FR2892180B1 - Amelioration des perfomances d'une chambre de combustion par multiperforation des parois - Google Patents

Amelioration des perfomances d'une chambre de combustion par multiperforation des parois

Info

Publication number
FR2892180B1
FR2892180B1 FR0510584A FR0510584A FR2892180B1 FR 2892180 B1 FR2892180 B1 FR 2892180B1 FR 0510584 A FR0510584 A FR 0510584A FR 0510584 A FR0510584 A FR 0510584A FR 2892180 B1 FR2892180 B1 FR 2892180B1
Authority
FR
France
Prior art keywords
multiperforating
perfomance
walls
improving
combustion chamber
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.)
Active
Application number
FR0510584A
Other languages
English (en)
Other versions
FR2892180A1 (fr
Inventor
Daniel Bernier
Jean Michel Campion
Stephane Touchaud
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 SAS
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 SAS filed Critical SNECMA SAS
Priority to FR0510584A priority Critical patent/FR2892180B1/fr
Priority to EP06120816.1A priority patent/EP1777458B1/fr
Priority to US11/544,554 priority patent/US7748222B2/en
Priority to RU2006136873/06A priority patent/RU2413134C2/ru
Publication of FR2892180A1 publication Critical patent/FR2892180A1/fr
Application granted granted Critical
Publication of FR2892180B1 publication Critical patent/FR2892180B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23R3/002—Wall structures
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
FR0510584A 2005-10-18 2005-10-18 Amelioration des perfomances d'une chambre de combustion par multiperforation des parois Active FR2892180B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FR0510584A FR2892180B1 (fr) 2005-10-18 2005-10-18 Amelioration des perfomances d'une chambre de combustion par multiperforation des parois
EP06120816.1A EP1777458B1 (fr) 2005-10-18 2006-09-18 Amélioration des performances d'une chambre de combustion par multiperforation des parois
US11/544,554 US7748222B2 (en) 2005-10-18 2006-10-10 Performance of a combustion chamber by multiple wall perforations
RU2006136873/06A RU2413134C2 (ru) 2005-10-18 2006-10-17 Усовершенствование характеристик камеры сгорания при помощи мультиперфорирования ее стенок

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0510584A FR2892180B1 (fr) 2005-10-18 2005-10-18 Amelioration des perfomances d'une chambre de combustion par multiperforation des parois

Publications (2)

Publication Number Publication Date
FR2892180A1 FR2892180A1 (fr) 2007-04-20
FR2892180B1 true FR2892180B1 (fr) 2008-02-01

Family

ID=36263914

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0510584A Active FR2892180B1 (fr) 2005-10-18 2005-10-18 Amelioration des perfomances d'une chambre de combustion par multiperforation des parois

Country Status (4)

Country Link
US (1) US7748222B2 (fr)
EP (1) EP1777458B1 (fr)
FR (1) FR2892180B1 (fr)
RU (1) RU2413134C2 (fr)

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US7614235B2 (en) * 2005-03-01 2009-11-10 United Technologies Corporation Combustor cooling hole pattern
US8171634B2 (en) * 2007-07-09 2012-05-08 Pratt & Whitney Canada Corp. Method of producing effusion holes
US7905094B2 (en) * 2007-09-28 2011-03-15 Honeywell International Inc. Combustor systems with liners having improved cooling hole patterns
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
US8616004B2 (en) * 2007-11-29 2013-12-31 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
US8127554B2 (en) * 2007-11-29 2012-03-06 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
US8056342B2 (en) * 2008-06-12 2011-11-15 United Technologies Corporation Hole pattern for gas turbine combustor
US8091367B2 (en) * 2008-09-26 2012-01-10 Pratt & Whitney Canada Corp. Combustor with improved cooling holes arrangement
US8438856B2 (en) * 2009-03-02 2013-05-14 General Electric Company Effusion cooled one-piece can combustor
FR2972027B1 (fr) * 2011-02-25 2013-03-29 Snecma Chambre annulaire de combustion de turbomachine comprenant des orifices de dilution ameliores
FR2974162B1 (fr) * 2011-04-14 2018-04-13 Safran Aircraft Engines Virole de tube a flamme dans une chambre de combustion de turbomachine
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
US9062884B2 (en) 2011-05-26 2015-06-23 Honeywell International Inc. Combustors with quench inserts
FR2981733B1 (fr) * 2011-10-25 2013-12-27 Snecma Module de chambre de combustion de turbomachine d'aeronef et procede de conception de celui-ci
FR2982008B1 (fr) * 2011-10-26 2013-12-13 Snecma Paroi annulaire de chambre de combustion a refroidissement ameliore au niveau des trous primaires et de dilution
FR2991028B1 (fr) * 2012-05-25 2014-07-04 Snecma Virole de chambre de combustion de turbomachine
US10260748B2 (en) * 2012-12-21 2019-04-16 United Technologies Corporation Gas turbine engine combustor with tailored temperature profile
WO2014143209A1 (fr) * 2013-03-15 2014-09-18 Rolls-Royce Corporation Chemisage de chambre de combustion de moteur à turbine à gaz
CA2903368A1 (fr) * 2013-03-15 2014-09-25 Rolls-Royce Corporation Chambre de combustion a doublet de contre-tourbillon
EP3077728B8 (fr) 2013-12-06 2021-03-31 Raytheon Technologies Corporation Chambre de combustion de moteur à turbine à gaz ayant des passages d'effusion avec orientation de co-tourbillonnement, et procédé
US20160178199A1 (en) * 2014-12-17 2016-06-23 United Technologies Corporation Combustor dilution hole active heat transfer control apparatus and system
FR3035707B1 (fr) * 2015-04-29 2019-11-01 Safran Aircraft Engines Chambre de combustion coudee d'une turbomachine
US10670267B2 (en) * 2015-08-14 2020-06-02 Raytheon Technologies Corporation Combustor hole arrangement for gas turbine engine
GB201518345D0 (en) * 2015-10-16 2015-12-02 Rolls Royce Combustor for a gas turbine engine
JP6026028B1 (ja) * 2016-03-10 2016-11-16 三菱日立パワーシステムズ株式会社 燃焼器用パネル、燃焼器、燃焼装置、ガスタービン、及び燃焼器用パネルの冷却方法
DE102016219424A1 (de) * 2016-10-06 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung einer Gasturbine sowie Fluggasturbine
US11015529B2 (en) 2016-12-23 2021-05-25 General Electric Company Feature based cooling using in wall contoured cooling passage
US20180266687A1 (en) * 2017-03-16 2018-09-20 General Electric Company Reducing film scrubbing in a combustor
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
DE102019105442A1 (de) * 2019-03-04 2020-09-10 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung eines Triebwerksbauteils mit einer Kühlkanalanordnung und Triebwerksbauteil
EP3848556A1 (fr) * 2020-01-13 2021-07-14 Ansaldo Energia Switzerland AG Moteur à turbine à gaz ayant une pièce de transition avec trous de refroidissement obliques
CN116202106B (zh) * 2023-03-08 2024-05-03 中国科学院工程热物理研究所 一种气膜孔与掺混孔耦合设计的发动机燃烧室火焰筒结构

