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FR2930628B1 - Chambre annulaire de combustion pour turbomachine - Google Patents

Chambre annulaire de combustion pour turbomachine

Info

Publication number
FR2930628B1
FR2930628B1 FR0802295A FR0802295A FR2930628B1 FR 2930628 B1 FR2930628 B1 FR 2930628B1 FR 0802295 A FR0802295 A FR 0802295A FR 0802295 A FR0802295 A FR 0802295A FR 2930628 B1 FR2930628 B1 FR 2930628B1
Authority
FR
France
Prior art keywords
turbomachine
combustion chamber
annular combustion
revolution
downstream end
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
FR0802295A
Other languages
English (en)
Other versions
FR2930628A1 (fr
Inventor
Caroline Jacqueline Denise Berdou
Sylvain Duval
Romain Nicolas Lunel
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 FR0802295A priority Critical patent/FR2930628B1/fr
Priority to PCT/FR2009/000473 priority patent/WO2009133322A1/fr
Priority to US12/989,292 priority patent/US20110120144A1/en
Publication of FR2930628A1 publication Critical patent/FR2930628A1/fr
Application granted granted Critical
Publication of FR2930628B1 publication Critical patent/FR2930628B1/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
    • F23R3/50—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
    • F23R3/002—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
    • F23R3/42—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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Chambre annulaire de combustion pour turbomachine, telle qu'un turboréacteur ou turbopropulseur d'avion, comprenant à l'extrémité aval d'une de ses parois de révolution externe ou interne (48, 50), une bride annulaire (58) de fixation sur un carter (62) de la turbomachine, l'extrémité aval de l'autre paroi de révolution de la chambre comprenant des moyens (66) écartés à froid d'un autre carter (40) de la turbomachine et s'appliquant radialement à chaud sur ce carter.
FR0802295A 2008-04-24 2008-04-24 Chambre annulaire de combustion pour turbomachine Active FR2930628B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR0802295A FR2930628B1 (fr) 2008-04-24 2008-04-24 Chambre annulaire de combustion pour turbomachine
PCT/FR2009/000473 WO2009133322A1 (fr) 2008-04-24 2009-04-21 Chambre annulaire de combustion pour turbomachine
US12/989,292 US20110120144A1 (en) 2008-04-24 2009-04-21 annular combustion chamber for a turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0802295A FR2930628B1 (fr) 2008-04-24 2008-04-24 Chambre annulaire de combustion pour turbomachine

Publications (2)

Publication Number Publication Date
FR2930628A1 FR2930628A1 (fr) 2009-10-30
FR2930628B1 true FR2930628B1 (fr) 2010-04-30

Family

ID=40149716

Family Applications (1)

Application Number Title Priority Date Filing Date
FR0802295A Active FR2930628B1 (fr) 2008-04-24 2008-04-24 Chambre annulaire de combustion pour turbomachine

Country Status (3)

Country Link
US (1) US20110120144A1 (fr)
FR (1) FR2930628B1 (fr)
WO (1) WO2009133322A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2953907B1 (fr) 2009-12-11 2012-11-02 Snecma Chambre de combustion pour turbomachine
FR2959795B1 (fr) * 2010-05-05 2013-12-06 Snecma Virole de chambre de combustion a contact glissant avec le carter de chambre
FR3020865B1 (fr) 2014-05-12 2016-05-20 Snecma Chambre annulaire de combustion
FR3047545B1 (fr) * 2016-02-10 2018-03-02 Safran Aircraft Engines Chambre de combustion de turbomachine
FR3101935B1 (fr) 2019-10-15 2021-09-10 Safran Aircraft Engines Chambre annulaire de combustion pour turbomachine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1539035A (en) * 1976-04-22 1979-01-24 Rolls Royce Combustion chambers for gas turbine engines
US5024058A (en) * 1989-12-08 1991-06-18 Sundstrand Corporation Hot gas generator
US5197289A (en) * 1990-11-26 1993-03-30 General Electric Company Double dome combustor
FR2686683B1 (fr) * 1992-01-28 1994-04-01 Snecma Turbomachine a chambre de combustion demontable.
US5335502A (en) * 1992-09-09 1994-08-09 General Electric Company Arched combustor
US5970716A (en) * 1997-10-02 1999-10-26 General Electric Company Apparatus for retaining centerbody between adjacent domes of multiple annular combustor employing interference and clamping fits
US6079199A (en) * 1998-06-03 2000-06-27 Pratt & Whitney Canada Inc. Double pass air impingement and air film cooling for gas turbine combustor walls
FR2825785B1 (fr) * 2001-06-06 2004-08-27 Snecma Moteurs Liaison de chambre de combustion cmc de turbomachine en deux parties
US7080513B2 (en) * 2001-08-04 2006-07-25 Siemens Aktiengesellschaft Seal element for sealing a gap and combustion turbine having a seal element
FR2892181B1 (fr) * 2005-10-18 2008-02-01 Snecma Sa Fixation d'une chambre de combustion a l'interieur de son carter
JP4749124B2 (ja) * 2005-11-11 2011-08-17 Ｓｍｃ株式会社 真空用直線搬送装置
FR2897417A1 (fr) * 2006-02-10 2007-08-17 Snecma Sa Chambre de combustion annulaire d'une turbomachine

Also Published As

Publication number Publication date
WO2009133322A1 (fr) 2009-11-05
FR2930628A1 (fr) 2009-10-30
US20110120144A1 (en) 2011-05-26

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