EP1312863A1 - Verbesserungen an Turbomaschineninjektoren - Google Patents

Verbesserungen an Turbomaschineninjektoren Download PDF

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Publication number
EP1312863A1
EP1312863A1 EP02292867A EP02292867A EP1312863A1 EP 1312863 A1 EP1312863 A1 EP 1312863A1 EP 02292867 A EP02292867 A EP 02292867A EP 02292867 A EP02292867 A EP 02292867A EP 1312863 A1 EP1312863 A1 EP 1312863A1
Authority
EP
European Patent Office
Prior art keywords
fuel
valve
injector
pressure
flow
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP02292867A
Other languages
English (en)
French (fr)
Other versions
EP1312863B1 (de
Inventor
Marion Michau
José Rodrigues
Alain Tiepel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Transmission Systems SAS
Original Assignee
Hispano Suiza SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hispano Suiza SA filed Critical Hispano Suiza SA
Publication of EP1312863A1 publication Critical patent/EP1312863A1/de
Application granted granted Critical
Publication of EP1312863B1 publication Critical patent/EP1312863B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K5/00—Feeding or distributing other fuel to combustion apparatus
    • F23K5/02—Liquid fuel
    • F23K5/14—Details thereof
    • F23K5/147—Valves
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/2496—Self-proportioning or correlating systems
    • Y10T137/2559—Self-controlled branched flow systems
    • Y10T137/265—Plural outflows
    • Y10T137/2663—Pressure responsive

