JP2013505419A5 - - Google Patents

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Publication number
JP2013505419A5
JP2013505419A5 JP2012529332A JP2012529332A JP2013505419A5 JP 2013505419 A5 JP2013505419 A5 JP 2013505419A5 JP 2012529332 A JP2012529332 A JP 2012529332A JP 2012529332 A JP2012529332 A JP 2012529332A JP 2013505419 A5 JP2013505419 A5 JP 2013505419A5
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JP
Japan
Prior art keywords
adjacent region
flow rate
air passing
hole
outside
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
JP2012529332A
Other languages
English (en)
Japanese (ja)
Other versions
JP2013505419A (ja
JP5902621B2 (ja
Filing date
Publication date
Priority claimed from FR0956467A external-priority patent/FR2950415B1/fr
Application filed filed Critical
Publication of JP2013505419A publication Critical patent/JP2013505419A/ja
Publication of JP2013505419A5 publication Critical patent/JP2013505419A5/ja
Application granted granted Critical
Publication of JP5902621B2 publication Critical patent/JP5902621B2/ja
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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JP2012529332A 2009-09-21 2010-09-21 異なる形態の燃焼孔を有する航空機タービンエンジンの燃焼室 Active JP5902621B2 (ja)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0956467 2009-09-21
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

Related Child Applications (1)

Application Number Title Priority Date Filing Date
JP2016001532A Division JP2016106210A (ja) 2009-09-21 2016-01-07 異なる形態の燃焼孔を有する航空機タービンエンジンの燃焼室

Publications (3)

Publication Number Publication Date
JP2013505419A JP2013505419A (ja) 2013-02-14
JP2013505419A5 true JP2013505419A5 (enExample) 2014-10-16
JP5902621B2 JP5902621B2 (ja) 2016-04-13

Family

ID=42115450

Family Applications (2)

Application Number Title Priority Date Filing Date
JP2012529332A Active JP5902621B2 (ja) 2009-09-21 2010-09-21 異なる形態の燃焼孔を有する航空機タービンエンジンの燃焼室
JP2016001532A Pending JP2016106210A (ja) 2009-09-21 2016-01-07 異なる形態の燃焼孔を有する航空機タービンエンジンの燃焼室

Family Applications After (1)

Application Number Title Priority Date Filing Date
JP2016001532A Pending JP2016106210A (ja) 2009-09-21 2016-01-07 異なる形態の燃焼孔を有する航空機タービンエンジンの燃焼室

Country Status (9)

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

Families Citing this family (14)

* 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
EP4202301A1 (en) * 2021-12-21 2023-06-28 General Electric Company Combustor with dilution openings
US11774100B2 (en) * 2022-01-14 2023-10-03 General Electric Company Combustor fuel nozzle assembly
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
US12435877B2 (en) 2023-02-20 2025-10-07 General Electric Company Gas turbine engine combustor with a set of dilution passages

Family Cites Families (20)

* 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
US5481867A (en) * 1988-05-31 1996-01-09 United Technologies Corporation Combustor
US5297385A (en) * 1988-05-31 1994-03-29 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
FR2922629B1 (fr) * 2007-10-22 2009-12-25 Snecma Chambre de combustion a dilution optimisee et turbomachine en etant munie
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
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

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