WO2013021118A1 - Procédé d ' estimation de la température du carburant en sortie d ' un échangeur d'une turbomachine. - Google Patents
Procédé d ' estimation de la température du carburant en sortie d ' un échangeur d'une turbomachine. Download PDFInfo
- Publication number
- WO2013021118A1 WO2013021118A1 PCT/FR2012/051801 FR2012051801W WO2013021118A1 WO 2013021118 A1 WO2013021118 A1 WO 2013021118A1 FR 2012051801 W FR2012051801 W FR 2012051801W WO 2013021118 A1 WO2013021118 A1 WO 2013021118A1
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- WO
- WIPO (PCT)
- Prior art keywords
- oil
- fuel
- temperature
- output
- engine
- Prior art date
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K13/00—Thermometers specially adapted for specific purposes
- G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
-
- 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
- F02C7/06—Arrangements of bearings; Lubricating
-
- 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
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
-
- 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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
-
- 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
- F05D2270/01—Purpose of the control system
- F05D2270/07—Purpose of the control system to improve fuel economy
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a method for determining the temperature of the fuel at the outlet of an exchanger of a turbomachine.
- turbomachine It is useful to know the temperature of the fuel in the oil / fuel system of a turbomachine, in particular to refine the control laws of the variable geometries, to estimate the density of the fuel, to improve the measurement of the fuel flow meter, or to refine the fuel dosage laws. This is why some turbomachines are sometimes provided with a temperature sensor disposed generally at the inlet of the injectors in order to know the fuel temperature at the inlet of the injectors. However, the multiplicity of measuring means in the turbine engine weighs down the latter and increases its cost.
- the invention aims to remedy the drawbacks of the state of the art by proposing a method for determining the fuel temperature in an oil / fuel system of a turbomachine which does not use a specific sensor of this temperature.
- a method for estimating the temperature of the fuel at the outlet of an oil / fuel exchanger of a turbomachine comprising engine enclosures, enclosures motor and the oil / fuel exchanger being traversed by oil, the oil / fuel exchanger having an efficiency, the engine enclosures comprising a high pressure body, the method comprising the following steps:
- (c) A step of calculating the temperature of the fuel at the outlet of the oil / fuel exchanger from the temperature of the engine inlet oil and the speed of rotation of the high pressure body.
- the invention proposes to reuse the data already measured in the turbomachine for other purposes to calculate the temperature in the fuel circuit.
- the method according to the invention therefore makes it possible to know the fuel temperature at the inlet of the injectors without using a specific sensor.
- the method according to the invention proposes in particular to use the measures of: the temperature of the oil which enters the engine chambers in order to lubricate and cool it, and
- the method according to the invention may also have one or more of the features below taken individually or in any technically possible combination.
- the method according to the invention is preferably applied to a turbomachine comprising:
- an injector capable of injecting fuel into the combustion chamber; a hydromechanical block upstream of the injector, the hydromechanical block being able to measure the quantity of fuel injected into the combustion chamber;
- an oil circuit to lubricate and cool the engine enclosure; an oil / fuel exchanger upstream of the hydromechanical block, the oil / fuel exchanger being traversed by the fuel and the oil from the engine enclosures;
- the fuel tank is able to store the fuel which then passes through the oil / fuel exchanger, before passing through the hydromechanical block and the injector.
- the rotating body is a high pressure body.
- the fuel pump and the oil pump are driven at a speed proportional to that of the high pressure body and the components of the engine enclosures dissipate power in proportion to that of the high pressure body.
- the method would also be applicable in the case where the rotating body is a low pressure body, provided that the rotational speed of the fuel pump and the oil pump can be calculated, as well as the power dissipated in the engine enclosures from this rotational speed of the low pressure body.
- the step of calculating the temperature of the fuel at the outlet of the oil / fuel exchanger preferably comprises, first of all, a sub-step of calculating the temperature of the oil at the outlet of the engine enclosures.
- This calculation of the oil temperature at the output of the engine enclosures may for example comprise the following sub-steps: - Calculation of the oil flow in the engine enclosure from the speed of rotation of the high pressure body and possibly the altitude;
- the temperature of the oil output of the engine enclosure is similar to the oil temperature at the inlet of the engine. the oil / fuel exchanger, provided that there is no other exchanger that is taken into account in the circuit.