Definitions

  • the present invention relates to improvements supplied to fuel injectors for a turbomachine engine. She relates more particularly to the adjustment of the flow rate of injected fuel in a turbomachine combustion chamber.
  • a turbomachine engine comprises several injectors for supplying fuel and air to the combustion chamber during start-up and normal operation of the turbomachine engine.
  • injectors for supplying fuel and air to the combustion chamber during start-up and normal operation of the turbomachine engine.
  • injectors there are two types injectors: so-called “aeromechanical” injectors designed for two fuel flows (primary and secondary) according to the phases of engine operation (ignition, low to full power), and so-called “aerodynamic” injectors which have only one circuit fuel for all operating phases.
  • the current the invention relates more particularly to the injectors belonging to this first category.
  • a fuel injector aeromechanics for a turbomachine engine has two circuits fuel supply: a primary circuit corresponding to low flow rates (intended for example for an ignition and running at low engine power) and a secondary circuit intervening for medium and high flows (intended for example to subsequent operating phases until full power).
  • This type of injector notably includes a shut-off valve intended to open for a first predetermined pressure fuel supply and remain open beyond this pressure to supply the primary fuel circuit.
  • a metering valve arranged to open under a second pressure predetermined feed, greater than the first press predetermined, and remain open in response to an increase in this pressure, provides the fuel feed rate of the secondary circuit.
  • the adjustment of this secondary flow is carried out by through dosing slots provided at a head of the valve and whose passage sections vary depending on the pressure applied supply: the higher this pressure, the more the sections Passing slots are important.
  • the present invention therefore aims to overcome such drawbacks by proposing a fuel injector which reduces the flow heterogeneity between injectors.
  • An object of the invention is also to propose an injector to simplify production and improve the performance of adjusting the average fuel flow rates.
  • an engine fuel injector is provided. of a turbomachine comprising an injector body having means pressure fuel inlet, a first valve fitted downstream of said pressure fuel admission means and arranged to open in response to a predetermined pressure of fuel defining a first threshold pressure in order to admit fuel in the injector body, a second valve mounted in downstream of said first valve and capable of opening in response to a second fuel threshold pressure, higher than said first threshold pressure, in order to dose at least part of the admitted fuel in said injector body to means for using this fuel, the flow of fuel dosed to the means of use being a function of passage sections practiced at said level second valve, characterized in that it further comprises a diaphragm disposed between the fuel intake means under pressure and the first valve in order to fix at a determined value the fuel flow admitted into the injector body.
  • the fuel flow admitted into the injector body is including function of the diaphragm. It is fixed at a determined value by choosing an aperture according to the technical characteristics specific to each injector of the same combustion chamber. More precisely, we choose a diaphragm for each injector according to its differences in flow compared to a flow calculated means.
  • each injector of the same chamber of combustion is provided with a diaphragm which can vary from injector to the other. In this way, we eliminate any risk of flow differences between the different injectors.
  • replacing the diaphragm is easy since it does not require disassembly of the two valves.
  • the injector further comprises means for setting to define a third fuel threshold pressure, higher than the second threshold pressure, from which the flow of fuel dosed to the means of use is solely a function of fuel supply pressure.
  • the adjustment means for defining a third pressure of fuel threshold advantageously include a stop to limit the stroke of the second fuel metering valve.
  • Figure 1 shows in longitudinal section a fuel injector for a turbomachine engine according to the invention.
  • This injector is of the aeromechanical type, i.e. it is designed to provide two fuel flows: a primary flow for a start-up phase of the turbomachine equipped with this injector and a low power operating phase, and a secondary flow for subsequent operating phases and up to full power.
  • the fuel injector 2 comprises, in a injector body 4, a fuel intake orifice 6 intended for receive pressurized fuel from a suitable pump (not shown) and which leads into a pre-admission chamber 8a after passing through filtering means 9 of the strainer type.
  • a sealing valve 10 intended to seal the injector at the stop is mounted in an intake chamber 8b arranged downstream of the pre-admission chamber 8a in the direction of flow of the combustible. It is conventionally formed by a valve head 12 and a valve stem 14 and is held in position by means of a tubular central part 16 forming a valve support.
  • the part tubular central unit 16 also rests by a cylindrical shoulder 17, on a first end of a cylindrical peripheral part 18 which extends downstream from the central part over a large part of the volume internal remaining of the injector body 4 and which delimits a chamber annular primary fuel 20 and an annular chamber of secondary fuel 22.
  • the annular primary fuel chamber 20 communicates with the inlet chamber 8b via a plurality of holes lateral 24 and through a strainer 25 defining sections of fixed passage.
  • the annular secondary fuel chamber 22 is connected to the intake chamber 8b through longitudinal bores 26 drilled regularly in the cylindrical shoulder 17 of the support valve 16.
  • the seat of the sealing valve 10 is formed by a flange a cylindrical jacket 28 resting on the cylindrical shoulder 17 of the central tubular part 16 and held in the injector body 4 of sealingly by means of a sealing means 30 of the type seal.
  • a coil spring 32 is disposed between the valve support 16 and the valve head 12 to allow adjustment of a pressure predetermined fuel supply defining a first threshold pressure S1 above which the sealing valve 10 opens.
  • the fuel present in the pre-admission chamber 8a then enters the intake chamber 8b and flows into the chamber annular primary fuel 20 through side holes 24 before being evacuated to a central fuel ejection channel primary 33 defining first means of using the fuel.
  • a fuel metering device 34 is also mounted directly into the annular secondary fuel chamber 22 of so as to dose the fuel flowing from this chamber. He understands conventionally a metering valve 36 of tubular shape provided with a first end of an opening 38 opening into a bore longitudinal 40 secondary fuel intake, and one second end forming a bottom, with a substantially circular shoulder forming valve head 42 and supporting a second end of the part cylindrical peripheral 18.
  • the metering valve 36 comprises also side outlets 44 for fuel flow secondary.
  • the valve head 42 has slots around its periphery metering 46 of the fuel opening in the longitudinal bore 40 and defining variable passage sections towards second means fuel use. These slots 46 are shaped very precisely to measure the amount of fuel flowing from the annular secondary fuel chamber 22 to a reception 48 formed in the injector body 4 and opening towards a annular secondary fuel ejection channel 50 surrounding the channel primary fuel ejection center 33.
  • Metering valve 36 can slide in a socket cylindrical 52, one end of which has a circular recess 54 forming valve seat.
  • This socket is held on the part cylindrical device 18 in a sealed manner by means of a sealing means 56 of the joint type.
  • the socket 52 also forms a bearing surface for one end of a helical spring 58 of which the opposite end is mounted in an annular retaining element 60 threaded on the first end of the metering valve 36 and fixed to this using a ring 62 in C.
  • An annular wedge 64 is arranged between the ring 62 at C and the annular retaining element 60 so as to adjust the load of the spring 58 and define a second threshold pressure S2, higher than the first threshold pressure S1, for which the pressure relief valve dosage 36 opens.
  • This spring load is chosen so that allow the metering valve to open for the second pressure of S2 threshold and stay open in response to an increase in the supply pressure, the flow supplied then being a function of the sections of passage of the dosing slots 46.
  • the injector 2 is further provided with a diaphragm 66 disposed between the inlet 6 and the sealing valve 10. More precisely, the diaphragm 66 is mounted in the pre-admission chamber 8a upstream, in the direction of flow of the fuel, from the cylindrical jacket 28 resting on the cylindrical peripheral part 18. This diaphragm allows the flow rate of fuel admitted into the intake chamber 8b.
  • the opening of diaphragm is chosen according to the characteristics specific to the injector (manufacture and machining of the metering valve and its slits, spring tension, effects of friction between the valve and the socket in which it slides ...) and according to its flow differences by compared to a calculated average flow.
  • This choice is therefore made so as to what the curve of average flows as a function of pressure fuel supply does not come out of a tolerance envelope preset.
  • This tolerance envelope is pre-established according to a theoretical average calculated flow curve. For example, it can be defined by a maximum flow deviation of the order of ⁇ 5% compared to this theoretical mean curve.
  • the injector of fuel further comprises adjustment means for defining a third fuel threshold pressure S3, greater than the second threshold pressure S2, from which the fuel flow metered to the second means of use is only a function of the pressure fuel supply.
  • adjustment means are presented under the shape of a stop 68, for example mounted at the socket 52 so as to cooperate with the annular retaining element 60 to limit the stroke of the metering valve 36.
  • This stop 68 is adjusted for a predetermined fuel pressure corresponding to a close flow rate of full opening. It is also possible to consider climbing a ring (not shown) on the first end of the check valve dosage 36, this ring also making it possible to limit the stroke of the metering valve.
  • Figure 2 clearly shows the effect of diaphragm 66 on the differences average flows that may exist at an injector 200 of a combustion chamber with respect to a calculated flow curve 202.
  • two curves 204 and 204 ′ have also been represented. They form an envelope of tolerance beyond which the deviations of flows compared to the theoretical average curve 202 are considered too large. For this envelope of tolerance, a maximum flow deviation of ⁇ 5% was chosen. So the presence of diaphragm 66 makes it possible to considerably reduce heterogeneity in terms of average flow rates between several injectors of the same combustion chamber.
  • the fuel flow is no longer a function of machining characteristics of the spring and slots, as well as friction of the injector valve but of the supply pressure in fuel and the valve flow section which is in stop. From this third threshold pressure S3, the valve dosing thus behaves like a fixed diaphragm.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
EP02292867A 2001-11-20 2002-11-19 Verbesserungen an Turbomaschineninjektoren Expired - Lifetime EP1312863B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0114973 2001-11-20
FR0114973A FR2832492B1 (fr) 2001-11-20 2001-11-20 Perfectionnements apportes aux injecteurs de turbomachine

