BR112012006146B8 - câmara de combustão de turbomáquina aeronáutica - Google Patents

câmara de combustão de turbomáquina aeronáutica

Info

Publication number
BR112012006146B8
BR112012006146B8 BR112012006146A BR112012006146A BR112012006146B8 BR 112012006146 B8 BR112012006146 B8 BR 112012006146B8 BR 112012006146 A BR112012006146 A BR 112012006146A BR 112012006146 A BR112012006146 A BR 112012006146A BR 112012006146 B8 BR112012006146 B8 BR 112012006146B8
Authority
BR
Brazil
Prior art keywords
holes
combustion chamber
primary holes
primary
zones
Prior art date
Application number
BR112012006146A
Other languages
English (en)
Other versions
BR112012006146B1 (pt
BR112012006146A2 (pt
Inventor
Commaret Patrice
Noel Thomas
Original Assignee
Snecma
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 filed Critical Snecma
Publication of BR112012006146A2 publication Critical patent/BR112012006146A2/pt
Publication of BR112012006146B1 publication Critical patent/BR112012006146B1/pt
Publication of BR112012006146B8 publication Critical patent/BR112012006146B8/pt

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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • 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
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2227/00—Ignition or checking
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Spark Plugs (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

câmara de combustão de turbomáquina aeronáutica a invenção refere-se a uma câmara de combustão (10) turbomáquina aeronáutica, anular de eixo longitudinal (a), delimitada por uma parede lateral externa (12), uma parede lateral interna (14), e um fundo de câmara (13) anular ligando uma extremidade desta parede lateral externa e uma extremidade desta parede lateral interna, a parede lateral externa (12) comportando, distribuídas ao longo de sua circunferência, velas de ignição (36), furos primários (100), e furos de diluição (200) situados a jusante dos furos primários (100), e furos de diluição (200) situados a jusante dos furos primários (100), e furos de diluição (200) situados a jusante dos furos primários (100) na direção do eixo longitudinal (a). os furos primários (100) sitiados em cada uma das zonas adjacentes (60) a uma das velas de ignição (36) apresentam uma configuração diferente dos furos primários (100) situados fora destas zonas de modo que o suprimento de ar nas zonas adjacentes (60) seja diferente do suprimento de ar fora destas zonas.
BR112012006146A 2009-09-21 2010-09-21 câmara de combustão de turbomáquina aeronáutica BR112012006146B8 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0956467A FR2950415B1 (fr) 2009-09-21 2009-09-21 Chambre de combustion de turbomachine aeronautique avec trous de combustion decales ou de debits differents
PCT/FR2010/051970 WO2011033242A2 (fr) 2009-09-21 2010-09-21 Chambre de combustion de turbomachine aeronautique avec trous de combustion de configurations differentes

Publications (3)

Publication Number Publication Date
BR112012006146A2 BR112012006146A2 (pt) 2016-06-28
BR112012006146B1 BR112012006146B1 (pt) 2020-05-05
BR112012006146B8 true BR112012006146B8 (pt) 2021-01-12

Family

ID=42115450

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012006146A BR112012006146B8 (pt) 2009-09-21 2010-09-21 câmara de combustão de turbomáquina aeronáutica

Country Status (9)

Country Link
US (1) US9279588B2 (pt)
EP (1) EP2480834B1 (pt)
JP (2) JP5902621B2 (pt)
CN (1) CN102510978B (pt)
BR (1) BR112012006146B8 (pt)
CA (1) CA2774440C (pt)
FR (1) FR2950415B1 (pt)
RU (1) RU2539949C2 (pt)
WO (1) WO2011033242A2 (pt)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2975465B1 (fr) * 2011-05-19 2018-03-09 Safran Aircraft Engines Paroi pour chambre de combustion de turbomachine comprenant un agencement optimise d'orifices d'entree d'air
FR2979005B1 (fr) * 2011-08-09 2015-04-03 Snecma Systemes d'injection de carburant pour turbomachine d'aeronef a permeabilites differenciees
FR2980553B1 (fr) 2011-09-26 2013-09-20 Snecma Chambre de combustion de turbomachine
EP3015770B1 (en) * 2014-11-03 2020-07-01 Ansaldo Energia Switzerland AG Can combustion chamber
DE102016219424A1 (de) 2016-10-06 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung einer Gasturbine sowie Fluggasturbine
US11268438B2 (en) 2017-09-15 2022-03-08 General Electric Company Combustor liner dilution opening
US10816202B2 (en) 2017-11-28 2020-10-27 General Electric Company Combustor liner for a gas turbine engine and an associated method thereof
US11255543B2 (en) 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
US11181269B2 (en) 2018-11-15 2021-11-23 General Electric Company Involute trapped vortex combustor assembly
DE102018222897A1 (de) 2018-12-21 2020-06-25 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit angepassten Mischluftlöchern
CN114076324B (zh) * 2022-01-19 2022-07-08 中国航发四川燃气涡轮研究院 能够自动调节掺混进气的燃烧室

