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EP1278012A2 - Aeromechanisches Einspritzsystem mit Primärverwirbelungs- und Rückschlagvorrichtung - Google Patents

Aeromechanisches Einspritzsystem mit Primärverwirbelungs- und Rückschlagvorrichtung Download PDF

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Publication number
EP1278012A2
EP1278012A2 EP02291767A EP02291767A EP1278012A2 EP 1278012 A2 EP1278012 A2 EP 1278012A2 EP 02291767 A EP02291767 A EP 02291767A EP 02291767 A EP02291767 A EP 02291767A EP 1278012 A2 EP1278012 A2 EP 1278012A2
Authority
EP
European Patent Office
Prior art keywords
fuel
injection nozzle
injection
combustion chamber
injection system
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
EP02291767A
Other languages
English (en)
French (fr)
Other versions
EP1278012A3 (de
EP1278012B1 (de
Inventor
Christophe Baudoin
Patrice-André Commaret
Christophe Viguier
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 Aircraft Engines SAS
Original Assignee
SNECMA Moteurs 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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1278012A2 publication Critical patent/EP1278012A2/de
Publication of EP1278012A3 publication Critical patent/EP1278012A3/de
Application granted granted Critical
Publication of EP1278012B1 publication Critical patent/EP1278012B1/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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Definitions

  • the present invention relates to the specific field of turbomachines and is particularly interested in the problem posed by injecting fuel into the combustion chamber of a turbomachine.
  • fuel injection into the chamber of combustion 50 is carried out from several injection systems 52 each comprising, on the one hand, a fuel injection nozzle 54 ensuring the vaporization of the fuel in the combustion chamber and secondly a mixer / deflector assembly 56 which produces the combustion / fuel mixture and diffuses it into this combustion chamber.
  • This mixer / baffle assembly includes a first swirl device or primary swirler (swirler 58) mounted sliding on the fuel injection nozzle 54 (via a sleeve 60), a venturi device 62, a second vortex or secondary spin device 64 and a deflector 66 fixed on the bottom of the combustion chamber 68.
  • This conventional injection system architecture however has the major disadvantage of presenting, under certain particular conditions of use, a risk of self-ignition likely to cause destruction of the combustion chamber. Indeed, the impact of fuel on the internal surface venturi, necessary to obtain a film of fuel whose fragmentation into fine droplets will be ensured by the shears generated by the primary tendrils and secondary, sometimes results in fuel lift in the bladders of the primary spin. Moreover, because the impact zone of the fuel on this internal surface is not precisely localized, a fuel injection to countercurrent in this primary swirl may also possibly occur. However, such a return of fuel in the primary swirler can help to bring this fuel on the outside of the flame tube and thus risk destroying the fire of the combustion chamber of the turbomachine.
  • the present invention overcomes these disadvantages by proposing a system turbomachine injection system comprising on the one hand an injection nozzle of fuel to vaporize the fuel in the combustion chamber and on the other hand a mixer / deflector assembly disposed coaxially with said nozzle of injection and which carries out the combustion / fuel mixture and diffuses it into said combustion chamber, said mixer / deflector assembly having a first vortex device (or primary swirler) and at least one second device with a vortex (or secondary swirl) arranged axially at a determined distance from each other and separated by a venturi device arranged coaxially with said injection nozzle, characterized in that said first vortex device is attached integrally with said injection nozzle and separated therefrom by a radial distance constant, determined so that the fuel vaporized by said nozzle injection device can not in any way impact on said first device whirlwind.
  • a system turbomachine injection system comprising on the one hand an injection nozzle of fuel to vaporize the fuel in the combustion chamber and on the other hand
  • the second vortex device is slidably mounted by relative to said injection nozzle via a fixed crown of said second vortex device and which can move, perpendicular to a axis of revolution of said injection nozzle, in an annular housing of said Venturi device.
  • this venturi device comprises an inner surface having on an upstream portion a slope discontinuity.
  • This upstream part of the internal surface of the venturi device may comprise a concave step or a convex step.
  • the annular combustion chamber is formed of an outer axial wall 24 and an inner axial wall 26, both coaxial axis 10, and a wall transverse 28 forming chamber bottom and provided with a plurality of openings 30 for fixing the injection systems.
  • the different links between upstream ends of the axial walls of the chamber 24, 26, optionally caps 32, 34 extending upstream these ends of walls, and ends folded from the bottom chamber 28 is performed by any means of attachment conventional (not shown), for example screw bolts with conical head, preferably of prison nut type.
  • Each injection system of the injection assembly comprises on the one hand a fuel injection nozzle 36 ensuring the vaporization of the fuel in the combustion chamber and secondly a mixer / deflector assembly 38 coaxial with this injection nozzle and which produces the fuel / fuel mixture and the diffuses into this combustion chamber.
  • This mixer / baffle assembly has at least one first vortex or swirl device (swirler 40) and a second secondary vortex or swirl device 42 spaced axially from each other by a determined distance and separated by a venturi device 44.
  • the secondary swirler is extended by a deflector 46 fixed to the chamber bottom 28 and which extends through the opening 30 in the combustion chamber 22.
  • the primary swirler 40 is fixed integrally to the nozzle injection device 36, for example by means of a sleeve 48, and of which it is therefore separated by a constant radial distance. This distance is determined from such that, irrespective of the operating conditions of the turbomachine (autorotation, idle, full throttle), the fuel vaporized by the injection nozzle can in no way impact the primary swirler.
  • the turbomachine autorotation, idle, full throttle
  • the fuel vaporized by the injection nozzle can in no way impact the primary swirler.
  • venturi device further comprises on its inner surface 44A an upstream portion P with a slope discontinuity so as to prevent, or at the very least, significantly reduce any risk of fuel rising by capillarity in the primary swirl 40 of the injection system 20.
  • This discontinuity of slope carried out upstream of the outer surface E of the fuel injection cone may example be constituted by a concave step.
  • this discontinuity of slope is instead constituted by a step convex.
  • the secondary spin 42 is slidably mounted relative to this injection nozzle, perpendicular to a axis of revolution S of the nozzle, for example by means of a ring 47 fixed on this secondary swirler and able to move in an annular housing 49 of the venturi device 44.
  • sufficient clearance is left between the inner periphery of this annular housing and the outer periphery of the crowned.
  • the injection nozzle is constantly centered with respect to the primary swirler and the venturi device thus avoiding any fuel injection against the current, and the discontinuity of slope of this venturi also makes it possible to avoid any fuel capillarity.
  • the particular structure of the invention ensures a good spraying fuel in all flight conditions and in particular in the most severe conditions for re-ignition in low autorotation Mach, conditions under which the air supply pressure drops are too small to guarantee sufficient fragmentation of the fuel and thus access a vast re-ignition domain.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
EP02291767A 2001-07-16 2002-07-12 Aeromechanisches Einspritzsystem mit Primärverwirbelungs- und Rückschlagvorrichtung Expired - Lifetime EP1278012B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0109456 2001-07-16
FR0109456A FR2827367B1 (fr) 2001-07-16 2001-07-16 Systeme d'injection aeromecanique a vrille primaire anti-retour

