WO2012093235A1 - Circuit de carburant de turbomachine aéronautique a vanne de régulation de pression de carburant. - Google Patents
Circuit de carburant de turbomachine aéronautique a vanne de régulation de pression de carburant. Download PDFInfo
- Publication number
- WO2012093235A1 WO2012093235A1 PCT/FR2012/050019 FR2012050019W WO2012093235A1 WO 2012093235 A1 WO2012093235 A1 WO 2012093235A1 FR 2012050019 W FR2012050019 W FR 2012050019W WO 2012093235 A1 WO2012093235 A1 WO 2012093235A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- fuel
- valve
- pump
- line
- circuit
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/224—Heating fuel before feeding to the burner
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/236—Fuel delivery systems comprising two or more pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/263—Control of fuel supply by means of fuel metering valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/40—Transmission of power
- F05D2260/406—Transmission of power through hydraulic systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/303—Temperature
Definitions
- the present invention relates to the general field of fuel circulation in a turbomachine.
- the invention applies to any type of aircraft turbine engine and more particularly to aircraft turbojets.
- the fuel In an aviation turbine engine, it is common for the fuel to be used not only as a fuel (in the combustion chamber of the turbomachine), but also as a hydraulic fluid in hydraulic actuators for the control of equipment with variable geometry of the turbomachine (such as air discharge valves and valves to adapt the geometry of the compressor of the turbomachine).
- the fuel system of a turbomachine typically comprises a main fuel line for supplying fuel to a combustion chamber of the turbomachine, and an auxiliary fuel line connected to the main fuel line and intended to supply fuel.
- fuel hydraulic actuators for the control of variable geometry equipment of the turbomachine.
- the auxiliary fuel line for supplying the hydraulic actuators comprises electrohydraulic servovalves, ie hydraulic valves controlled by servomotors. These servo valves are used to deliver a calibrated flow of fuel to one or the other of the chambers of a hydraulic actuator and are controlled by the electronic computer of the turbomachine (also called ECU for "Electronic Control Unit").
- an oil or air heat exchanger upstream of the servovalves in the auxiliary line of the fuel circuit in order to heat the fuel at the input of the servovalves and thus avoid any risk of clogging of the fuel. their ducts by ice formed by the water contained in the icing fuel.
- the calories from the engine oil circuit are: used to heat transfer the input fuel of the servovalves.
- an air exchanger it is placed downstream of the low-pressure pump and it is air from a sample on the compressor or the engine blower that is used to heat the air. whole fuel.
- an oil or air heat exchanger for heating the fuel at the inlet of the servovalves has many disadvantages.
- an oil exchanger has a high mass, a risk of fuel leakage in the oil and hydraulic stresses in the oil circuit.
- the air exchanger it also has the disadvantages of a high mass, a large footprint and a complex installation and control.
- the main object of the present invention is thus to overcome such disadvantages by proposing a fuel circuit which makes it possible in a simplified and efficient way to increase the temperature of the fuel entering the servovalves under extreme cold conditions.
- an aviation turbomachine fuel circuit comprising a main fuel line for supplying fuel to a combustion chamber of the turbomachine and comprising a positive displacement pump, and an auxiliary fuel line connected to the main line of fuel.
- fuel at a junction located downstream of the pump and for supplying fuel to hydraulic actuators for the control of equipment with variable geometry of the turbomachine the auxiliary fuel line comprising electrohydraulic servo valves upstream of each cylinder, the circuit further comprising, in accordance with the invention, a fuel pressure regulating valve disposed on the main fuel line downstream of the pump.
- the fuel pressure regulating valve is controlled to be partially closed, which has the effect of increasing the temperature of the fuel downstream thereof, and more particularly at the inlet of the servo valves.
- the auxiliary fuel line for supplying the hydraulic actuators for the control of variable geometry equipment.
