbine according to claim 6 , wherein number of the ...

Подробнее
Номер записи: 71
02-04-2020 дата публикации

FUEL METERING UNIT

Номер: US20200102893A1
Автор: Berry Erin E.
Принадлежит:

A fuel metering unit includes a metering valve and a sensor. The metering valve includes a valve body movably disposed within a valve housing. The valve body defines a first bore that extends from a first valve body end towards a second valve body end along a first axis and a first window that extends through the valve body along a second axis. The sensor extends at least partially through the valve housing and faces towards the first window. The sensor being arranged to provide a signal indicative of a position of the first window relative to the sensor. 1. A fuel metering unit , comprising: 'a valve body movably disposed within a valve housing, the valve body defining a first bore that extends from a first valve body end towards a second valve body end along a first axis and a first window that extends through the valve body along a second axis; and', 'a metering valve, comprisinga sensor extending at least partially through the valve housing and facing towards the first window, the sensor being arranged to provide a signal indicative of a position of the first window relative to the sensor.2. The fuel metering unit of claim 1 , wherein the first bore is fluidly connected to the first window.3. The fuel metering unit of claim 1 , wherein the valve housing defines a bypass port that is spaced apart from the sensor.4. The fuel metering unit of claim 3 , wherein the first window is selectively fluidly connected to the bypass port.5. The fuel metering unit of claim 1 , wherein the sensor is a proximity probe.6. The fuel metering unit of claim 1 , wherein the valve body defines a first recessed region that extends from an outer surface of the valve body towards the first bore.7. The fuel metering unit of claim 6 , wherein the first recessed region includes a first face claim 6 , a second face claim 6 , and a monitoring surface that extends between the first face and the second face.8. The fuel metering unit of claim 7 , wherein the monitoring surface is disposed ...

Подробнее
Номер записи: 72
02-04-2020 дата публикации

CONTROL AND TUNING OF GAS TURBINE COMBUSTION

Номер: US20200102902A1
Автор: Liu Yan, Petro Robert Nicholas, Piche Stephen William, Pickard Fred Francis, Virani Nurali
Принадлежит: GENERAL ELECTRIC COMPANY

A system that includes: a gas turbine having a combustion system; a control system operably connected to the gas turbine for controlling an operation thereof; and a combustion auto-tuner, which is communicatively linked to the control system, that includes an optimization system having an empirical model of the combustion system and an optimizer; sensors configured to measure the inputs and outputs of the combustion system; a hardware processor; and machine-readable storage medium on which is stored instructions that cause the hardware processor to execute a tuning process for tuning the operation of the combustion system. The tuning process includes the steps of: receiving current measurements from the sensors for the inputs and outputs; given the current measurements received from the sensors, using the optimization system to calculate an optimized control solution for the combustion system; and communicating the optimized control solution to the control system. 1. A system comprising:a gas turbine having a combustion system;a control system operably connected to the gas turbine for controlling an operation thereof; and a model, the model comprising an empirical model that models the combustion system via statistically mapping inputs to outputs of an operation of the combustion system so to generate predicted values for the outputs at future times based on the inputs of the combustion system; and', 'an optimizer;, 'an optimization system comprising, 'a combustion auto-tuner communicatively linked to the control system, the combustion auto-tuner comprisingsensors configured to measure the inputs and outputs of the operation of the combustion system;a hardware processor; andmachine-readable storage medium on which is stored instructions that cause the hardware processor to execute a tuning process for tuning the operation of the combustion system; receiving current measurements from the sensors for the inputs and outputs;', 'given the current measurements received ...

Подробнее
Номер записи: 73
27-04-2017 дата публикации

APPARATUS AND METHOD FOR CONTROLLING AND MONITORING AN ELECTRO-HYDRAULIC SERVOVALVE

Номер: US20170114726A1
Автор: Selstad Tyler J.
Принадлежит:

A method for actively calculating a capability of an electronically controlled valve is provided. The method including the steps of: a) operating the electronically controlled valve in accordance with a task; b) testing the electronically controlled valve in order to determine a range of movement of the electronically controlled valve in accordance with an initial gain, wherein the testing of the electronically controlled valve occurs after the valve has been operated in accordance with the task; c) determining a new gain required for providing a predetermined range of movement of the electronically controlled valve; and d) repeating steps a-c at least once, wherein the new gain is used to operate the valve in accordance with the task. 1. A method for calculating a capability of an electronically controlled valve , comprising:a) operating the electronically controlled valve in accordance with a task;b) testing the electronically controlled valve in order to determine a range of movement of the electronically controlled valve in accordance with an initial gain, wherein the testing of the electronically controlled valve occurs after the valve has been operated in accordance with the task;c) determining a new gain required for providing a predetermined range of movement of the electronically controlled valve; andd) repeating steps a-c at least once, wherein the new gain is used to operate the valve in accordance with the task.2. The method as in claim 1 , wherein the task is controlling an amount of fuel provided to a gas turbine engine.3. The method as in claim 1 , wherein the electronically controlled valve is a fuel valve of a gas turbine engine.4. The method as in claim 1 , wherein the new gain is an average of a plurality of gains each being a result of one of a plurality of tests of the electronically controlled valve claim 1 , wherein each one of the plurality of tests determines a range of movement of the electronically controlled valve in accordance with the ...

Подробнее
Номер записи: 74
24-07-2014 дата публикации

OXIDIZING FUEL IN MULTIPLE OPERATING MODES

Номер: US20140202165A1
Автор: PRABHU Edan
Принадлежит: ENER-CORE POWER, INC.