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1493144A (fr) * 1966-08-19 1967-08-25 Lucas Industries Ltd Perfectionnements aux appareils de combustion pour moteurs de turbines à gaz
US4720970A (en) * 1982-11-05 1988-01-26 The United States Of America As Represented By The Secretary Of The Air Force Sector airflow variable geometry combustor
FR2588919B1 (fr) * 1985-10-18 1987-12-04 Snecma Dispositif d'injection a bol sectorise
JPH0729403Y2 (ja) * 1986-02-12 1995-07-05 トヨタ自動車株式会社 ガスタ−ビンエンジン用燃焼器
US5297385A (en) * 1988-05-31 1994-03-29 United Technologies Corporation Combustor
US5481867A (en) * 1988-05-31 1996-01-09 United Technologies Corporation Combustor
JPH02183719A (ja) * 1989-01-11 1990-07-18 Hitachi Ltd ガスタービン燃焼器
US5289656A (en) * 1992-07-06 1994-03-01 Truth Division Of Spx Corporation Geared casement window hinges
US5289686A (en) * 1992-11-12 1994-03-01 General Motors Corporation Low nox gas turbine combustor liner with elliptical apertures for air swirling
FR2770283B1 (fr) * 1997-10-29 1999-11-19 Snecma Chambre de combustion pour turbomachine
US6145319A (en) * 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
US6266961B1 (en) * 1999-10-14 2001-07-31 General Electric Company Film cooled combustor liner and method of making the same
US7614235B2 (en) * 2005-03-01 2009-11-10 United Technologies Corporation Combustor cooling hole pattern
US7887322B2 (en) * 2006-09-12 2011-02-15 General Electric Company Mixing hole arrangement and method for improving homogeneity of an air and fuel mixture in a combustor
US7926284B2 (en) * 2006-11-30 2011-04-19 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
CN101275741B (zh) * 2007-03-26 2011-02-02 靳宇男 脉冲矢量高压燃烧器
FR2922630B1 (fr) * 2007-10-22 2015-11-13 Snecma Paroi de chambre de combustion a dilution et refroidissement optimises,chambre de combustion et turbomachine en etant munies
FR2922629B1 (fr) * 2007-10-22 2009-12-25 Snecma Chambre de combustion a dilution optimisee et turbomachine en etant munie
RU2352864C1 (ru) * 2007-12-11 2009-04-20 Общество с ограниченной ответственностью "Научно-технический центр "Альтернатива" Способ и устройство для сжигания топлива
FR2941287B1 (fr) * 2009-01-19 2011-03-25 Snecma Paroi de chambre de combustion de turbomachine a une seule rangee annulaire d'orifices d'entree d'air primaire et de dilution
US8584466B2 (en) * 2010-03-09 2013-11-19 Honeywell International Inc. Circumferentially varied quench jet arrangement for gas turbine combustors

Also Published As

Publication number Publication date
RU2012116126A (ru) 2013-10-27
CN102510978B (zh) 2015-08-26
CA2774440A1 (fr) 2011-03-24
FR2950415B1 (fr) 2011-10-14
WO2011033242A3 (fr) 2011-05-26
RU2539949C2 (ru) 2015-01-27
FR2950415A1 (fr) 2011-03-25
JP5902621B2 (ja) 2016-04-13
WO2011033242A2 (fr) 2011-03-24
JP2016106210A (ja) 2016-06-16
US20120186222A1 (en) 2012-07-26
CA2774440C (fr) 2017-08-22
BR112012006146B1 (pt) 2020-05-05
CN102510978A (zh) 2012-06-20
JP2013505419A (ja) 2013-02-14
BR112012006146A2 (pt) 2016-06-28
EP2480834B1 (fr) 2015-07-22
US9279588B2 (en) 2016-03-08
EP2480834A2 (fr) 2012-08-01

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Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 21/09/2010, OBSERVADAS AS CONDICOES LEGAIS.

B16C Correction of notification of the grant

Free format text: REF. RPI 2574 DE 05/05/2020 QUANTO AOS DESENHOS.