FR2599821B1 - Chambre de combustion pour turbomachines a orifices de melange assurant le positionnement de la paroi chaude sur la paroi froide - Google Patents

Chambre de combustion pour turbomachines a orifices de melange assurant le positionnement de la paroi chaude sur la paroi froide

Info

Publication number
FR2599821B1
FR2599821B1 FR8608015A FR8608015A FR2599821B1 FR 2599821 B1 FR2599821 B1 FR 2599821B1 FR 8608015 A FR8608015 A FR 8608015A FR 8608015 A FR8608015 A FR 8608015A FR 2599821 B1 FR2599821 B1 FR 2599821B1
Authority
FR
France
Prior art keywords
wall
turbomachines
positioning
combustion chamber
mixing holes
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.)
Expired
Application number
FR8608015A
Other languages
English (en)
Other versions
FR2599821A1 (fr
Inventor
Gerard Yves Georges Barbier
Gerard Joseph Pa Bayle-Laboure
Michel Andre Albert Desaulty
Francois Duchene
Pascal Maurice Trouillot
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 FR8608015A priority Critical patent/FR2599821B1/fr
Priority to DE8787401235T priority patent/DE3760036D1/de
Priority to US07/056,884 priority patent/US4805397A/en
Priority to EP87401235A priority patent/EP0248731B1/fr
Publication of FR2599821A1 publication Critical patent/FR2599821A1/fr
Application granted granted Critical
Publication of FR2599821B1 publication Critical patent/FR2599821B1/fr
Expired 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
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/202—Heat transfer, e.g. cooling by film cooling

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)
  • Spray-Type Burners (AREA)
FR8608015A 1986-06-04 1986-06-04 Chambre de combustion pour turbomachines a orifices de melange assurant le positionnement de la paroi chaude sur la paroi froide Expired FR2599821B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FR8608015A FR2599821B1 (fr) 1986-06-04 1986-06-04 Chambre de combustion pour turbomachines a orifices de melange assurant le positionnement de la paroi chaude sur la paroi froide
DE8787401235T DE3760036D1 (en) 1986-06-04 1987-06-03 Gas turbine combustion chamber having mixing orifices which assure the positioning of a hot wall on a cool wall
US07/056,884 US4805397A (en) 1986-06-04 1987-06-03 Combustion chamber structure for a turbojet engine
EP87401235A EP0248731B1 (fr) 1986-06-04 1987-06-03 Chambre de combustion pour turbomachines à orifices de mélange assurant le positionnement de la paroi chaude sur la paroi froide

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR8608015A FR2599821B1 (fr) 1986-06-04 1986-06-04 Chambre de combustion pour turbomachines a orifices de melange assurant le positionnement de la paroi chaude sur la paroi froide

Publications (2)

Publication Number Publication Date
FR2599821A1 FR2599821A1 (fr) 1987-12-11
FR2599821B1 true FR2599821B1 (fr) 1988-09-02

Family

ID=9335972

Family Applications (1)

Application Number Title Priority Date Filing Date
FR8608015A Expired FR2599821B1 (fr) 1986-06-04 1986-06-04 Chambre de combustion pour turbomachines a orifices de melange assurant le positionnement de la paroi chaude sur la paroi froide

Country Status (4)

Country Link
US (1) US4805397A (fr)
EP (1) EP0248731B1 (fr)
DE (1) DE3760036D1 (fr)
FR (1) FR2599821B1 (fr)