A fuel oxidizer system is operated in a first operating mode. In the first operating mode, a mixture that includes fuel from a fuel source is compressed in a compressor of the fuel oxidizer system; the fuel of the compressed mixture is oxidized in a reaction chamber of the fuel oxidizer system; and the oxidized fuel is expanded to generate rotational kinetic energy. The fuel oxidizer system is operated in a second operating mode. In the second operating mode, fuel from the fuel source is directed to bypass the compressor, and the fuel that bypassed the compressor is oxidized in the reaction chamber. 1. A method comprising: directing fuel from a fuel source to a compressor;', 'compressing a mixture comprising the fuel in the compressor to produce a compressed mixture comprising the fuel;', 'oxidizing the fuel of the compressed mixture in a reaction chamber to produce a first oxidation product; and', 'directing the first oxidation product to a turbine; and', 'expanding the first oxidation product in the turbine to generate rotational kinetic energy; and, 'operating a fuel oxidizer system in a first operating mode, comprising directing fuel from the fuel source to the reaction chamber by bypassing the compressor;', 'oxidizing the fuel in the reaction chamber to produce a second oxidation product; and', 'directing the second oxidation product to an exhaust path by bypassing the turbine., 'operating the fuel oxidizer system in a second operating mode, comprising2. The method of claim 1 , wherein operating the fuel oxidizer system in the first operating mode further comprises outputting electrical energy based on the rotational kinetic energy.3. The method of claim 1 , wherein operating the fuel oxidizer system in the second operating mode comprises operating the fuel oxidizer system as a flare.4. The method of claim 1 , wherein operating the fuel oxidizer system in the second operating mode comprises operating the fuel oxidizer system as a thermal oxidizer.5. The method ...

Подробнее
Номер записи: 75
04-05-2017 дата публикации

System and Method for Determining Fuel Splits for a Gas Turbine

Номер: US20170122222A1
Автор: Kalya Prabhanjana, Mitchell Paul Jeffrey, Punjala Ratna Manedhar
Принадлежит:

A method for determining fuel splits may generally include monitoring an airflow-related parameter of a gas turbine and determining first and second reference values for the airflow-related parameter based on a combustion reference temperature. The first reference value may be associated with a first load path of the gas turbine and the second reference value may be associated with a second load path of the gas turbine. The method may also include determining first and second fuel split commands based on the combustion reference temperature. In addition, the method may include determining a fuel split value to be applied in association with a monitored value of the airflow-related parameter based at least in part on the reference values and the fuel split commands and applying the fuel split value to regulate an amount of fuel supplied to one or more fuel circuits of the gas turbine. 1. A method for determining fuel splits for a gas turbine , the method comprising:monitoring, with a computing device, an airflow-related parameter of the gas turbine;determining, with the computing device, first and second reference values for the airflow-related parameter based on a combustion reference temperature of the gas turbine, the first reference value being associated with a first load path of the gas turbine and the second reference value being associated with a second load path of the gas turbine;determining, with the computing device, first and second fuel split commands based on the combustion reference temperature, the first fuel split command being associated with the first load path of the gas turbine and the second fuel split command being associated with the second load path of the gas turbine;determining, with the computing device, a fuel split value to be applied within the gas turbine in association with a monitored value of the airflow-related parameter based at least in part on the first and second reference values and the first and second fuel split commands; ...

Подробнее
Номер записи: 76
25-04-2019 дата публикации

GAS TURBINE HAVING FUEL GAS MONITORING SYSTEM

Номер: US20190120145A1
Автор: Bunce Richard H., Teehan Damien G.
Принадлежит:

A gas turbine and a method for operating a gas turbine having a fuel gas monitoring system are presented. The fuel gas monitoring system may provide a measurement of a parameter of a fuel gas in real time. An operation of a gas turbine may be optimized to adapt variation in hydrocarbon content of a fuel gas from the measurement. The fuel gas monitoring system may provide an optical, flow through, online monitoring of fuel gas composition. 1. A gas turbine comprising:a compressor that is configured to compress air;a combustor located downstream of the compressor that is configured to receive the compressed air;a fuel gas supply line connected to the combustor that is configured to supply fuel gas to the combustor, wherein the fuel gas and the compressed air are mixed and combusted in the combustor to generate working gas;a turbine located downstream of the combustor that is configured to expend the working gas to generate power output;a fuel gas monitoring system that is configured to provide a measurement of a parameter of the fuel gas in real time, wherein the fuel gas monitoring system comprises an inlet and an outlet, wherein a fuel gas sample flows into the fuel gas monitoring system through the inlet, wherein the fuel gas sample is discharged from the fuel gas monitoring system through the outlet; anda control system that is configured to adjust an operating parameter of the gas turbine based on the measurement of the parameter of the fuel gas.2. The gas turbine as claimed in claim 1 , wherein the fuel gas monitoring system comprises an optical system.3. The gas turbine as claimed in claim 1 , wherein the fuel gas monitoring system is configured to provide an online measurement of the parameter of the fuel gas.4. The gas turbine as claimed in claim 1 , wherein the fuel gas sample is discharged from the fuel gas monitoring system into the fuel gas supply line.5. The gas turbine as claimed in claim 1 , further comprising an upstream pressure regulating device ...

Подробнее
Номер записи: 77
16-04-2020 дата публикации

Fuel metering system

Номер: US20200116084A1
Автор: Jonathan D. PYE
Принадлежит: Rolls Royce PLC

The present disclosure provides a fuel metering system for a gas turbine engine, the fuel metering system comprising: a fuel supply line; a fuel metering valve configured to pass an amount of fuel received from the fuel supply line to the gas turbine engine; a spill line configured to receive excess fuel from the fuel supply line; a spill valve provided in the spill line and configured to control the flow of fuel through the spill line; an engine control unit configured to control the position of the spill valve; a sensor configured to measure the position of the spill valve; wherein the engine so control unit is further configured to identify an uncommanded increase in fuel flow by comparing an expected position of the spill valve to a position of the spill valve measured by the sensor.