- This hydraulic power supplied to the fuel will then dissipate thermally by rolling in the fuel circuit because of the pressure drops experienced by the fuel as it passes through the valve. This results in an increase in the temperature of the fuel at the outlet of the valve. For example, a rise in the pressure of 40 bars at the outlet of the pump makes it possible to increase the fuel temperature by 8 ° C at the start in extreme cold conditions compared to a circuit architecture devoid of a device dedicated to the protection against the icing of the fuel.
- valve in the fuel system makes it possible to increase the temperature of the fuel at the input of the servovalves of the circuit, if necessary, thus avoiding frost formation.
- the use of such a valve has a low mass addition and a reduced space requirement (the valve can be integrated directly into the pump). Such a valve also has a simplified operation.
- the valve can be connected to an electronic computer of the turbomachine which controls its opening and closing.
- the electronic computer of the turbomachine can be connected to a fuel temperature sensor disposed downstream of the pump.
- valve can be connected to a thermostatic valve which controls its opening and closing, said valve being disposed in a fuel sampling line connecting the valve to the auxiliary fuel line upstream of the servovalves.
- the main fuel line may be devoid of loss of pressure equipment between the pump and the valve.
- loss of pressure equipment for example means a filter, a heat exchanger or other equipment disposed on the fuel line and subject to pressure losses fuel passing therethrough.
- the invention also relates to an aviation turbine engine comprising a fuel circuit as defined above.
- the invention also relates to a method for controlling a fuel pressure regulating valve of a fuel system as defined above, the method of partially closing the valve when the fuel temperature in the auxiliary line of fuel upstream of the servovalves is below a predetermined threshold temperature and to open the valve when the fuel temperature in the auxiliary fuel line upstream of the servovalves is higher than the predetermined threshold temperature.
- FIG. 1 very schematically represents an aeronautical turbomachine fuel circuit according to the invention.
- FIG. 2 very schematically shows a fuel circuit portion according to an alternative embodiment of the invention. Detailed description of embodiments
- the fuel system 10 for an aviation turbomachine comprises a main fuel line 12 equipped, in the direction of flow of the fuel, with a low-pressure pump 14, a fuel / oil heat exchanger 16, a fuel main filter 18 and a so-called high pressure volumetric pump 20.
- a low-pressure pump 14 a fuel / oil heat exchanger 16
- a fuel main filter 18 a fuel main filter 18
- a so-called high pressure volumetric pump 20 a different arrangement of this equipment could be considered.
- the low-pressure pump 14 is connected upstream to the fuel tanks of the aircraft (not shown in Figure 1).
- the fuel / oil heat exchanger 16 makes it possible to cool the lubricating oil of the turbomachine by heat exchange with fuel through an exchange surface separating these two fluids, which has the effect of heating the fuel.
- the main fuel line 12 Downstream of the high-pressure pump 20, the main fuel line 12 comprises a metering member 22 for controlling the flow of fuel injected into the combustion chamber 24 of the turbomachine via fuel injection systems (not shown). .
- the fuel metering member 22 is controlled by the hydromechanical unit 26 of the turbine engine (or HMU for "Hydro Mechanical Unit").
- the excess fuel in this main line is returned upstream of the fuel / oil heat exchanger 16 via a fuel recirculation loop 28.
- the fuel system further comprises an auxiliary fuel line 30 connected to the main fuel line 12 at a junction 32 located downstream of the high-pressure pump 20.
- This auxiliary line is intended to supply fuel to the actuators hydraulic actuators 34 (for example cylinders) for the control of equipment with variable geometry of the turbomachine (not shown).
- this auxiliary fuel line comprises electrohydraulic servovalves 36 which are well known per se, each servovalve being used to deliver a flow of fuel to one or the other of the chambers of a hydraulic jack 34.
- These servovalves 36 are electrically controlled by the electronic computer 38 of the turbomachine (or ECU for "Electronic Control Unit” designating an electronic control unit).
- the fuel leaving the servovalves joins the re-circulation loop 28 passing through the metering member 22.
- the fuel system further comprises a fuel pressure regulating valve 40 which is arranged on the main fuel line 12 downstream of the high-pressure pump 20.
