FR2998038B1 - Chambre de combustion pour une turbomachine - Google Patents

Chambre de combustion pour une turbomachine

Info

Publication number
FR2998038B1
FR2998038B1 FR1260644A FR1260644A FR2998038B1 FR 2998038 B1 FR2998038 B1 FR 2998038B1 FR 1260644 A FR1260644 A FR 1260644A FR 1260644 A FR1260644 A FR 1260644A FR 2998038 B1 FR2998038 B1 FR 2998038B1
Authority
FR
France
Prior art keywords
turbomachine
combustion chamber
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
FR1260644A
Other languages
English (en)
Other versions
FR2998038A1 (fr
Inventor
Jacques Marcel Arthur Bunel
Gilles Ulryck
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 FR1260644A priority Critical patent/FR2998038B1/fr
Priority to US14/070,698 priority patent/US9599344B2/en
Priority to GB1319801.5A priority patent/GB2514203B/en
Publication of FR2998038A1 publication Critical patent/FR2998038A1/fr
Application granted granted Critical
Publication of FR2998038B1 publication Critical patent/FR2998038B1/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • 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
FR1260644A 2012-11-09 2012-11-09 Chambre de combustion pour une turbomachine Active FR2998038B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR1260644A FR2998038B1 (fr) 2012-11-09 2012-11-09 Chambre de combustion pour une turbomachine
US14/070,698 US9599344B2 (en) 2012-11-09 2013-11-04 Combustion chamber for a turbine engine
GB1319801.5A GB2514203B (en) 2012-11-09 2013-11-11 A combustion chamber for a turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1260644A FR2998038B1 (fr) 2012-11-09 2012-11-09 Chambre de combustion pour une turbomachine

Publications (2)

Publication Number Publication Date
FR2998038A1 FR2998038A1 (fr) 2014-05-16
FR2998038B1 true FR2998038B1 (fr) 2017-12-08

Family

ID=47989088

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1260644A Active FR2998038B1 (fr) 2012-11-09 2012-11-09 Chambre de combustion pour une turbomachine

Country Status (3)

Country Link
US (1) US9599344B2 (fr)
FR (1) FR2998038B1 (fr)
GB (1) GB2514203B (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013007443A1 (de) * 2013-04-30 2014-10-30 Rolls-Royce Deutschland Ltd & Co Kg Brennerdichtung für Gasturbinen-Brennkammerkopf und Hitzeschild
US10859269B2 (en) 2017-03-31 2020-12-08 Delavan Inc. Fuel injectors for multipoint arrays
FR3078384B1 (fr) * 2018-02-28 2021-05-28 Safran Aircraft Engines Chambre de combustion a fond de chambre double
FR3081539B1 (fr) 2018-05-23 2021-06-04 Safran Aircraft Engines Fond de chambre de combustion de turbomachine
FR3084446B1 (fr) 2018-07-25 2024-02-02 Safran Aircraft Engines Chambre de combustion monobloc
US11149684B2 (en) * 2018-09-28 2021-10-19 Raytheon Technologies Corporation Method for fabricating dilution holes in ceramic matrix composite combustor panels
US11859819B2 (en) 2021-10-15 2024-01-02 General Electric Company Ceramic composite combustor dome and liners

Family Cites Families (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5117624A (en) * 1990-09-17 1992-06-02 General Electric Company Fuel injector nozzle support
GB2287310B (en) * 1994-03-01 1997-12-03 Rolls Royce Plc Gas turbine engine combustor heatshield
DE4444961A1 (de) * 1994-12-16 1996-06-20 Mtu Muenchen Gmbh Einrichtung zur Kühlung insbesondere der Rückwand des Flammrohrs einer Brennkammer für Gasturbinentriebwerke
FR2751731B1 (fr) * 1996-07-25 1998-09-04 Snecma Ensemble bol-deflecteur pour chambre de combustion de turbomachine
US6497105B1 (en) * 2001-06-04 2002-12-24 Pratt & Whitney Canada Corp. Low cost combustor burner collar
US6546733B2 (en) * 2001-06-28 2003-04-15 General Electric Company Methods and systems for cooling gas turbine engine combustors
US6792757B2 (en) * 2002-11-05 2004-09-21 Honeywell International Inc. Gas turbine combustor heat shield impingement cooling baffle
US6923002B2 (en) * 2003-08-28 2005-08-02 General Electric Company Combustion liner cap assembly for combustion dynamics reduction
US7013649B2 (en) * 2004-05-25 2006-03-21 General Electric Company Gas turbine engine combustor mixer
US7690207B2 (en) * 2004-08-24 2010-04-06 Pratt & Whitney Canada Corp. Gas turbine floating collar arrangement
FR2885201B1 (fr) * 2005-04-28 2010-09-17 Snecma Moteurs Chambre de combustion aisement demontable a performance aerodynamique amelioree
FR2887015B1 (fr) 2005-06-14 2010-09-24 Snecma Moteurs Assemblage d'une chambre de combustion annulaire de turbomachine
FR2889732B1 (fr) * 2005-08-12 2011-09-23 Snecma Chambre de combustion a tenue thermique amelioree
FR2905166B1 (fr) 2006-08-28 2008-11-14 Snecma Sa Chambre de combustion annulaire d'une turbomachine.
DE112007002152T5 (de) * 2006-09-14 2009-07-23 Solar Turbines Inc., San Diego Prallplattenkuppelanordnung für einen Turbinenmotor
FR2910115B1 (fr) * 2006-12-19 2012-11-16 Snecma Deflecteur pour fond de chambre de combustion, chambre de combustion en etant equipee et turboreacteur les comportant
US8438853B2 (en) * 2008-01-29 2013-05-14 Alstom Technology Ltd. Combustor end cap assembly
FR2931929B1 (fr) * 2008-05-29 2010-06-04 Snecma Chambre de combustion annulaire de moteur a turbine a gaz
FR2935465B1 (fr) 2008-08-29 2013-09-20 Snecma Fixation d'un deflecteur en cmc sur un fond de chambre par pincage a l'aide d'un support metallique.
FR2943404B1 (fr) 2009-03-20 2015-08-07 Snecma Fond de chambre de combustion definissant en partie une fente pour le passage d'un film d'air de refroissement
EP2256413A1 (fr) * 2009-05-27 2010-12-01 Siemens Aktiengesellschaft Brûleur, procédé de fonctionnement et procédé de montage
FR2972027B1 (fr) 2011-02-25 2013-03-29 Snecma Chambre annulaire de combustion de turbomachine comprenant des orifices de dilution ameliores

Also Published As

Publication number Publication date
FR2998038A1 (fr) 2014-05-16
GB2514203A (en) 2014-11-19
US20140318138A1 (en) 2014-10-30
GB201319801D0 (en) 2013-12-25
US9599344B2 (en) 2017-03-21
GB2514203B (en) 2018-04-04

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