Подробнее
Номер записи: 78
01-09-2022 дата публикации

GAS TURBINE ENGINE

Номер: US20220275763A1
Автор: Brown David, CALDERON Jorge
Принадлежит:

A gas turbine engine for an aircraft. The engine including: an engine core with a turbine, a compressor, a fan located upstream of the compressor and including a plurality of fan blades, and a core shaft connecting the turbine to the compressor; a gearbox which receives an input from the core shaft and outputs drive, via a driveshaft, to the fan so as to drive the fan at a lower rotational speed than the turbine, the drive shaft and core shaft forming a shaft system. 1. A gas turbine engine for an aircraft comprising:an engine core comprising a turbine, a compressor, a fan located upstream of the compressor and comprising a plurality of fan blades, and a core shaft connecting the turbine to the compressor; a first portion which extends forward from a first thrust bearing to the fan, the first thrust bearing supporting the shaft system and being located between the turbine and the gearbox, and', 'a second portion extending rearward from the first thrust bearing to the turbine, such that in the event of a shaft break within the second portion of the shaft system, said shaft break dividing the shaft system into a front portion axially located by the first thrust bearing and a rear portion no longer axially located by the first thrust bearing, the rear portion is free to move axially rearwardly under a gas load; and, 'a gearbox which receives an input from the core shaft and outputs drive, via a driveshaft, to the fan so as to drive the fan at a lower rotational speed than the turbine, the drive shaft and core shaft forming a shaft system, wherein the shaft system provideswherein the engine further comprises a shaft break detector, configured to detect a shaft break in the shaft system.2. The gas turbine engine as claimed in claim 1 , wherein the core shaft is supported by one or more non-thrust bearings located rearwards of the first thrust bearing.3. The gas turbine engine as claimed in claim 1 , wherein the first thrust bearing is located such that the pathway for ...

Подробнее
Номер записи: 79
23-04-2020 дата публикации

Direct feedback regarding metered flow of fuel system

Номер: US20200123986A1
Автор: Michael Hahn
Принадлежит: Woodward Inc

The present disclosure describes a fuel system for an engine. The fuel system includes a fuel metering valve, a flow measuring system, and a controller in communication with the fuel metering valve and the flow measuring system. The fuel metering valve is operable to meter a flow rate of fuel based on a stroke of the fuel metering valve. The flow measuring system is configured to measure a mass flow rate of the fuel leaving the fuel system at a bandwidth greater than 20 Hz. The controller is configured to dynamically adjust the stroke of the fuel measuring system based on the mass flow rate of the fuel measured by the flow measuring system to change the flow rate of the fuel.

Подробнее
Номер записи: 80
07-08-2014 дата публикации

Engine fuel control system

Номер: US20140216037A1
Автор: Alexander Macdonald, Mohammad Khalid KHAN, Nigel Herbert Henson
Принадлежит: Rolls Royce Controls and Data Services Ltd

An engine fuel control system includes a metering valve to control fuel flow between the supply and delivery line with a pressure drop control regulating the pressure across the valve and maintain a substantially constant pressure across the valve. The fuel control system includes a backup system controllable by a pullback signal to operate the pressure control, thus increasing the pullback signal reducing the fuel flow between the supply and delivery line. The fuel control system detects a start of an engine overthrust event, and when the upward runaway is caused by the arrested overthrust event. The fuel control system's controller which (i) determines the overthrust detection, the pullback signal increase rate and the pullback signal offset, (ii) sends the pullback signal to the backup system at the rate of increase, and (iii), reduces the pullback signal to the backup system when the upward runaway is arrested by the offset.

Подробнее
Номер записи: 81
19-05-2016 дата публикации

APPLICATION OF PROBABILISTIC CONTROL IN LIQUID-FUELED GAS TURBINE TUNING, RELATED CONTROL SYSTEMS, COMPUTER PROGRAM PRODUCTS AND METHODS

Номер: US20160138470A1
Автор: Davis, Jordan, JR. Harold Lamar, JR. Lewis Berkley, Morgan Rex Allen, Smith Raub Warfield
Принадлежит:

Various embodiments include a system having: at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT; commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value and an actual emissions value for each GT; adjusting at least one of a fuel flow or a water flow for each GT to an adjusted water/fuel ratio in response to the actual emissions value deviating from an emissions level associated with the base load level, while maintaining the respective adjusted output; and adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition, while maintaining the adjusted water/fuel ratio. 1. A system comprising: commanding each GT in the set of GTs to a base load level, based upon a measured ambient condition for each GT;', 'commanding each GT in the set of GTs to adjust a respective output to match a nominal mega-watt power output value, and subsequently measuring an actual fuel flow value and an actual emissions value for each GT;', 'adjusting at least one of a fuel flow or a water flow for each GT to an adjusted water/fuel ratio in response to the actual emissions value deviating from an emissions level associated with the base load level, while maintaining the respective adjusted output; and', 'adjusting an operating condition of each GT in the set of GTs based upon a difference between the respective measured actual fuel flow value and a nominal fuel flow value at the ambient condition, while maintaining the adjusted water/fuel ratio., 'at least one computing device configured to tune a set of gas turbines (GTs) by performing actions including2. The system of claim 1 , ...

Подробнее
Номер записи: 82
03-06-2021 дата публикации

FUEL NOZZLE WITH REDUCED FLOW TOLERANCE

Номер: US20210164577A1
Автор: McCormack Jimroy A.
Принадлежит: Woodward, Inc

A fuel nozzle metering valve that includes a spool having an inlet port and an outlet flow port, and a retainer assembled to one end of the spool. A valve liner houses a portion of the spool. The spool is configured to move back and forth within the valve liner. The metering valve is biased in a closed position in which the outlet flow port is disposed entirely within the valve liner. The valve is opened when the spool slides within the valve liner such that some portion of the outlet flow port extends beyond an end of the valve liner. The retainer has a stepped portion configured to abut an end of the retainer at a fuel flow pressure below the expected maximum fuel flow pressure to be used in the fuel nozzle metering valve. 1. A fuel nozzle metering valve comprising:a spool having an inlet port and a flow control port;a retainer assembled to one end of the spool;a valve liner which houses a portion of the spool, the spool configured to move back and forth within the valve liner;wherein the metering valve is biased in a closed position in which the flow control port is disposed entirely within the valve liner, wherein the valve is opened when the spool slides out of the valve liner such that some portion of the flow control port extends beyond an end of the valve liner, the retainer having a stepped portion configured to abut an end of the valve liner at a fuel flow pressure below the expected maximum fuel flow pressure to be used in the fuel nozzle metering valve.2. The fuel nozzle metering valve of claim 1 , wherein the spool is configured to slide out of the valve liner when a fuel flow pressure from fuel flowing into the inlet port overcomes the closing bias on the metering valve.3. The fuel nozzle metering valve of claim 1 , wherein the retainer is disc-shaped and the stepped portion extends from a central region of the disc-shaped retainer.4. The fuel nozzle metering valve of claim 1 , wherein the stepped portion is cylindrical or partially cylindrical.5. The ...