Publications (3)

Publication Number Publication Date
EP1278012A2 true EP1278012A2 (de) 2003-01-22
EP1278012A3 EP1278012A3 (de) 2003-11-19
EP1278012B1 EP1278012B1 (de) 2006-10-25

Family

ID=8865551

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02291767A Expired - Lifetime EP1278012B1 (de) 2001-07-16 2002-07-12 Aeromechanisches Einspritzsystem mit Primärverwirbelungs- und Rückschlagvorrichtung

Country Status (10)

Country Link
US (1) US6959551B2 (de)
EP (1) EP1278012B1 (de)
JP (1) JP4066241B2 (de)
CN (1) CN1230650C (de)
CA (1) CA2393082C (de)
DE (1) DE60215589T2 (de)
ES (1) ES2272650T3 (de)
FR (1) FR2827367B1 (de)
RU (1) RU2295645C2 (de)
UA (1) UA76709C2 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1488086A1 (de) * 2002-03-12 2004-12-22 Rolls-Royce Corporation Trockenverbrennungssystem mit niedrigem ausstoss und mitteln zur beseitung von verbrennungslärm
EP1873456A1 (de) * 2006-06-29 2008-01-02 Snecma Vorrichtung zum Einspritzen einer Mischung aus Luft und Treibstoff, Brennkammer und Strömungsmaschine, die mit einer solchen Vorrichtung ausgestattet ist
EP1873457A1 (de) * 2006-06-29 2008-01-02 Snecma Vorrichtung zum Einspritzen einer Mischung aus Luft und Treibstoff, Brennkammer und Strömungsmaschine, die mit einer solchen Vorrichtung ausgestattet ist