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FR1493144A (fr) * 1966-08-19 1967-08-25 Lucas Industries Ltd Perfectionnements aux appareils de combustion pour moteurs de turbines à gaz
US3572031A (en) * 1969-07-11 1971-03-23 United Aircraft Corp Variable area cooling passages for gas turbine burners
GB1492049A (en) * 1974-12-07 1977-11-16 Rolls Royce Combustion equipment for gas turbine engines
US4244178A (en) * 1978-03-20 1981-01-13 General Motors Corporation Porous laminated combustor structure
US4180972A (en) * 1978-06-08 1980-01-01 General Motors Corporation Combustor support structure
US4269032A (en) * 1979-06-13 1981-05-26 General Motors Corporation Waffle pattern porous material
US4302940A (en) * 1979-06-13 1981-12-01 General Motors Corporation Patterned porous laminated material
US4296606A (en) * 1979-10-17 1981-10-27 General Motors Corporation Porous laminated material
US5241827A (en) * 1991-05-03 1993-09-07 General Electric Company Multi-hole film cooled combuster linear with differential cooling
US5261223A (en) * 1992-10-07 1993-11-16 General Electric Company Multi-hole film cooled combustor liner with rectangular film restarting holes
FR2733582B1 (fr) * 1995-04-26 1997-06-06 Snecma Chambre de combustion comportant une multiperforation d'inclinaison axiale et tangentielle variable
US6192689B1 (en) * 1998-03-18 2001-02-27 General Electric Company Reduced emissions gas turbine combustor
US6474070B1 (en) * 1998-06-10 2002-11-05 General Electric Company Rich double dome combustor
US6145319A (en) * 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
US6205789B1 (en) * 1998-11-13 2001-03-27 General Electric Company Multi-hole film cooled combuster liner
US6434821B1 (en) * 1999-12-06 2002-08-20 General Electric Company Method of making a combustion chamber liner
US6427446B1 (en) * 2000-09-19 2002-08-06 Power Systems Mfg., Llc Low NOx emission combustion liner with circumferentially angled film cooling holes
US6408629B1 (en) * 2000-10-03 2002-06-25 General Electric Company Combustor liner having preferentially angled cooling holes
US6620457B2 (en) * 2001-07-13 2003-09-16 General Electric Company Method for thermal barrier coating and a liner made using said method
US6513331B1 (en) * 2001-08-21 2003-02-04 General Electric Company Preferential multihole combustor liner
US7093439B2 (en) * 2002-05-16 2006-08-22 United Technologies Corporation Heat shield panels for use in a combustor for a gas turbine engine
US7216485B2 (en) * 2004-09-03 2007-05-15 General Electric Company Adjusting airflow in turbine component by depositing overlay metallic coating
US7895841B2 (en) * 2006-07-14 2011-03-01 General Electric Company Method and apparatus to facilitate reducing NOx emissions in turbine engines

Also Published As

Publication number Publication date
EP1777458B1 (fr) 2015-08-12
US7748222B2 (en) 2010-07-06
US20070084219A1 (en) 2007-04-19
RU2413134C2 (ru) 2011-02-27
RU2006136873A (ru) 2008-04-27
FR2892180A1 (fr) 2007-04-20
EP1777458A1 (fr) 2007-04-25

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