EP1278012A3 - Système d'injection aéromécanique à vrille primaire anti-retour - Google Patents

Système d'injection aéromécanique à vrille primaire anti-retour Download PDF

Info

Publication number
EP1278012A3
EP1278012A3 EP02291767A EP02291767A EP1278012A3 EP 1278012 A3 EP1278012 A3 EP 1278012A3 EP 02291767 A EP02291767 A EP 02291767A EP 02291767 A EP02291767 A EP 02291767A EP 1278012 A3 EP1278012 A3 EP 1278012A3
Authority
EP
European Patent Office
Prior art keywords
injection nozzle
fuel
swirler
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
German (de)
English (en)
Other versions
EP1278012B1 (fr
EP1278012A2 (fr
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/fr
Publication of EP1278012A3 publication Critical patent/EP1278012A3/fr
Application granted granted Critical
Publication of EP1278012B1 publication Critical patent/EP1278012B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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

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)

Abstract

Système d'injection d'une chambre de combustion de turbomachine comportant une buse d'injection de carburant assurant la vaporisation du carburant dans la chambre de combustion et un ensemble mélangeur/déflecteur coaxial à cette buse d'injection et qui réalise le mélange comburant/carburant et le diffuse dans la chambre de combustion, cet ensemble mélangeur/déflecteur comportant une vrille primaire (40) et une vrille secondaire (42) disposés axialement à une distance déterminée l'un de l'autre et séparés par un dispositif à venturi (44) disposé coaxialement à la buse d'injection, la vrille primaire étant fixée solidairement à la buse d'injection et séparée de celle-ci d'une distance radiale constante, déterminée de telle sorte que le carburant vaporisé par la buse d'injection ne peut en aucune façon impacter sur la vrille primaire. De préférence, le dispositif à venturi comporte une surface interne (44A) présentant sur une partie amont une discontinuité de pente P.
EP02291767A 2001-07-16 2002-07-12 Système d'injection aéromécanique à vrille primaire anti-retour Expired - Lifetime EP1278012B1 (fr)

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 EP1278012A2 (fr) 2003-01-22
EP1278012A3 true EP1278012A3 (fr) 2003-11-19
EP1278012B1 EP1278012B1 (fr) 2006-10-25

Family

ID=8865551

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02291767A Expired - Lifetime EP1278012B1 (fr) 2001-07-16 2002-07-12 Système d'injection aéromécanique à vrille primaire anti-retour

Country Status (10)

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

Families Citing this family (31)

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US6691515B2 (en) * 2002-03-12 2004-02-17 Rolls-Royce Corporation Dry low combustion system with means for eliminating combustion noise
EP1499800B1 (fr) 2002-04-26 2011-06-29 Rolls-Royce Corporation Module de premelange de combustible pour chambre de combustion de turbine a gaz
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
FR2903170B1 (fr) * 2006-06-29 2011-12-23 Snecma Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2903173B1 (fr) * 2006-06-29 2008-08-29 Snecma Sa Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
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
CN115711176B (zh) 2021-08-23 2025-09-05 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
EP4202304B1 (fr) 2021-12-21 2025-02-26 General Electric Company Moteur à turbine avec buse de carburant et tourbillonneur
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

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2246734A1 (fr) * 1973-10-01 1975-05-02 Gen Electric
EP0469899A1 (fr) * 1990-08-02 1992-02-05 General Electric Company Assemblage d'un dôme d'une chambre de combustion
US5966937A (en) * 1997-10-09 1999-10-19 United Technologies Corporation Radial inlet swirler with twisted vanes for fuel injector

Family Cites Families (12)

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Publication number Priority date Publication date Assignee Title
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
RU2098719C1 (ru) * 1995-06-13 1997-12-10 Акционерное общество "Авиадвигатель" Камера сгорания газовой турбины энергетической установки
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)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2246734A1 (fr) * 1973-10-01 1975-05-02 Gen Electric
EP0469899A1 (fr) * 1990-08-02 1992-02-05 General Electric Company Assemblage d'un dôme d'une chambre de combustion
US5966937A (en) * 1997-10-09 1999-10-19 United Technologies Corporation Radial inlet swirler with twisted vanes for fuel injector

Also Published As

Publication number Publication date
RU2295645C2 (ru) 2007-03-20
EP1278012B1 (fr) 2006-10-25
RU2002118252A (ru) 2004-02-10
FR2827367B1 (fr) 2003-10-17
CA2393082A1 (fr) 2003-01-16
UA76709C2 (uk) 2006-09-15
JP4066241B2 (ja) 2008-03-26
ES2272650T3 (es) 2007-05-01
EP1278012A2 (fr) 2003-01-22
US20030010034A1 (en) 2003-01-16
DE60215589T2 (de) 2007-08-30
CN1407280A (zh) 2003-04-02
DE60215589D1 (de) 2006-12-07
CA2393082C (fr) 2010-10-19
FR2827367A1 (fr) 2003-01-17
US6959551B2 (en) 2005-11-01
JP2003042452A (ja) 2003-02-13
CN1230650C (zh) 2005-12-07

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