Families Citing this family (27)

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JP4414769B2 (ja) 2002-04-26 2010-02-10 ロールス−ロイス・コーポレーション ガスタービンエンジン燃焼器用の燃料予混合モジュール
US20050229600A1 (en) * 2004-04-16 2005-10-20 Kastrup David A Methods and apparatus for fabricating gas turbine engine combustors
US7966832B1 (en) * 2004-12-29 2011-06-28 Solar Turbines Inc Combustor
US7316117B2 (en) * 2005-02-04 2008-01-08 Siemens Power Generation, Inc. Can-annular turbine combustors comprising swirler assembly and base plate arrangements, and combinations
US7628019B2 (en) * 2005-03-21 2009-12-08 United Technologies Corporation Fuel injector bearing plate assembly and swirler assembly
JP2006300448A (ja) * 2005-04-22 2006-11-02 Mitsubishi Heavy Ind Ltd ガスタービンの燃焼器
CN100390397C (zh) * 2005-04-30 2008-05-28 张鸿元 空气压缩航空发动机
US7513098B2 (en) 2005-06-29 2009-04-07 Siemens Energy, Inc. Swirler assembly and combinations of same in gas turbine engine combustors
US7617689B2 (en) * 2006-03-02 2009-11-17 Honeywell International Inc. Combustor dome assembly including retaining ring
FR2901574B1 (fr) * 2006-05-29 2008-07-04 Snecma Sa Dispositif de guidage d'un flux d'air a l'entree d'une chambre de combustion dans une turbomachine
FR2908867B1 (fr) * 2006-11-16 2012-06-15 Snecma Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2920032B1 (fr) * 2007-08-13 2014-08-22 Snecma Diffuseur d'une turbomachine
US9027350B2 (en) * 2009-12-30 2015-05-12 Rolls-Royce Corporation Gas turbine engine having dome panel assembly with bifurcated swirler flow
US10317081B2 (en) * 2011-01-26 2019-06-11 United Technologies Corporation Fuel injector assembly
FR2986856B1 (fr) * 2012-02-15 2018-05-04 Safran Aircraft Engines Dispositif d'injection d'air et de carburant pour une chambre de combustion d'une turbomachine
CN103836647B (zh) * 2014-02-27 2015-07-29 中国科学院工程热物理研究所 一种文丘里管流道壁面结构
FR3029608B1 (fr) 2014-12-03 2017-01-13 Snecma Couronne d'admission d'air pour systeme d'injection de chambre de combustion de turbomachine et procede d'atomisation de carburant dans un systeme d'injection comprenant ladite couronne d'admission d'air
CN104676647A (zh) * 2014-12-15 2015-06-03 西北工业大学 一种强化液膜破碎效果的文氏管装置
CN104566467B (zh) * 2014-12-31 2018-02-23 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种防回火型喷嘴
FR3038699B1 (fr) * 2015-07-08 2022-06-24 Snecma Chambre de combustion coudee d'une turbomachine
US10801726B2 (en) 2017-09-21 2020-10-13 General Electric Company Combustor mixer purge cooling structure
FR3080437B1 (fr) * 2018-04-24 2020-04-17 Safran Aircraft Engines Systeme d'injection pour une chambre annulaire de combustion de turbomachine
US11378275B2 (en) * 2019-12-06 2022-07-05 Raytheon Technologies Corporation High shear swirler with recessed fuel filmer for a gas turbine engine
US11428411B1 (en) * 2021-05-18 2022-08-30 General Electric Company Swirler with rifled venturi for dynamics mitigation
CN115711176A (zh) 2021-08-23 2023-02-24 通用电气公司 具有集成喇叭形旋流器的圆顶
GB2611115B (en) * 2021-09-23 2024-10-09 Gen Electric Floating primary vane swirler
US12072099B2 (en) * 2021-12-21 2024-08-27 General Electric Company Gas turbine fuel nozzle having a lip extending from the vanes of a swirler

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FR2246734A1 (de) * 1973-10-01 1975-05-02 Gen Electric
EP0469899A1 (de) * 1990-08-02 1992-02-05 General Electric Company Aufbau eines Brennkammerdomes
US5966937A (en) * 1997-10-09 1999-10-19 United Technologies Corporation Radial inlet swirler with twisted vanes for fuel injector