Подробнее
Номер записи: 83
17-05-2018 дата публикации

COMBINED OVERSPEED AND FUEL STREAM SELECTOR SYSTEMS

Номер: US20180135529A1
Автор: Arnett Eric, Futa Paul W., Portolese Larry, Tuttle David, Zielinski Edward
Принадлежит: HONEYWELL INTERNATIONAL INC.

Embodiments of a combined overspeed and fuel stream selector system are provided. In an embodiment, the assembly includes a conduit network, a Discharge Select Valve (DSV), and a shutoff valve. The DSV is fluidly coupled to a primary fuel inlet, a secondary fuel inlet, and a primary fuel outlet included in the conduit network. The shutoff valve is fluidly coupled between the primary fuel inlet and the primary fuel outlet. In a standard operation mode, the shutoff valve is maintained in an open position, while fuel received at the primary fuel inlet is directed through the shutoff valve, through the DSV, and to the primary fuel inlet. Conversely, in a backup operation mode, the shutoff valve is closed to block fuel flow from the primary fuel inlet to the primary fuel outlet, while the DSV directs fuel flow received at the secondary fuel inlet to the primary fuel outlet. 1. A combined overspeed and fuel stream selector system , comprising:a conduit network having a primary fuel inlet, a secondary fuel inlet, a primary fuel outlet, and a secondary fuel outlet;a shutoff valve fluidly coupled between the primary fuel inlet and the primary fuel outlet;a Discharge Select Valve (DSV) fluidly coupled to the shutoff valve; a standard operation mode in which the shutoff valve is maintained in an open position, while fuel received at the primary fuel inlet is directed through the shutoff valve, through the DSV, and to the primary fuel inlet; and', 'a backup operation mode in which the shutoff valve is maintained in a closed position to block fuel flow from the primary fuel inlet to the primary fuel outlet, while the DSV reroutes fuel flow received at the secondary fuel inlet to the primary fuel outlet., 'wherein the combined overspeed and fuel stream selector system is operable in2. The combined overspeed and fuel stream selector system of wherein the DSV directs fuel received at the secondary fuel inlet to the secondary fuel outlet in the standard operation mode.3. The ...

Подробнее
Номер записи: 84
17-05-2018 дата публикации

SYSTEMS AND METHODS FOR ADAPTIVELY PURGING FUEL CIRCUITS

Номер: US20180135530A1
Автор: Ewens David Spencer
Принадлежит:

A method includes instructing a purge valve of a gas turbine system to open, thereby purging a fuel circuit by filling the fuel circuit with purge gas, wherein the fuel circuit initially contains fuel. The method also includes generating a model of the gas turbine system that simulates a modeled output based on a model input corresponding to a measured input. The method further includes receiving a measured output of the gas turbine system. The method also includes adjusting the model input such that the modeled output more closely matches the measured output when the measured output is not approximately equal to the modeled output. The method further includes instructing the purge valve to open during a subsequent purge operation and a gas control valve to open more fully or at least partially close during the subsequent purge operation based at least in part on adjusting the model input 1. A gas turbine system comprising: a plurality of purge valves, each purge valve of the plurality of purge valves coupled to a purge gas supply;', 'a plurality of fuel circuits, wherein each fuel circuit of the plurality of fuel circuits is coupled to a respective purge valve of the plurality of purge valves;', 'a gas turbine configured to operate based on fuel received via the plurality of fuel circuits; and', transmit a first set of instructions to a set of purge valves of the plurality of purge valves to open, thereby purging one or more fuel circuits of the plurality of fuel circuits by filling the one or more fuel circuits with purge gas, wherein the one or more fuel circuits initially contain fuel;', 'generate a model of the gas turbine system that simulates one or more modeled outputs of the gas turbine system based on one or more model inputs corresponding to one or more measured inputs to the gas turbine system;', 'receive one or more measured outputs of the gas turbine system after the set of purge valves open;', 'adjust the one or more model inputs to match the one or ...

Подробнее
Номер записи: 85
18-05-2017 дата публикации

Method and system for improving parameter measurement

Номер: US20170138781A1
Автор: Sridhar Adibhatla
Принадлежит: General Electric Co

Parameter measurement systems including improved sensor calibration are provided herein. The measurement system includes a first sensor with a first output signal including a plurality of output characteristics, at least one output characteristic being deficient for measuring a desired parameter and at least one output characteristic being suitable for measuring the desired parameter. The measurement system also includes a second sensor with a second output signal comprising at least some of the plurality of output characteristics, the at least one deficient characteristic of the first output signal being suitable in the second output signal for measuring the desired parameter. The measurement system further includes a processor programmed to calibrate the first output signal using the second output signal to generate a third output signal including the at least one suitable characteristic of the first output signal and the at least one suitable characteristic of the second output signal.