- the step of calculating the temperature of the fuel at the outlet of the oil / fuel exchanger then comprises, in addition, the following sub-steps:
- the method according to the invention therefore makes it possible to have a good approximation of the fuel temperature at the inlet of the injectors, without, however, adding temperature sensors in the turbomachine. Other calculation steps can be performed according to the desired accuracy for the inlet temperature of the injector.
- the method according to the invention can also be applied to a turbomachine further comprising an air / oil exchanger between the engine chambers and the oil / fuel exchanger, the turbomachine further comprising a fan.
- the step of calculating the temperature of the fuel at the outlet of the oil / fuel exchanger the temperature of the oil at the outlet of the engine enclosures is no longer compared to the temperature of the oil. input of the oil / fuel exchanger, so that the step of calculating the temperature at the outlet of the oil / fuel exchanger comprises, following the step of calculating the temperature of the oil output of the engine enclosures , a step of calculating the temperature of the oil at the outlet of the air oil exchanger.
- the method further comprises a step of measuring the temperature of the air upstream of the blower.
- the step of calculating the temperature of the fuel at the outlet of the oil / fuel exchanger further comprises a sub-step of calculating the temperature of the oil at the outlet of the air / oil exchanger from the air temperature upstream of the blower and oil temperature at the output of the engine enclosure.
- the temperature of the oil at the inlet of the oil / fuel exchanger is then equated with the temperature of the oil at the outlet of the air / oil exchanger, so that the step of calculating the temperature at the outlet of the oil / fuel exchanger then comprises the following sub-steps:
- the method can also be applied to other types of exchangers, in a larger or smaller number, in any order.
- Another aspect of the invention also relates to a computer implementing the method according to the first aspect of the invention, and a turbomachine comprising such a computer.
- FIG. 1 a diagrammatic representation of an oil / fuel system of a turbomachine to which the method according to the invention applies;
- FIG. 2 a schematic representation of the steps of the method implemented in the circuit of FIG. 1;
- FIG. 3 a schematic representation of another oil / fuel system of a turbomachine to which the method according to the invention applies;
- FIG. 4 a schematic representation of the steps of the method implemented in the circuit of FIG. 3.
- FIG. 1 diagrammatically represents an oil / fuel system of a turbomachine to which the method according to the invention applies.
- This turbomachine comprises a fuel tank 1 capable of storing fuel.
- the turbomachine also comprises a low pressure stage 2 downstream of the fuel tank.
- upstream and downstream are used with reference to the direction of circulation of the fluids in the oil / fuel system and in particular with reference to the direction of circulation of the fuel in the turbomachine.
- the fuel circuit in the turbomachine is represented by a solid double line.
- the circuit of the oil in the turbomachine is represented by a dashed line.
- the oil / fuel system also comprises an oil / fuel exchanger 3 which is able to be traversed by oil and by fuel, so as to allow heat exchange between these two fluids.
- the oil / fuel exchanger 3 is downstream of the low pressure stage 2.
- the oil / fuel system also comprises a high pressure stage 4 downstream of the oil / fuel exchanger 3.
- the oil / fuel system also comprises a hydromechanical block 5 downstream of the high pressure stage 4.
- the hydromechanical block makes it possible to determine the quantity of fuel that is sent towards the combustion chamber of the turbomachine.
- the oil / fuel system also comprises one or more injectors 7 downstream of the hydromechanical block. The injector or injectors allow to inject fuel into the combustion chamber.
- the oil / fuel system also comprises a recirculation loop 6 between the hydromechanical block 5 and the outlet of the low pressure stage 2. This recirculation loop 6 makes it possible to return a portion of the fuel that is not injected into the chamber of combustion.
- the oil / fuel system also comprises engine enclosures 8 which are lubricated with oil 9.
- the oil / fuel system may also include a servo valve heater.
- a method according to the invention for estimating the fuel temperature at the inlet of the injector (s) 7 of the turbomachine of FIG. 1 will now be described with reference to FIG. 2.
- the method uses quantities measured elsewhere in the turbomachine, for example for the control of the engine enclosures, to estimate the fuel temperature at the inlet of the injector or injectors, thanks to a thermal balance in the turbomachine.
- the method comprises a step 101 for measuring the temperature of the oil T hui i e motor input to the input of the motor enclosures.