- valve 40 could be placed anywhere on the main line of fuel downstream of the high-pressure pump 20 and upstream of the combustion chamber 24, for example upstream of the junction 32 between the main line of fuel and the auxiliary fuel line 30 as shown in Figures 1 and 2.
- This valve 40 has the function of regulating the pressure of the fuel passing through it by acting on the passage section of the fuel passing therethrough.
- This is for example a solenoid valve of the electro-valve type associated with a slide valve provided with a setting spring.
- valve 40 is connected to the electronic computer 38 of the turbomachine which electrically controls and controls the opening and closing of its fuel passage section.
- the opening and closing of the valve are more precisely controlled according to the temperature of the fuel in the fuel circuit downstream of the high-pressure pump 20.
- the electronic computer is connected to a temperature sensor 42 fuel placed in the main fuel line, for example downstream of the high-pressure pump 20, in particular at the outlet of the fuel metering device 22.
- the electronic computer of the turbomachine will command a partial closure or a full opening of the valve 40.
- a predetermined threshold temperature for example of 10 ° C
- the electronic computer controls a partial closure of the valve 40, this partial closure ultimately resulting in an increase in the temperature of the fuel downstream of the valve, and therefore at the input of the servovalves 36.
- the electronic computer controls a full opening of the valve, the presence of it then having no effect on the fuel pressure (and therefore its temperature) downstream of the valve.
- a temperature below the threshold temperature of 10 ° C can only be reached at the start or the takeoff of the aircraft (and in the presence of extreme cold conditions). Indeed, during the other phases of flight, the heating of the input fuel servovalves is no longer necessary, the presence of the fuel / oil heat exchanger 16 located further upstream in the fuel circuit being sufficient with the input of heat at the re-circulation loop 28 to bring the fuel to a temperature above this threshold.
- the rise in the temperature of the fuel at the outlet of the valve 40 is due to an increase in the pressure differential between the inlet and the outlet of the high-pressure pump 20, this increase being caused by the restriction of the passage section. of fuel from the valve following partial closure.
- a rise in the pressure of 40 bars at the outlet of the high-pressure pump makes it possible to increase the fuel temperature by 8 ° C when starting in extreme cold conditions compared to a circuit architecture devoid of a device dedicated to protection against icing of fuel.
- the fuel pressure regulating valve 40 of the fuel circuit 10 ' is connected to a thermostatic valve 44 which controls the opening and closing of its valve section. passage.
- this thermostatic valve is arranged in a sampling line of fuel 46 connecting the valve to the auxiliary fuel line 30 upstream of the servovalves 36.
- the thermostatic valve opens and causes a partial closure of the fuel passage section of the fuel. the valve 40. As previously indicated, this partial closure of the valve ultimately causing a rise in the temperature of the fuel downstream of the valve, and therefore at the input of the servovalves 36.
- a predetermined threshold temperature for example of 10 ° C.