Подробнее
Номер записи: 86
24-05-2018 дата публикации

PURGING LIQUID FUEL NOZZLES AND SUPPLY TUBING WITH THE ASSISTANCE OF A FLOW DIVIDER

Номер: US20180142570A1
Автор: HEALEY James R., MESMER Jason A.
Принадлежит:

A fuel delivery system for a gas turbine engine that employs a technique for purging fuel delivery tubes in an effective manner. The fuel delivery system includes at least one multifunction valve that has a flow through position and a bi-directional purge position. The fuel delivery system also includes at least one flow divider that is positioned downstream from the multifunction valve and divides the flow of fuel from the valve into a number of the fuel delivery tubes, where a separate fuel delivery tube is provided for each combustor in the engine. The flow divider includes a pump element for all of the fuel delivery tubes that can operate in a forward and a reverse direction. Purge water provided downstream from the flow divider for each of the fuel delivery tubes can be pumped by the flow divider when the multifunction valve is in the purge position. 1. A fuel delivery system for providing fuel to a plurality of combustors in a gas turbine engine , said fuel delivery system comprising:a fuel line receiving a liquid fuel;at least one control valve provided along the fuel line and controlling the flow of the fuel therethrough;at least one multifunction valve provided along the fuel line downstream from the control valve and including a flow-through position, a drain position and a purge position;at least one flow divider provided along the fuel line downstream from the multifunction valve, said flow divider directing the fuel in the flow line into a plurality of flow delivery tubes where a separate one of the flow tubes is coupled to a separate one of the combustors, said at least one flow divider including a separate pump element for each flow tube that is controlled to allow flow in both a forward direction and a reverse direction;a separate water injection line coupled to each of the flow tubes downstream from the at least one flow divider; anda drain coupled to the at least one multifunction valve, wherein water injected at a certain pressure into the flow ...

Подробнее
Номер записи: 87
04-06-2015 дата публикации

METHOD AND DEVICE FOR ADJUSTING A THRESHOLD VALUE OF A FUEL FLOW RATE

Номер: US20150152790A1
Автор: DJELASSI Cedrik, GAULLY Bruno Robert, JAVELOT Christophe, Sylla Ismail
Принадлежит: SNECMA

A method of adjusting a fuel flow rate in a turbine engine propelling an aircraft, including: obtaining a first estimate of a flow rate of fuel injected into a combustion chamber of the turbine engine propelling an aircraft and as delivered by a fuel metering device of the turbine engine; obtaining a second estimate of the fuel flow rate, which second estimate is more accurate than the first estimate for at least one range of fuel flow rate values and being delivered by an estimator device having a flow meter; and adjusting the fuel flow rate threshold value with help of a difference evaluated between the first estimate and the second estimate, the threshold value being for use in an open loop for regulating the turbine engine. 112-. (canceled)13: A method of adjusting a fuel flow rate threshold value for use in an open loop for regulating a turbine engine propelling an aircraft , the method comprising:obtaining a first estimate of a flow rate of fuel injected into a combustion chamber of the turbine engine and as delivered by a fuel metering device of the turbine engine;obtaining a second estimate of flow rate of fuel injected into the combustion chamber, the second estimate being more accurate than the first estimate for at least one range of fuel flow rate values and being delivered by an estimator device having a flow meter; andadjusting the fuel flow rate threshold value with help of a difference evaluated between the first estimate and the second estimate.14: An adjustment method according to claim 13 , wherein the adjusting comprises adding to the fuel flow rate threshold value the difference evaluated between the first estimate and the second estimate claim 13 , as weighted by a predetermined weighting factor.15: An adjustment method according to claim 14 , further comprising comparing the difference evaluated between the first estimate and the second estimate as weighted by the predetermined weighting factor with an expected accuracy difference between the ...

Подробнее
Номер записи: 88
04-06-2015 дата публикации

GAS TURBINE COMBUSTOR DIAGNOSTIC SYSTEM AND METHOD

Номер: US20150152791A1
Автор: White Eugene Delano
Принадлежит:

In an embodiment, a method includes performing a turbine combustor diagnostic routine including operating a first turbine combustor of a plurality of turbine combustors at a substantially steady state of combustion; adjusting an operational parameter of the first turbine combustor to cause a change in combustion products produced by the first turbine combustor; identifying a first sensor response of a first subset of a plurality of sensors disposed within or downstream from a turbine fluidly coupled to the turbine combustor, the first sensor response being indicative of the change in the combustion products, and wherein the first subset comprises one or more first sensors; correlating the first subset of sensors with the first turbine combustor; and diagnosing a condition of the first subset of the plurality of sensors, the first turbine combustor, or a combination thereof, based on the first sensor response. 1. A system , comprising: a turbine combustion system comprising a plurality of turbine combustors each configured to combust a fuel/oxidant mixture to produce combustion products;', 'a turbine driven by the combustion products produced by the turbine combustion system;', 'a plurality of sensors positioned downstream of the turbine combustion system and configured to monitor one or more parameters of the combustion products; and', adjusting an operational parameter of a first turbine combustor of the plurality of turbine combustors to cause a change in the combustion products produced by the first turbine combustor;', 'identifying respective sensor responses of one or more first sensors of the plurality of sensors that detects the change in the combustion products;', 'correlating the respective sensor responses with the first turbine combustor; and', 'diagnosing a condition of the one or more first sensors, the first turbine combustor, or a combination thereof, based on the respective sensor responses., 'a control system comprising one or more non-transitory ...

Подробнее
Номер записи: 89
21-08-2014 дата публикации

Valve control device, gas turbine, and valve control method

Номер: US20140230449A1
Автор: Akihiko Saito, Fuminori Fujii, Takafumi Uda, Takashi Sonoda
Принадлежит: Mitsubishi Hitachi Power Systems Ltd

A valve control device is provided in a gas turbine having a combustor for generating combustion gas, a turbine driven by the combustion gas generated by the combustor, a flow rate regulating valve for regulating the flow rate of the fuel to be supplied to the combustor, and a pressure regulating valve disposed upstream of the flow rate regulating valve, for regulating the fuel pressure. The valve control device controls the opening degree of the valve. The valve control device includes a load decrease detection part which detects a load decrease of the gas turbine, and a pressure control part which controls the opening degree of the valve in accordance with the output of the gas turbine. The valve control device suppresses instability of the gas turbine output even when the load rapidly decreases.