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US3703259A (en) * 1971-05-03 1972-11-21 Gen Electric Air blast fuel atomizer
US3946552A (en) * 1973-09-10 1976-03-30 General Electric Company Fuel injection apparatus
GB9023004D0 (en) * 1990-10-23 1990-12-05 Rolls Royce Plc A gas turbine engine combustion chamber and a method of operating a gas turbine engine combustion chamber
DE4110507C2 (de) 1991-03-30 1994-04-07 Mtu Muenchen Gmbh Brenner für Gasturbinentriebwerke mit mindestens einer für die Zufuhr von Verbrennungsluft lastabhängig regulierbaren Dralleinrichtung
GB2272756B (en) * 1992-11-24 1995-05-31 Rolls Royce Plc Fuel injection apparatus
DE4444961A1 (de) 1994-12-16 1996-06-20 Mtu Muenchen Gmbh Einrichtung zur Kühlung insbesondere der Rückwand des Flammrohrs einer Brennkammer für Gasturbinentriebwerke
FR2753779B1 (fr) * 1996-09-26 1998-10-16 Systeme d'injection aerodynamique d'un melange air carburant
US6571559B1 (en) * 1998-04-03 2003-06-03 General Electric Company Anti-carboning fuel-air mixer for a gas turbine engine combustor
US6314739B1 (en) * 2000-01-13 2001-11-13 General Electric Company Brazeless combustor dome assembly
US6735950B1 (en) * 2000-03-31 2004-05-18 General Electric Company Combustor dome plate and method of making the same
US6427435B1 (en) * 2000-05-20 2002-08-06 General Electric Company Retainer segment for swirler assembly

Patent Citations (3)

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Publication number Priority date Publication date Assignee Title
FR2246734A1 (de) * 1973-10-01 1975-05-02 Gen Electric
EP0469899A1 (de) * 1990-08-02 1992-02-05 General Electric Company Aufbau eines Brennkammerdomes
US5966937A (en) * 1997-10-09 1999-10-19 United Technologies Corporation Radial inlet swirler with twisted vanes for fuel injector

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1488086A1 (de) * 2002-03-12 2004-12-22 Rolls-Royce Corporation Trockenverbrennungssystem mit niedrigem ausstoss und mitteln zur beseitung von verbrennungslärm
EP1488086A4 (de) * 2002-03-12 2007-07-04 Rolls Royce Corp Trockenverbrennungssystem mit niedrigem ausstoss und mitteln zur beseitung von verbrennungslärm
EP1873456A1 (de) * 2006-06-29 2008-01-02 Snecma Vorrichtung zum Einspritzen einer Mischung aus Luft und Treibstoff, Brennkammer und Strömungsmaschine, die mit einer solchen Vorrichtung ausgestattet ist
EP1873457A1 (de) * 2006-06-29 2008-01-02 Snecma Vorrichtung zum Einspritzen einer Mischung aus Luft und Treibstoff, Brennkammer und Strömungsmaschine, die mit einer solchen Vorrichtung ausgestattet ist
FR2903170A1 (fr) * 2006-06-29 2008-01-04 Snecma Sa Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2903173A1 (fr) * 2006-06-29 2008-01-04 Snecma Sa Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
US7861529B2 (en) 2006-06-29 2011-01-04 Snecma Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine both equipped with such a device
US7908865B2 (en) 2006-06-29 2011-03-22 Snecma Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device

Also Published As

Publication number Publication date
CN1230650C (zh) 2005-12-07
CA2393082C (fr) 2010-10-19
CA2393082A1 (fr) 2003-01-16
DE60215589D1 (de) 2006-12-07
FR2827367B1 (fr) 2003-10-17
RU2295645C2 (ru) 2007-03-20
JP4066241B2 (ja) 2008-03-26
JP2003042452A (ja) 2003-02-13
FR2827367A1 (fr) 2003-01-17
RU2002118252A (ru) 2004-02-10
US20030010034A1 (en) 2003-01-16
UA76709C2 (uk) 2006-09-15
CN1407280A (zh) 2003-04-02
DE60215589T2 (de) 2007-08-30
ES2272650T3 (es) 2007-05-01
EP1278012A3 (de) 2003-11-19
US6959551B2 (en) 2005-11-01
EP1278012B1 (de) 2006-10-25

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