- This temperature T hui i e engine inlet is measured elsewhere to avoid oil overtemperature in the engine enclosure.
- This temperature T hui i e engine input is for example measured by a thermocouple.
- the method also comprises a step 102 for measuring the high pressure regime, that is to say the rotational speed XN25 of the high pressure body.
- the rotational speed of the XN25 high pressure body is measured in the engine control system anyway.
- the rotational speed of the XN25 high pressure body is for example measured by means of an inductive gear sensor.
- the steps of measuring the oil temperature at the inlet of the engine enclosure 101 and measuring the rotational speed of the high pressure body 102 can be performed in any order, or simultaneously.
- the method then comprises a step 103 for calculating the fuel temperature T AC input rburant mjecteur the input of the injector or injectors, which amounts to calculating the temperature of the fuel at the outlet of the oil / fuel rburant T AC output MHX
- This calculation is made in particular from the temperature of the engine inlet oil T hui i e engine inlet and the speed of rotation of the HP XN25 body, thanks to a thermal balance in the turbomachine.
- this calculation of the fuel temperature at the outlet of the oil / fuel exchanger firstly comprises a sub-step 1 1 1 for calculating the temperature of the oil at the output of the engine enclosures T hui i e motor output .
- a sub-step 1 1 1 for calculating the temperature of the oil at the output of the engine enclosures T hui i e motor output .
- the QnuNe oil flow that passes through the engine enclosures can also be calculated from the altitude ALT of the turbomachine.
- the method further comprises a step 104 for determining the altitude of the turbomachine.
- the coefficients a and b are preferably determined empirically during test phases prior to flight.
- the density of the oil RhOnuNe and the specific heat of the oil Cp hui i e can then be calculated, in a sub-step 123, from the temperature of the oil entering the engine enclosures T hui i e engine input j for example through the following formulas:
- Oil oil + engine oil (oil or oil)
- the temperature of the oil is then assimilated to the output of the engine chambers T hui i e engine output at the oil temperature at the inlet of the oil / fuel heat exchanger T huNe input - MHX .
- thermal power dissipated in the engine enclosure Pmoteur is equal to the thermal power dissipated in the oil / fuel heat exchanger PMHX-
- the efficiency of the Eff M Hx oil / fuel exchanger is taken as a constant. This constant is determined empirically. This constant can for example be taken equal to 0.5 whatever the phase of the flight and the temperatures of the fluids. However, this efficiency could also be variable depending on other parameters, so as to increase the accuracy of the method according to the invention.
- the step of calculating the temperature of the fuel at the inlet of the injector or injectors then comprises a sub-stage 1 1 2 calculation of the fuel temperature at the inlet of the oil / fuel heat exchanger T C entering the MHX inlet from the temperature oil output from the engine enclosures T hui i e motor output , the inlet temperature of the engine inlet T hui i e engine inlet and efficiency of the exchanger Eff M Hx, for example thanks to the following formula:
- I fuel I oil + I oil "I oil / ⁇
- the process then comprises a substep of calculation 14 of the Qcarburam fuel flow through the oil / fuel exchanger from the rotational speed of the XN25 high pressure body, for example through to the following formula:
- the step of calculating the temperature of the injector or injectors into the fuel then comprises a sub step 1 15 of calculating the temperature of the fuel at the outlet of the oil / fuel T ca rburant MHX output from the temperature of the fuel inlet of the oil / fuel rburant T AC input MHX, the power dissipated in the oil / fuel P M HX, Qhuiie the oil flow, the density of the fuel Rho ca rburant and heat specific fuel Cp ca rburant, for example using the following formula:
- FIG. 3 diagrammatically represents another turbomachine to which the method according to the invention applies.
- This turbine engine is identical to that described above, with the exception that it further comprises an air / oil exchanger January 1 disposed between the output of the engine enclosure 8 and the oil / fuel exchanger 3.
- the method could also s apply in the case where the air / oil exchanger is arranged at other locations of the oil / fuel system.
- the method used is identical to that used to estimate the temperature of the fuel in the turbine engine of FIG. 1, except that the temperature at the inlet of the oil / fuel exchanger T hui i e enters MHX is no longer assimilated to the oil temperature at the output of the engine enclosure T hui i e engine output , but that of the oil output of the fuel oil exchanger T hui i e ACOC output .