Подробнее
Номер записи: 90
15-09-2022 дата публикации

FUEL SUPPLY SYSTEM

Номер: US20220290619A1
Автор: OTA Akira
Принадлежит:

A fuel supply system includes an ecology device that includes a first passage and a second passage , a cylinder and a piston provided between the first passage and the second passage , an urging portion that urges the piston , and a third passage that branches off from the first passage . A volume A of the first space of the cylinder at the time of the engine operation of the gas turbine engine is defined as a first volume when operating B. A total volume of fuel remaining in a fuel manifold and a fuel nozzle at the time of the engine stop of the gas turbine engine is defined as a required recovery volume D. The first volume when operating B is greater than the required recovery volume D. 1. A fuel supply system of a gas turbine engine , the fuel supply system comprising:a fuel tank;a fuel manifold which supplies a fuel from the fuel tank to a fuel nozzle; andan ecology device provided between the fuel tank and the fuel manifold to recover the fuel from the fuel manifold,wherein the ecology device includesa first passage connected to the fuel tank,a second passage connected to the fuel manifold,a cylinder which is provided between the first passage and the second passage and has a first port communicating with the first passage and a second port communicating with the second passage,a piston which partitions an internal space of the cylinder into a first space communicating with the first passage and a second space communicating with the second passage, and slides inside the cylinder,an urging portion which urges the piston from the second port side toward the first port side,a third passage which branches off from the first passage and communicates with the second passage, anda check valve which is provided in the third passage to block circulation from the second passage to the first passage,a volume of the cylinder is equivalent to a total of a volume of the first space and a volume of the second space,the volume of the first space of the cylinder at the time of ...

Подробнее
Номер записи: 91
07-05-2020 дата публикации

METHOD AND SYSTEM FOR SAFE GAS TURBINE STARTUP

Номер: US20200141321A1
Автор: Botarelli Claudio, BRUNI Daniele, CARNIERI Andrea, GIUNTA Bruno, QUARTIERI Eugenio, VANNI Nicola
Принадлежит:

A method for safe gas turbine startup is disclosed. The method comprises a first step wherein a fuel metering valve () arranged along a fuel delivery line is tested for possible leakages. If the leakage test is successfully passed, a subsequent turbine startup step can be performed. Further disclosed is a gas turbine engine () comprising a fuel supply system () comprised of a fuel delivery line () and a valve arrangement () positioned along said fuel delivery line (). The valve arrangement () further comprises sequentially arranged shut off valves () and a fuel metering valve (), positioned downstream of the shut off valves (). A pressure measuring arrangement () is further provided, adapted to measure fuel pressure in at least one portion of the fuel delivery line () upstream of the fuel metering valve (). 1. A method for safe gas turbine startup , comprising the following steps:{'b': 33', '21', '7', '3, 'performing a leakage test of a fuel metering valve () positioned along a fuel delivery line () and fluidly coupled with a combustor section () of the gas turbine engine (),'}when the leakage test is successfully passed, initiating a gas turbine engine startup procedure.233. The method of claim 1 , wherein the step of performing the leakage test of the fuel metering valve () further comprises the following steps:{'b': 33', '33, 'establishing a first test pressure in a closed volume upstream of the fuel metering valve (), while the fuel metering valve () is closed; wherein said first test pressure is preferably lower than a full fuel supply pressure;'}{'b': '33', 'detecting a pressure drop upstream of the fuel metering valve ();'}if the pressure drop is above a threshold value, generating a leakage alert signal;if the pressure drop is below the threshold value, executing a further step of the startup procedure.3. The method of claim 2 , wherein the step of establishing the first test pressure comprises the steps of:{'b': '33', 'establishing a full fuel supply ...

Подробнее
Номер записи: 92
31-05-2018 дата публикации

MODEL-LESS COMBUSTION DYNAMICS AUTOTUNE

Номер: US20180149363A1
Автор: ARTHANARI Akilezkrishnamurthy, Dean Douglas Edward, Harper James, Kulkarni Abhijit Prabhakar, Lal Mihir
Принадлежит:

This disclosure relates to systems and methods for tuning combustion dynamics in a combustor. In one embodiment of the disclosure, a method includes providing, via at least one sensor, combustion dynamics amplitude data associated with a combustor. Method may allow monitoring, by an equipment controller communicatively coupled to the at least one sensor, the combustion dynamics amplitude data. The method may allow detecting at least one change in acoustic pressure amplitude associated with combustion in the combustor. In response to detecting the change in the acoustic pressure amplitude, the method proceeds with determining a fuel split change to at least two fuel circuits configured to supply fuel to the combustor, and applying the fuel split change to the combustor. 1. A system for tuning of combustion dynamics , the system comprising:a combustor;at least two fuel circuits configured to supply fuel to the combustor;at least one sensor to detect and provide combustion dynamics amplitude data associated with the combustor; and analyze the combustion dynamics amplitude data to detect at least one change in acoustic pressure amplitude associated with combustion in the combustor; and', 'in response to the at least one change in acoustic pressure amplitude:', 'determine a fuel split change, the fuel split change being a change of the ratio of flow to the at least two fuel circuits; and', 'apply the fuel split change to the combustor., 'an equipment controller communicatively coupled to the at least one sensor, the equipment controller configured to2. The system of claim 1 , wherein detection of the at least one change in the acoustic pressure amplitude includes determining that the acoustic pressure amplitude exceeds a predefined dynamics amplitude threshold level for at least one vibrational frequency band of a set of ranges of frequencies.3. The system of claim 2 , wherein the fuel split change is determined based on a predefined split change direction and an ...