- the thermostatic valve remains closed and the valve completely open, the presence of which then has no effect on the pressure. fuel (and therefore its temperature) downstream of the valve.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fuel-Injection Apparatus (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/978,470 US9702301B2 (en) | 2011-01-06 | 2012-01-04 | Fuel circuit for an aviation turbine engine, the circuit having a fuel pressure regulator valve |
GB1312087.8A GB2501198B (en) | 2011-01-06 | 2012-01-04 | A fuel circuit for an aviation turbine engine, the circuit having a fuel pressure regulator valve |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1150094A FR2970303B1 (fr) | 2011-01-06 | 2011-01-06 | Circuit de carburant de turbomachine aeronautique a vanne de regulation de pression de carburant |
FR1150094 | 2011-01-06 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012093235A1 true WO2012093235A1 (fr) | 2012-07-12 |
Family
ID=44509936
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/050019 WO2012093235A1 (fr) | 2011-01-06 | 2012-01-04 | Circuit de carburant de turbomachine aéronautique a vanne de régulation de pression de carburant. |
Country Status (4)
Country | Link |
---|---|
US (1) | US9702301B2 (fr) |
FR (1) | FR2970303B1 (fr) |
GB (1) | GB2501198B (fr) |
WO (1) | WO2012093235A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170198640A1 (en) * | 2014-05-26 | 2017-07-13 | Safran Power Units | Device and method for pre-heating fuel in a turbomachine |
FR3116858A1 (fr) * | 2020-12-01 | 2022-06-03 | Safran Aircraft Engines | Ensemble pour turbomachine d’aeronef comprenant une vanne passive de contournement d’un echangeur de chaleur carburant / huile |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9249800B2 (en) * | 2012-11-01 | 2016-02-02 | Hamilton Sundstrand Corporation | Bypass directional control valve |
EP3017166B1 (fr) * | 2013-07-03 | 2020-01-22 | United Technologies Corporation | Tamis filtrants chauffés électriquement |
EP3044443B1 (fr) * | 2013-09-10 | 2018-08-08 | United Technologies Corporation | Système de gestion de combustible pour un moteur à turbine |
FR3021360B1 (fr) * | 2014-05-21 | 2020-02-28 | Safran Aircraft Engines | Circuit d'alimentation en fluide de geometries variables et circuit d'alimentation de systeme d'injection |
US9850917B2 (en) * | 2014-09-23 | 2017-12-26 | Woodward, Inc. | Pump authority switching apparatus for a fluid distribution system |
FR3028245B1 (fr) * | 2014-11-06 | 2019-05-24 | Airbus Operations | Circuit d'alimentation en carburant d'un aeronef |
US9512783B2 (en) * | 2014-11-14 | 2016-12-06 | Hamilton Sundstrand Corporation | Aircraft fuel system |
US20160178204A1 (en) * | 2014-12-18 | 2016-06-23 | Rolls-Royce Plc | Means and arrangement for fuel icing protection |
GB201608449D0 (en) * | 2016-05-13 | 2016-06-29 | Rolls Royce Controls & Data Services Ltd | Axial piston pump |
US20180016024A1 (en) * | 2016-07-12 | 2018-01-18 | United Technologies Corporation | Electric heating for fuel system components |
FR3074533B1 (fr) | 2017-12-06 | 2020-11-06 | Safran Aircraft Engines | Circuit de commande hydraulique et pneumatique pour turboreacteur a echangeur de chaleur carburant/air |
US11236682B2 (en) * | 2018-02-22 | 2022-02-01 | Hamilton Sundstrand Corporation | Fuel pump systems for turbomachines |
WO2019167276A1 (fr) * | 2018-03-02 | 2019-09-06 | 三菱日立パワーシステムズ株式会社 | Système de stockage de gaz combustible pour turbine à gaz et procédé d'alimentation de turbine à gaz en gaz combustible |
EP3594475A1 (fr) * | 2018-07-10 | 2020-01-15 | Siemens Aktiengesellschaft | Procédé de fonctionnement d'une installation de turbine à gaz à combustible gazeux |