- the method according to this embodiment comprises a step 101 for measuring the temperature of the oil T hui i e motor input to the input of the motor chambers and a step 102 for measuring the high pressure regime, that is to say the XN25 rotational speed of the high pressure body in the engine enclosures.
- the method further comprises a step 106 for measuring the temperature of the air T12 at the inlet of the fan of the turbomachine. This air temperature at the inlet of the blower T12 will make it possible to calculate the temperature of the oil at the outlet of the air / oil exchanger.
- This measurement step 106 may be simultaneous, posterior or anterior to the measurement steps 101 and 102.
- the method then comprises, as in the previous embodiment, a step 103 for calculating the temperature of the fuel at the outlet of the oil / fuel rburant T AC output MHX from measurements made during steps 101, 102 and 106 , thanks to a thermal balance in the turbomachine.
- the method firstly comprises a substep 1 1 1 for calculating the temperature of the oil output of the engine speakers T hui i e motor output .
- the method further comprises a step 104 for determining the altitude of the turbomachine.
- the coefficients a and b are preferably determined empirically during test phases prior to flight.
- the density of the oil Rhohuiie and the specific heat of the oil Cp hui i e from the oil temperature can then be calculated in a sub-step 123. at the input of the motor enclosures T hui i e motor input j for example with the following formulas:
- the method then comprises a sub-step 1 16 for calculating the temperature of the oil at the outlet of the air / oil exchanger T hui i e ACOC output from the temperature of the oil output of the engine enclosures T hui i the motor output and the air temperature at the inlet of the blower T12.
- this efficiency is taken equal to 0.25 whatever the phase of flight and the fluid temperatures.
- other values for efficiency could be chosen, and in particular one could take variable efficiency.
- the temperature T hui i e ACOC output can then be given by the following formula: ACOC output ⁇ motor output * / cff ⁇ , Cff * ⁇ / ⁇ ⁇ ⁇ ⁇ ⁇
- I oil oil (1 - tTiACOC) + tiAACOC T (f (T12) being a function which depends on T12, and which may also depend on other parameters.
- the temperature of the fuel at the outlet of the oil / fuel exchanger T hui i e output MHX is calculated .
- the power dissipated by the oil / fuel exchanger P M HX- This power can be determined as in the previous embodiment, or it can be determined by the following formula:
- the efficiency of the oil / fuel exchanger Eff M Hx is taken, as in the previous embodiment, equal to a constant, preferably 0.5.
- the fuel inlet temperature of the oil / fuel heat exchanger T C flowing in between MHX from the temperature of the oil is calculated as in the previous embodiment.
- output of the oil / fuel heat exchanger T hU iie ACOC output , the oil temperature at the inlet of the engine speakers T hU ii e engine inlet , and the efficiency of the oil / fuel exchanger Eff M HX by example using the following formula: input MHX output ACOC, ir input motor output / c "
- the method then comprises a sub-step 1 14 for calculating the Qcarburam fuel flow rate through the oil / fuel exchanger from the rotational speed of the XN25 high-pressure body, for example by the following formula:
- the temperature of the fuel at the outlet of the oil / fuel exchanger T C arburant output MHX from the temperature of the fuel is calculated.
- the fuel temperature at the outlet of the oil / fuel exchanger is equal to the fuel temperature at the inlet of the injector or injectors.
- the method is not limited to the embodiments described with reference to the figures.