Подробнее
Номер записи: 93
17-06-2021 дата публикации

Combustion Engine

Номер: US20210180519A1
Автор: Williams Clive
Принадлежит:

A combustion engine () comprises a radial compressor () in flow communication via a flow passage () with a compressor-combustor array () radially outward of the radial compressor (), both rotatable around a central axis (). The compressor-combustor () comprises an array of rotor blades (). The walls of the blades () define a plurality of chambers (). Each chamber () has a flow inlet () to receive fluid from the radial compressor (), and a flow outlet to exhaust fluid radially outwards from the compressor-combustor (). The plurality of chambers () comprises a first pilot combustion chamber () and a second pilot combustion chamber (). The first pilot combustion chamber () is provided with a first fuel injector (), and the second pilot combustion chamber () is provided with a second fuel injector (). The first fuel injector () is in flow communication with a first fuel reservoir (), and the second fuel injector () is in flow communication with a second fuel reservoir (). The first fuel reservoir () and the second fuel reservoir () are each in fluid communication with a flow regulator (), the flow regulator () operable to vary fuel flow delivery rate to the first reservoir () and vary fuel flow delivery rate to the second reservoir (). The differential regulation of fuel flow between pilot combustion chambers results in different levels of thrust being generated downstream of the combustion chambers. In this way the engine is operable to produce vectored thrust. 115-. (canceled)16. A combustion engine comprising:a first fuel reservoir;a second fuel reservoir;a flow regulator;a compressor-combustor array and a radial compressor, the compressor-combustor array is provided radially outward of the radial compressor;both the radial compressor and compressor-combustor array being co-axial with, and rotatable around, a central axis;wherein the compressor-combustor array comprises an array of rotor blades comprising walls; a first pilot combustion chamber; and', 'a second pilot ...

Подробнее
Номер записи: 94
11-06-2015 дата публикации

Method and Apparatus for Controlling Gas Turbine Combustor

Номер: US20150159562A1
Автор: HAYASHI Akinori, HIRATA Yoshitaka, SAITOU Nozomi, SAITOU Takeo, Sekiguchi Tatsuya, TAKAHASHI Kazuo, YOSHIDA Shouhei
Принадлежит:

An apparatus for controlling a gas turbine combustor having a diffusion combustion burner and a premix combustion burner comprising: a rotating speed detector for detecting a rotating speed of gas turbine, a recorder for recording the detected value of the rotating speed of gas turbine detected by the rotating speed detector, an arithmetic unit for calculating a change with time of the rotating speed of gas turbine in accordance with details of the detected value of the rotating speed of gas turbine recorded in the recorder, and a fuel control unit for judging a starting situation of reduction in the rotating speed of gas turbine on the basis of the change with time of the rotating speed of gas turbine calculated by the arithmetic unit and controlling respectively a fuel flow rate for the diffusion combustion burner to be fed to the diffusion combustion burner installed in the gas turbine combustor and a fuel flow rate for the premix combustion to be fed to the premix combustion burner. 1. An apparatus for controlling a gas turbine combustor having a diffusion combustion burner and a premix combustion burner comprising:a detector for detecting a rotating speed of gas turbine, a recorder for recording the detected value of the rotating speed of gas turbine detected by the rotating speed detector, an arithmetic unit for calculating a change with time of the rotating speed of gas turbine in accordance with details of the detected value of the rotating speed of gas turbine recorded in the recorder, a bleed valve opening angle detector for detecting an opening angle of a compressor bleed valve installed in a compressor, a logic circuit for checking a value of the change with time of the rotating speed of gas turbine calculated by the arithmetic unit and an opening angle signal of the bleed valve detected by the bleed valve opening angle detector, and a fuel control unit for respectively controlling a fuel flow rate for the diffusion combustion burner to be fed to the ...

Подробнее
Номер записи: 95
23-05-2019 дата публикации

SYSTEM AND METHOD FOR AN ENGINE CONTROLLER BASED ON INVERSE DYNAMICS OF THE ENGINE

Номер: US20190153962A1
Автор: MEUNIER Gabriel, PEDRAMI Reza
Принадлежит:

Systems and methods for controlling a gas turbine engine are provided. The system comprises an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command and a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow. The controller comprises a feedforward controller configured for receiving a requested engine speed and acceleration, obtaining a steady-state fuel flow for the requested engine speed and a relationship between fuel flow and gas generator speed, and determining the required fuel flow to obtain the requested engine acceleration as a function of the requested engine speed, the steady-state fuel flow, and the relationship between fuel flow and gas generator speed. 1. A system for controlling a gas turbine engine of an aircraft , the system comprising:an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command; and receiving a requested engine speed and a requested engine acceleration;', 'obtaining a steady-state fuel flow for the requested engine speed and a relationship between fuel flow and gas generator speed; and', 'determining the required fuel flow to obtain the requested engine acceleration as a function of the requested engine speed, the steady-state fuel flow, and the relationship between fuel flow and gas generator speed., 'a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow, the controller comprising a feedforward controller configured for2. The system of claim 1 , wherein the controller is further configured to limit acceleration of the gas turbine engine by applying a rate limit to the requested engine speed.3. The system of claim 1 , wherein the controller comprises a feedback controller configured to adjust the ...

Подробнее
Номер записи: 96
08-06-2017 дата публикации

PRESSURE REGULATING DEVICE FOR A GAS SUPPLY SYSTEM OF A GAS TURBINE PLANT

Номер: US20170159570A1
Автор: Bickert Rainer
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A pressure regulating device for a gas supply system of a gas turbine plant, having a pressure reduction unit for reducing the pressure of an inflowing gas, in particular a combustion gas, a compressor system for compressing the in-flowing gas and connected in parallel to the pressure reduction unit, and a regulating valve arranged on the output side of the pressure reduction unit, via which valve the pressure reduction unit can be fluidically separated on the output side from the compressor system. A gas supply system for a gas turbine plant has a corresponding pressure regulating device and a method for pressure regulation of a gas, uses a gas supply system with a corresponding pressure regulating device. 1. A pressure-regulating device for a gas supply system of a gas turbine plant , comprisinga pressure-reduction unit for reducing the pressure of an inflowing gas,a compressor unit, connected in parallel to the pressure-reduction unit, for compressing an inflowing gas, anda control armature arranged on the outlet side of the pressure-reduction unit, via which the pressure-reduction unit is separable fluidically from the compressor unit on the outlet side.2. The pressure-regulating device as claimed in claim 1 ,wherein the pressure-reduction unit and the compressor unit lead on the outlet side into a common collection line via a T-junction branching piece, and wherein the control armature is arranged between the pressure-reduction unit and the T-junction branching piece.3. The pressure-regulating device as claimed in claim 1 ,wherein the pressure setting in the compressor unit corresponds essentially to the pressure setting in the pressure-reduction unit.4. The pressure-regulating device as claimed in claim 1 ,wherein the pressure-reduction unit comprises two pressure control loops connected in parallel.5. The pressure-regulating device as claimed in claim 3 ,wherein the pressure control loops of the pressure-reduction unit are each set to different pressure ...