US20230358174A1 (en) * | 2022-05-06 | 2023-11-09 | Hamilton Sundstrand Corporation | Aircraft fuel pumping system |
US20230383736A1 (en) * | 2022-05-26 | 2023-11-30 | Hamilton Sundstrand Corporation | Dual pump fuel systems |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1018598A2 (fr) * | 1999-01-06 | 2000-07-12 | Lucas Industries Limited | Système de carburant |
EP1020637A1 (fr) * | 1999-01-14 | 2000-07-19 | Snecma Moteurs | Circuit de carburant à filtre principal protégé |
EP1329617A2 (fr) * | 2002-01-22 | 2003-07-23 | Hamilton Sundstrand Corporation | Système d' écoulement de fluide pour un moteur à turbine à gaz |
US20040011052A1 (en) * | 2002-07-18 | 2004-01-22 | Argo-Tech Corporation | Fuel delivery system |
FR2925594A1 (fr) * | 2007-12-20 | 2009-06-26 | Hispano Suiza Sa | Systeme de regulation d'une turbomachine |
FR2935749A1 (fr) * | 2008-09-11 | 2010-03-12 | Hispano Suiza Sa | Circuit de carburant de turbomachine aeronautique |
US20100089026A1 (en) * | 2008-10-15 | 2010-04-15 | Woodward Governor Company | Fuel Delivery and Control System Including a Variable Displacement Actuation Pump Supplementing a Fixed Displacement Main Pump |
Family Cites Families (34)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2916875A (en) * | 1953-09-09 | 1959-12-15 | Rolls Royce | Gas turbine engine fuel systems |
US3908360A (en) * | 1973-02-08 | 1975-09-30 | Chandler Evans Inc | Pump metering fuel control system |
US4607486A (en) * | 1983-12-02 | 1986-08-26 | United Technologies Corporation | Centrifugal main fuel pump |
GB2197909B (en) * | 1986-11-26 | 1991-07-31 | Rolls Royce Plc | Fuel control system for gas turbine aeroengine overspeed protection. |
US4915593A (en) * | 1987-12-24 | 1990-04-10 | Sundstrand Corporation | Fluid supply system with turbine driven start pump |
US5159808A (en) * | 1990-07-09 | 1992-11-03 | General Electric Company | Gas turbine engine fuel and hydraulic fluid pumping system |
US5168704A (en) * | 1990-08-17 | 1992-12-08 | General Electric Company | Gas turbine engine fuel and actuation pressure pumping system |
US5116362A (en) * | 1990-12-03 | 1992-05-26 | United Technologies Corporation | Fuel metering and actuation system |
US6135135A (en) * | 1997-12-12 | 2000-10-24 | Alliedsignal Inc. | Force balanced proportional bypass valve |
FR2806488B1 (fr) * | 2000-03-16 | 2002-05-17 | Snecma Moteurs | Dispositif et procede de regulation de pression et debit de carburant d'alimentation d'une unite de servovannes |
DE60129185T2 (de) * | 2000-05-12 | 2008-03-13 | Goodrich Control Systems Ltd., Luton | Überwachungsanordnung um den Zustand eines Ventils in einem Kraftstoffzufuhrsystem feststellen zu können |
US6487847B1 (en) * | 2000-11-03 | 2002-12-03 | General Electric Company | Gas turbine engine fuel control system |
DE10127196A1 (de) * | 2001-06-05 | 2002-12-12 | Rolls Royce Deutschland | Verfahren zur Brennstoffversorgung sowie Brennstoffversorgungssystem für ein mit zumindest einer Fluggasturbine versehenes Flugzeug |
FR2882095B1 (fr) * | 2005-02-17 | 2011-05-06 | Hispano Suiza Sa | Alimentation en carburant d'un moteur d'aeronef |
US7540141B2 (en) * | 2005-12-13 | 2009-06-02 | Hamilton Sundstrand Corporation | Smart fuel control system |
GB0708745D0 (en) * | 2007-05-04 | 2007-06-13 | Rolls Royce Plc | Fuel supply system |
FR2922264B1 (fr) * | 2007-10-12 | 2009-12-04 | Hispano Suiza Sa | Circuit d'alimentation en carburant d'un moteur d'aeronef |
US8348630B2 (en) * | 2008-08-18 | 2013-01-08 | Woodward, Inc. | Flow compensated proportional bypass valve combined with a control valve |
US8276360B2 (en) * | 2009-05-22 | 2012-10-02 | Hamilton Sundstrand Corporation | Dual-pump fuel system and method for starting a gas turbine engine |