Publications (2)

Publication Number Publication Date
EP1312863A1 true EP1312863A1 (de) 2003-05-21
EP1312863B1 EP1312863B1 (de) 2007-06-13

Family

ID=8869565

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02292867A Expired - Lifetime EP1312863B1 (de) 2001-11-20 2002-11-19 Verbesserungen an Turbomaschineninjektoren

Country Status (6)

Country Link
US (1) US6758043B2 (de)
EP (1) EP1312863B1 (de)
DE (1) DE60220625T2 (de)
ES (1) ES2287230T3 (de)
FR (1) FR2832492B1 (de)
RU (1) RU2293920C2 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2921113A1 (fr) * 2007-09-17 2009-03-20 Hispano Suiza Sa Procede de fabrication d'un injecteur de carburant pour turbomachine d'aeronef
CN101230987B (zh) * 2007-01-22 2011-03-30 伊斯帕诺-絮扎公司 两级喷油器
WO2013124568A1 (fr) * 2012-02-24 2013-08-29 Snecma Injecteur de carburant pour une turbomachine
FR2987430A1 (fr) * 2012-02-24 2013-08-30 Snecma Injecteur de carburant pour une turbomachine

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2745051A1 (de) * 2011-08-19 2014-06-25 Woodward, Inc. Stromdüsenventil mit abgestufter kühlung
FR3011619B1 (fr) * 2013-10-08 2018-03-02 Safran Aircraft Engines Injecteur de carburant pour une turbomachine
US9739202B2 (en) 2015-05-12 2017-08-22 Rolls-Royce North American Technologies, Inc. Thermal adjustment member for a fuel nozzle of a gas turbine engine
CN107023401A (zh) * 2017-05-28 2017-08-08 西安成立航空制造有限公司 一种航空发动机燃油喷嘴用预燃级副油路活门及其使用方法
FR3078142B1 (fr) * 2018-02-22 2020-03-20 Safran Aircraft Engines Chambre de combustion comportant deux types d'injecteurs dans lesquels les organes d'etancheite ont un seuil d'ouverture different
FR3094074B1 (fr) * 2019-03-20 2021-03-19 Safran Aircraft Engines Injecteur de carburant pour une turbomachine
US11585452B2 (en) 2019-12-03 2023-02-21 Woodward, Inc. Fuel nozzle with reduced flow tolerance
US11346281B2 (en) * 2020-08-21 2022-05-31 Woodward, Inc. Dual schedule flow divider valve, system, and method for use therein
US11913382B1 (en) * 2022-08-26 2024-02-27 Hamilton Sundstrand Corporation Variable restriction of a fuel circuit of a fuel nozzle
US11970976B2 (en) 2022-08-26 2024-04-30 Hamilton Sundstrand Corporation Variable restriction of fuel nozzle with an auxiliary circuit
US11913381B1 (en) 2022-08-26 2024-02-27 Hamilton Sundstrand Corporation Force modification of passive spool for control of secondary nozzle circuits
US11970977B2 (en) 2022-08-26 2024-04-30 Hamilton Sundstrand Corporation Variable restriction of a secondary circuit of a fuel injector