- other formulas could be used to calculate the different values given above according to the precision that is to be achieved.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
Description
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Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1402138.0A GB2508530B (en) | 2011-08-08 | 2012-07-31 | Method of estimating the temperature of the fuel leaving a turbomachine exchanger |
US14/237,837 US10018519B2 (en) | 2011-08-08 | 2012-07-31 | Method of estimating the temperature of the fuel leaving a turbomachine exchanger |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1157225 | 2011-08-08 | ||
FR1157225A FR2978986B1 (fr) | 2011-08-08 | 2011-08-08 | Procede d'estimation de la temperature du carburant en sortie d'un echangeur d'une turbomachine |
Publications (1)
Publication Number | Publication Date |
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WO2013021118A1 true WO2013021118A1 (fr) | 2013-02-14 |
Family
ID=46724518
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/FR2012/051801 WO2013021118A1 (fr) | 2011-08-08 | 2012-07-31 | Procédé d ' estimation de la température du carburant en sortie d ' un échangeur d'une turbomachine. |
Country Status (3)
Country | Link |
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US (1) | US10018519B2 (fr) |
FR (1) | FR2978986B1 (fr) |
WO (1) | WO2013021118A1 (fr) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
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US9140504B1 (en) * | 2012-02-02 | 2015-09-22 | The United States Of America As Represented By The Secretary Of The Army | Performance testing apparatus for microclimate cooling unit |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3779007A (en) * | 1972-04-28 | 1973-12-18 | Gen Electric | Fuel delivery and control system for a gas turbine engine |
US5177951A (en) * | 1989-04-06 | 1993-01-12 | Rolls-Royce Plc | Method for management of heat generated by aircraft gas turbine installations |
US20040119293A1 (en) * | 2002-12-12 | 2004-06-24 | Ebara Corporation | Gas turbine apparatus |
US20070169997A1 (en) * | 2006-01-25 | 2007-07-26 | Honeywell International, Inc. | Airframe mounted motor driven lubrication pump control system and method |
FR2951228A1 (fr) * | 2009-10-13 | 2011-04-15 | Snecma | Procede et systeme de gestion d'echanges thermiques entre fluides dans une turbomachine |
GB2477362A (en) * | 2010-01-29 | 2011-08-03 | Rolls Royce Plc | Oil cooler for gas turbine engine |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS6056894B2 (ja) * | 1977-05-18 | 1985-12-12 | トヨタ自動車株式会社 | 熱交換器付一軸式ガスタ−ビンの始動時および加速時における燃料制御方法および装置 |
US5241814A (en) * | 1989-04-06 | 1993-09-07 | Rolls-Royce Plc | Management of heat generated by aircraft gas turbine installations |
US8776952B2 (en) * | 2006-05-11 | 2014-07-15 | United Technologies Corporation | Thermal management system for turbofan engines |
US7997062B2 (en) * | 2009-01-29 | 2011-08-16 | Pratt & Whitney Canada Corp. | Dual channel regulated fuel-oil heat exchanger |
WO2011021291A1 (fr) * | 2009-08-20 | 2011-02-24 | 三菱重工業株式会社 | Dispositif de ventilation pour aérogénérateur et aérogénérateur |
CN102575577B (zh) * | 2010-02-09 | 2014-08-20 | 三菱重工业株式会社 | 带涡轮增压器发动机的控制装置 |
US9004154B2 (en) * | 2010-08-31 | 2015-04-14 | Pratt & Whitney | Combination fuel-oil and air-oil heat exchanger |
US8459033B2 (en) * | 2011-07-05 | 2013-06-11 | General Electric Company | Systems and methods for modified wobbe index control with constant fuel temperature |
FR2978211B1 (fr) * | 2011-07-19 | 2013-08-23 | Snecma | Procede de surveillance d'un clapet de surpression d'un circuit d'injection de carburant pour turbomachine |
-
2011
- 2011-08-08 FR FR1157225A patent/FR2978986B1/fr active Active
-
2012
- 2012-07-31 WO PCT/FR2012/051801 patent/WO2013021118A1/fr active Application Filing
- 2012-07-31 US US14/237,837 patent/US10018519B2/en active Active
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3779007A (en) * | 1972-04-28 | 1973-12-18 | Gen Electric | Fuel delivery and control system for a gas turbine engine |
US5177951A (en) * | 1989-04-06 | 1993-01-12 | Rolls-Royce Plc | Method for management of heat generated by aircraft gas turbine installations |
US20040119293A1 (en) * | 2002-12-12 | 2004-06-24 | Ebara Corporation | Gas turbine apparatus |
US20070169997A1 (en) * | 2006-01-25 | 2007-07-26 | Honeywell International, Inc. | Airframe mounted motor driven lubrication pump control system and method |
FR2951228A1 (fr) * | 2009-10-13 | 2011-04-15 | Snecma | Procede et systeme de gestion d'echanges thermiques entre fluides dans une turbomachine |
GB2477362A (en) * | 2010-01-29 | 2011-08-03 | Rolls Royce Plc | Oil cooler for gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
FR2978986B1 (fr) | 2013-08-23 |
US20140177670A1 (en) | 2014-06-26 |
US10018519B2 (en) | 2018-07-10 |
FR2978986A1 (fr) | 2013-02-15 |
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