Подробнее
Номер записи: 97
14-05-2020 дата публикации

FUEL FLOW CONTROL SYSTEM AND METHOD FOR ENGINE START

Номер: US20200149479A1
Автор: DES ROCHES-DIONNE Nicolas, LAMARRE Sylvain, LOPEZ Simon
Принадлежит:

Systems and methods for controlling fuel flow to an engine during start are provided. Fuel is caused to be injected into a combustor of the engine according to a first fuel schedule defining a minimum fuel flow limit required to achieve light-off of the engine, the minimum fuel flow limit set at an initial value. Following light-off of the engine, at least one operating parameter of the engine is monitored. Based on the at least one operating parameter, occurrence of flameout in the engine is detected. In response to detecting occurrence of flameout in the engine, the minimum fuel flow limit is increased from the initial value to a first value to obtain an adjusted fuel schedule, and fuel is caused to be injected into the combustor according to the adjusted fuel schedule. 1. A method for controlling fuel flow to an engine during start , the method comprising:causing fuel to be injected into a combustor of the engine according to a first fuel schedule defining a minimum fuel flow limit required to achieve light-off of the engine, the minimum fuel flow limit set at an initial value;monitoring, following light-off of the engine, at least one operating parameter of the engine;detecting, based on the at least one operating parameter, occurrence of flameout in the engine; andin response to detecting occurrence of flameout in the engine, increasing the minimum fuel flow limit from the initial value to a first value to obtain an adjusted fuel schedule, and causing fuel to be injected into the combustor according to the adjusted fuel schedule.2. The method of claim 1 , wherein the first fuel schedule follows an open loop profile.3. The method of claim 1 , wherein monitoring the at least one operating parameter of the engine comprises monitoring an acceleration of the engine claim 1 , and wherein detecting the presence of the flameout condition comprises comparing the acceleration to a predetermined threshold and detecting partial flameout responsive to determining that the ...

Подробнее
Номер записи: 98
14-06-2018 дата публикации

FLUID VALVES

Номер: US20180163635A1
Автор: Bleeker Daniel Edward, Marocchini Francis P.
Принадлежит:

A fluid valve for a gas turbine engine includes a valve body with a fluid inlet and a fluid outlet, a fluid circuit extending between the fluid inlet and the fluid outlet, and a linkage. The linkage is arranged within the fluid circuit between the fluid inlet and the fluid outlet to apply effort from a solenoid actuator to a valve member movable between first and second positions within the fluid circuit to meter fluid flow between the fluid inlet and the fluid outlet to issue fuel into a combustor of the gas turbine engine. 1. A fluid valve for a gas turbine engine , comprising:a valve body having a fluid inlet and a fluid outlet;a fluid circuit defined between the fluid inlet and the fluid outlet; anda linkage disposed between the fluid inlet and the fluid outlet,wherein the linkage includes a rocker arm pivotally fixed to the valve body and within the fluid circuit and is configured to apply effort from an electronic actuator to a valve member movable between a first position and a second position for metering a flow of fluid between the fluid inlet and the fluid outlet of the valve body for issuing fluid into a gas turbine engine.2. The fluid valve as recited in claim 1 , wherein the rocker arm includes a first segment and an second segment claim 1 , the second segment being longer than the first segment.3. The fluid valve as recited in claim 2 , wherein the second segment is about three times as long as the first segment.4. The fluid valve as recited in claim 2 , wherein first segment is angled relative to the second segment.5. The fluid valve as recited in claim 2 , wherein the second segment has a slotted joint to receive effort along an actuator drive axis claim 2 , wherein the first segment has a slotted joint to apply the effort along a load axis.6. The fluid valve as recited in claim 2 , wherein the first segment is angled relative to the second segment within an angular range of between about 85 degrees and 130 degrees.7. The fluid valve as recited in ...

Подробнее
Номер записи: 99
14-06-2018 дата публикации

FUEL SUPPLY SYSTEM

Номер: US20180163636A1
Автор: Griffiths Michael
Принадлежит: ROLLS-ROYCE PLC

The fuel supply system includes mains pressurising and metering arrangement including a positive displacement ecology pump and an ecology valve piston chamber and a piston slidably movable in the chamber between de-prime and re-prime positions, the chamber forming a fuel sink to one side of the piston which increases in volume when the piston moves to de-prime position and reduces in volume when the piston moves to re-prime position. The ecology valve is fluidly connected to the ecology pump for pilot-only operation reverse direction operation of the ecology pump causes the piston to move to de-prime position removing mains fuel from injectors through a mains fuel distribution pipework and into the fuel sink, and for pilot and mains operation the forward direction operation of the ecology pump causes the piston to move to re-prime position refilling injectors with mains fuel from the fuel sink. 1. A fuel supply system for fuel injectors of a multi-stage combustor of a gas turbine engine , the fuel supply system including:a pilot pressurising and metering arrangement which receives a first portion of a low pressure fuel flow, and pressurises and controllably meters the first portion of the low pressure fuel flow into a high pressure metered pilot flow for injecting at pilot discharge orifices of the injectors;a mains pressurising and metering arrangement including a positive displacement ecology pump, the mains pressurising and metering arrangement being configured to pressurise and controllably meter a second portion of the low pressure fuel flow into a high pressure metered mains flow for injecting at mains discharge orifices of the injectors, wherein the ecology pump is operable in a forward direction for pilot and mains operation in which there are pilot and mains supplies to the combustor from the injectors, the ratio of the metered pilot flow to the metered mains flow determining a staging control split of the pilot and mains flows, and wherein the ecology pump ...

Подробнее
Номер записи: 100