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3662959A (en) * 1970-08-07 1972-05-16 Parker Hannifin Corp Fuel injection nozzle
US4476675A (en) * 1981-03-06 1984-10-16 S.N.E.C.M.A. Acceleration limiter for turbojet engine
US4491272A (en) * 1983-01-27 1985-01-01 Ex-Cell-O Corporation Pressure atomizing fuel injection assembly
US4570668A (en) * 1984-01-16 1986-02-18 Parker-Hannifin Corporation Flow dividing valve
GB2250086A (en) * 1988-10-13 1992-05-27 United Technologies Corp Preventing blow-out in a gas turbine engine combustion chamber
US5732730A (en) * 1995-09-11 1998-03-31 Delavan Inc Combined check valve and metering valve assembly

Family Cites Families (8)

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CH509195A (de) * 1969-12-12 1971-06-30 Netstal Ag Maschf Giesserei Einrichtung zum Herstellen und Füllen eines Kunststoff-Hohlkörpers
JPH02221649A (ja) * 1989-02-22 1990-09-04 Yamaha Motor Co Ltd 燃料噴射装置
US5353991A (en) * 1989-06-21 1994-10-11 General Motors Corporation Solenoid actuated valve assembly
US4987878A (en) * 1989-06-21 1991-01-29 Johnson Jerome V Fuel injection system
US5730369A (en) * 1994-04-25 1998-03-24 General Motors Corporation Fuel injection
FR2765635B1 (fr) * 1997-07-07 1999-09-03 Sagem Pompe d'injection directe de combustible pour moteur a allumage commande et systeme d'injection comportant une telle pompe
JP4052383B2 (ja) * 2000-10-11 2008-02-27 シーメンス ヴィディーオー オートモティヴ コーポレイション ソリッドステートアクチュエーターの補償器用圧力応答弁
FR2817054A1 (fr) * 2000-11-21 2002-05-24 Snecma Moteurs Dispositif doseur a reglage optimise

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3662959A (en) * 1970-08-07 1972-05-16 Parker Hannifin Corp Fuel injection nozzle
US4476675A (en) * 1981-03-06 1984-10-16 S.N.E.C.M.A. Acceleration limiter for turbojet engine
US4491272A (en) * 1983-01-27 1985-01-01 Ex-Cell-O Corporation Pressure atomizing fuel injection assembly
US4570668A (en) * 1984-01-16 1986-02-18 Parker-Hannifin Corporation Flow dividing valve
GB2250086A (en) * 1988-10-13 1992-05-27 United Technologies Corp Preventing blow-out in a gas turbine engine combustion chamber
US5732730A (en) * 1995-09-11 1998-03-31 Delavan Inc Combined check valve and metering valve assembly

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101230987B (zh) * 2007-01-22 2011-03-30 伊斯帕诺-絮扎公司 两级喷油器
FR2921113A1 (fr) * 2007-09-17 2009-03-20 Hispano Suiza Sa Procede de fabrication d'un injecteur de carburant pour turbomachine d'aeronef
WO2013124568A1 (fr) * 2012-02-24 2013-08-29 Snecma Injecteur de carburant pour une turbomachine
FR2987430A1 (fr) * 2012-02-24 2013-08-30 Snecma Injecteur de carburant pour une turbomachine
FR2987429A1 (fr) * 2012-02-24 2013-08-30 Snecma Injecteur de carburant pour une turbomachine
CN104114834A (zh) * 2012-02-24 2014-10-22 斯奈克玛 用于涡轮机组的燃料喷射器
US9494079B2 (en) 2012-02-24 2016-11-15 Snecma Turbine engine fuel injector with permanent leakage flow
CN104114834B (zh) * 2012-02-24 2016-11-16 斯奈克玛 用于涡轮机组的燃料喷射器

Also Published As

Publication number Publication date
ES2287230T3 (es) 2007-12-16
US6758043B2 (en) 2004-07-06
RU2293920C2 (ru) 2007-02-20
FR2832492A1 (fr) 2003-05-23
DE60220625T2 (de) 2008-02-21
FR2832492B1 (fr) 2004-02-06
US20030093998A1 (en) 2003-05-22
DE60220625D1 (de) 2007-07-26
EP1312863B1 (de) 2007-06-13

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