FR2950864B1 (fr) * | 2009-10-06 | 2011-11-25 | Snecma | Circuit d'alimentation en carburant d'un moteur d'aeronef |
FR2950863B1 (fr) | 2009-10-06 | 2012-03-02 | Snecma | Circuit d'alimentation en carburant d'un moteur d'aeronef |
US20110146288A1 (en) * | 2009-12-23 | 2011-06-23 | General Electric Company | Method of controlling a fuel flow to a turbomachine |
FR2959529B1 (fr) * | 2010-04-28 | 2014-04-18 | Snecma | Systeme carburant de turbomachine avec une pompe a jet pour pompe bp |
US8850818B2 (en) * | 2010-10-18 | 2014-10-07 | General Electric Company | Systems and methods for gas fuel delivery with hydrocarbon removal utilizing active pressure control and dew point analysis |
FR2971548B1 (fr) | 2011-02-11 | 2015-02-13 | Snecma | Systeme d'alimentation en carburant a moyens de pompage multiples |
FR2974149B1 (fr) * | 2011-04-14 | 2015-09-25 | Snecma | Circuit de carburant comportant des moyens de controle d'une pompe |
US9316157B2 (en) * | 2012-02-01 | 2016-04-19 | Hamilton Sundstrand Corporation | Fuel system for starting an APU using a hybrid pump arrangement |
US9206775B2 (en) * | 2012-02-01 | 2015-12-08 | United Technologies Corporation | Fuel preheating using electric pump |
US9140190B2 (en) * | 2012-06-06 | 2015-09-22 | Honeywell International Inc. | Gas turbine engine fuel metering valve adapted to selectively receive fuel flow increase/decrease commands from the engine control and from the back-up fuel control |
FR2999654B1 (fr) * | 2012-12-18 | 2015-02-13 | Snecma | Circuit de carburant d'une turbomachine |
US20140174409A1 (en) * | 2012-12-21 | 2014-06-26 | United Techologies Corporation | Gear Pump Protection Valve |
GB201400153D0 (en) * | 2014-01-06 | 2014-02-19 | Rolls Royce Controls & Data Services Ltd | Enfine fuel control system |
US9885287B2 (en) * | 2014-09-11 | 2018-02-06 | Honeywell International Inc. | Gas turbine engine mechanical-electrical hybrid fuel delivery system |
US10443503B2 (en) * | 2015-03-27 | 2019-10-15 | Pratt & Whitney Canada Corp. | Fuel system for a gas turbine engine |
-
2011
- 2011-01-06 FR FR1150094A patent/FR2970303B1/fr active Active
-
2012
- 2012-01-04 GB GB1312087.8A patent/GB2501198B/en active Active
- 2012-01-04 WO PCT/FR2012/050019 patent/WO2012093235A1/fr active Application Filing
- 2012-01-04 US US13/978,470 patent/US9702301B2/en active Active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1018598A2 (fr) * | 1999-01-06 | 2000-07-12 | Lucas Industries Limited | Système de carburant |
EP1020637A1 (fr) * | 1999-01-14 | 2000-07-19 | Snecma Moteurs | Circuit de carburant à filtre principal protégé |
EP1329617A2 (fr) * | 2002-01-22 | 2003-07-23 | Hamilton Sundstrand Corporation | Système d' écoulement de fluide pour un moteur à turbine à gaz |
US20040011052A1 (en) * | 2002-07-18 | 2004-01-22 | Argo-Tech Corporation | Fuel delivery system |
FR2925594A1 (fr) * | 2007-12-20 | 2009-06-26 | Hispano Suiza Sa | Systeme de regulation d'une turbomachine |
FR2935749A1 (fr) * | 2008-09-11 | 2010-03-12 | Hispano Suiza Sa | Circuit de carburant de turbomachine aeronautique |
US20100089026A1 (en) * | 2008-10-15 | 2010-04-15 | Woodward Governor Company | Fuel Delivery and Control System Including a Variable Displacement Actuation Pump Supplementing a Fixed Displacement Main Pump |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170198640A1 (en) * | 2014-05-26 | 2017-07-13 | Safran Power Units | Device and method for pre-heating fuel in a turbomachine |
FR3116858A1 (fr) * | 2020-12-01 | 2022-06-03 | Safran Aircraft Engines | Ensemble pour turbomachine d’aeronef comprenant une vanne passive de contournement d’un echangeur de chaleur carburant / huile |