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FR2624953B1 (fr) * 1987-12-16 1990-04-20 Snecma Chambre de combustion, pour turbomachines, possedant un convergent a doubles parois
US4887432A (en) * 1988-10-07 1989-12-19 Westinghouse Electric Corp. Gas turbine combustion chamber with air scoops
US5144793A (en) * 1990-12-24 1992-09-08 United Technologies Corporation Integrated connector/airtube for a turbomachine's combustion chamber walls
FR2674317B1 (fr) * 1991-03-20 1993-05-28 Snecma Chambre de combustion de turbomachine comportant un reglage du debit de comburant.
FR2710968B1 (fr) * 1993-10-06 1995-11-03 Snecma Chambre de combustion à double paroi.
US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
US5431517A (en) * 1994-01-12 1995-07-11 General Electric Company Apparatus and method for securing a bracket to a fixed member
FR2723177B1 (fr) * 1994-07-27 1996-09-06 Snecma Chambre de combustion comportant une double paroi
DE19547703C2 (de) * 1995-12-20 1999-02-18 Mtu Muenchen Gmbh Brennkammer, insbesondere Ringbrennkammer, für Gasturbinentriebwerke
JPH09195799A (ja) * 1996-01-17 1997-07-29 Mitsubishi Heavy Ind Ltd 燃焼器のスプリングシール装置
US6499993B2 (en) * 2000-05-25 2002-12-31 General Electric Company External dilution air tuning for dry low NOX combustors and methods therefor
US6334310B1 (en) * 2000-06-02 2002-01-01 General Electric Company Fracture resistant support structure for a hula seal in a turbine combustor and related method
CN1246638C (zh) * 2001-04-27 2006-03-22 西门子公司 燃烧室、尤其是燃气轮机的燃烧室
EP1312865A1 (fr) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Chambre de combustion annulaire de turbine à gaz
US8387396B2 (en) 2007-01-09 2013-03-05 General Electric Company Airfoil, sleeve, and method for assembling a combustor assembly
US8281600B2 (en) * 2007-01-09 2012-10-09 General Electric Company Thimble, sleeve, and method for cooling a combustor assembly
US8616004B2 (en) * 2007-11-29 2013-12-31 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
US8171740B2 (en) * 2009-02-27 2012-05-08 Honeywell International Inc. Annular rich-quench-lean gas turbine combustors with plunged holes
US8141365B2 (en) * 2009-02-27 2012-03-27 Honeywell International Inc. Plunged hole arrangement for annular rich-quench-lean gas turbine combustors
US9010123B2 (en) * 2010-07-26 2015-04-21 Honeywell International Inc. Combustors with quench inserts
US8813501B2 (en) * 2011-01-03 2014-08-26 General Electric Company Combustor assemblies for use in turbine engines and methods of assembling same
US9249679B2 (en) * 2011-03-15 2016-02-02 General Electric Company Impingement sleeve and methods for designing and forming impingement sleeve
JP5821550B2 (ja) 2011-11-10 2015-11-24 株式会社Ihi 燃焼器ライナ
US20130298564A1 (en) * 2012-05-14 2013-11-14 General Electric Company Cooling system and method for turbine system
US8695352B2 (en) * 2012-07-12 2014-04-15 Solar Turbines Inc. Baffle assembly for bleed air system of gas turbine engine
DE102012022259A1 (de) * 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine sowie Verfahren zu deren Herstellung
US20140190171A1 (en) * 2013-01-10 2014-07-10 Honeywell International Inc. Combustors with hybrid walled liners
EP2946145B1 (fr) 2013-01-16 2020-07-15 United Technologies Corporation Ensemble de zone de trempe refroidi de chambre de combustion
EP3039346B1 (fr) * 2013-08-30 2022-09-14 Raytheon Technologies Corporation Passages de dilution profilés pour chambre à combustion de turbine à gaz
US10655855B2 (en) 2013-08-30 2020-05-19 Raytheon Technologies Corporation Gas turbine engine wall assembly with support shell contour regions
EP3044444B1 (fr) * 2013-09-13 2019-11-06 United Technologies Corporation Chambre de combustion pour une turbine à gaz avec un panneau de chemisage hermétiquement scellé
EP3090209B1 (fr) 2014-01-03 2019-09-04 United Technologies Corporation Passe-fil refroidi pour un ensemble paroi de chambre de combustion de turbine à gaz
US10533745B2 (en) 2014-02-03 2020-01-14 United Technologies Corporation Film cooling a combustor wall of a turbine engine
US10112557B2 (en) * 2014-04-03 2018-10-30 United Technologies Corporation Thermally compliant grommet assembly
GB201514390D0 (en) 2015-08-13 2015-09-30 Rolls Royce Plc A combustion chamber and a combustion chamber segment
EP3315864B1 (fr) * 2016-10-26 2021-07-28 Raytheon Technologies Corporation Panneau de revêtement de combustion coulé à illet de passage de dilution arrondi pour chambre de combustion de moteur de turbine à gaz
US10697372B2 (en) * 2017-04-05 2020-06-30 General Electric Company Turbine engine conduit interface
GB201720254D0 (en) * 2017-12-05 2018-01-17 Rolls Royce Plc A combustion chamber arrangement
US10816203B2 (en) * 2017-12-11 2020-10-27 General Electric Company Thimble assemblies for introducing a cross-flow into a secondary combustion zone
US11022308B2 (en) * 2018-05-31 2021-06-01 Honeywell International Inc. Double wall combustors with strain isolated inserts
US10808930B2 (en) * 2018-06-28 2020-10-20 Raytheon Technologies Corporation Combustor shell attachment

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Publication number Priority date Publication date Assignee Title
GB845971A (en) * 1958-07-21 1960-08-24 Gen Electric Improvements relating to combustion chambers for gas turbine engines
GB1059199A (en) * 1965-10-20 1967-02-15 Rolls Royce Flame tube
US3496722A (en) * 1968-08-02 1970-02-24 Garrett Corp Combustion chamber flame tube construction
US3899876A (en) * 1968-11-15 1975-08-19 Secr Defence Brit Flame tube for a gas turbine combustion equipment
US3545202A (en) * 1969-04-02 1970-12-08 United Aircraft Corp Wall structure and combustion holes for a gas turbine engine
US4614082A (en) * 1972-12-19 1986-09-30 General Electric Company Combustion chamber construction
US4555901A (en) * 1972-12-19 1985-12-03 General Electric Company Combustion chamber construction
US4480436A (en) * 1972-12-19 1984-11-06 General Electric Company Combustion chamber construction
US4184326A (en) * 1975-12-05 1980-01-22 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
GB2017827B (en) * 1978-04-04 1983-02-02 Gen Electric Combustor liner cooling
US4302941A (en) * 1980-04-02 1981-12-01 United Technologies Corporation Combuster liner construction for gas turbine engine
US4512159A (en) * 1984-04-02 1985-04-23 United Technologies Corporation Clip attachment
FR2567250A1 (fr) * 1984-07-06 1986-01-10 Gen Electric Chambre de combustion pour moteur a turbine a gaz
US4748806A (en) * 1985-07-03 1988-06-07 United Technologies Corporation Attachment means
DE3535443C1 (de) * 1985-10-04 1986-11-20 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Brennkammer fuer ein Gasturbinentriebwerk,insbesondere Ringbrennkammer,mit mindestes einer Luftzufuhrbuchse

Also Published As

Publication number Publication date
FR2599821A1 (fr) 1987-12-11
US4805397A (en) 1989-02-21
DE3760036D1 (en) 1989-02-16
EP0248731A1 (fr) 1987-12-09
EP0248731B1 (fr) 1989-01-11

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CL Concession to grant licences
ST Notification of lapse