WO2022117947A1 (fr) * | 2020-12-01 | 2022-06-09 | Safran Aircraft Engines | Ensemble pour turbomachine d'aeronef comprenant une vanne passive de contournement d'un echangeur de chaleur carburant / huile |
Also Published As
Publication number | Publication date |
---|---|
GB201312087D0 (en) | 2013-08-21 |
FR2970303B1 (fr) | 2014-06-13 |
US9702301B2 (en) | 2017-07-11 |
GB2501198A (en) | 2013-10-16 |
US20130283811A1 (en) | 2013-10-31 |
GB2501198B (en) | 2017-03-22 |
FR2970303A1 (fr) | 2012-07-13 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2012093235A1 (fr) | Circuit de carburant de turbomachine aéronautique a vanne de régulation de pression de carburant. | |
EP1848884B1 (fr) | Dispositif d'alimentation en carburant d'un moteur à turbine à gaz avec debit de carburant regule | |
FR2979671A1 (fr) | Circuits d'huile et de carburant dans une turbomachine | |
EP2961966B1 (fr) | Procédé et dispositif de régulation de refroidissement d'huile d'une turbomachine | |
CA2894226C (fr) | Dispositif et procede d'augmentation temporaire de puissance | |
FR2959529A1 (fr) | Systeme carburant de turbomachine avec une pompe a jet pour pompe bp | |
FR2968041A1 (fr) | Dispositif et procede d'alimentation | |
FR3028888A1 (fr) | Dispositif de refroidissement pour une turbomachine alimente par un circuit de decharge | |
CA2758651A1 (fr) | Procede de detection d'un etat de givrage ou de besoin de maintenance d'un circuit de carburant de turbomachine | |
FR2979004A1 (fr) | Systeme de combustible ayant une unite de controle de combustible et echangeur de chaleur | |
FR2951228A1 (fr) | Procede et systeme de gestion d'echanges thermiques entre fluides dans une turbomachine | |
FR3017655A1 (fr) | Turboreacteur comportant un systeme de prelevement destine a prelever de l'air dans ledit turboreacteur | |
EP3365545B1 (fr) | Recirculation de fluide à travers une pompe centrifuge de turbomachine | |
FR2982319A1 (fr) | Systeme de commande d'une vanne pneumatique de turbomachine | |
EP3521589B1 (fr) | Système de refroidissement d'air moteur à deux étages de refroidissement et procédé correspondant | |
EP3495640B1 (fr) | Circuit de commande hydraulique et pneumatique pour turboréacteur à échangeur de chaleur carburant/air | |
FR2911932A1 (fr) | Dispositif de commande d'organe a geometrie variable dans un turboreacteur. | |
FR3075172A1 (fr) | Circuit pneumatique pour l'alimentation en air d'au moins une vanne de decharge et d'au moins un dispositif de depressurisation d'une enceinte huile d'une turbomachine | |
FR2923861A1 (fr) | Circuit de carburant de turbomachine. | |
FR2935749A1 (fr) | Circuit de carburant de turbomachine aeronautique | |
FR2969701A1 (fr) | Procede et systeme de gestion d'echanges thermiques entre fluides dans une turbomachine aeronautique. | |
FR3095840A1 (fr) | Système de dosage pour circuit de carburant de moteur d’aéronef | |
EP4256189A1 (fr) | Ensemble pour turbomachine d'aeronef comprenant une vanne passive de contournement d'un echangeur de chaleur carburant / huile | |
FR3067061B1 (fr) | Systeme d'alimentation d'un moteur a combustion interne | |
FR3079889A1 (fr) | Controleur pneumatique d'une vanne de decharge de turbomachine avec moyens de refroidissement |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 12702584 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 1312087 Country of ref document: GB Kind code of ref document: A Free format text: PCT FILING DATE = 20120104 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 13978470 Country of ref document: US Ref document number: 1312087.8 Country of ref document: GB |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
122 | Ep: pct application non-entry in european phase |
Ref document number: 12702584 Country of ref document: EP Kind code of ref document: A1 |