CA2613268C - Fond de chambre, procede de realisation de celui-ci, chambre de combustion le comportant et turboreacteur en etant equipe - Google Patents

Fond de chambre, procede de realisation de celui-ci, chambre de combustion le comportant et turboreacteur en etant equipe Download PDF

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Publication number
CA2613268C
CA2613268C CA2613268A CA2613268A CA2613268C CA 2613268 C CA2613268 C CA 2613268C CA 2613268 A CA2613268 A CA 2613268A CA 2613268 A CA2613268 A CA 2613268A CA 2613268 C CA2613268 C CA 2613268C
Authority
CA
Canada
Prior art keywords
combustion chamber
chamber
ribs
deflectors
combustion
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
CA2613268A
Other languages
English (en)
French (fr)
Other versions
CA2613268A1 (fr
Inventor
Christophe Pieussergues
Denis Jean Maurice Sandelis
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
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=38222462&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=CA2613268(C) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of CA2613268A1 publication Critical patent/CA2613268A1/fr
Application granted granted Critical
Publication of CA2613268C publication Critical patent/CA2613268C/fr
Active legal-status Critical Current
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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
    • 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
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49236—Fluid pump or compressor making

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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
CA2613268A 2006-12-07 2007-12-05 Fond de chambre, procede de realisation de celui-ci, chambre de combustion le comportant et turboreacteur en etant equipe Active CA2613268C (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0655377 2006-12-07
FR0655377A FR2909748B1 (fr) 2006-12-07 2006-12-07 Fond de chambre, procede de realisation de celui-ci, chambre de combustion le comportant et turboreacteur en etant equipe

Publications (2)

Publication Number Publication Date
CA2613268A1 CA2613268A1 (fr) 2008-06-07
CA2613268C true CA2613268C (fr) 2015-02-03

Family

ID=38222462

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2613268A Active CA2613268C (fr) 2006-12-07 2007-12-05 Fond de chambre, procede de realisation de celui-ci, chambre de combustion le comportant et turboreacteur en etant equipe

Country Status (6)

Country Link
US (1) US7954327B2 (https=)
EP (1) EP1930659B1 (https=)
JP (1) JP4974295B2 (https=)
CA (1) CA2613268C (https=)
FR (1) FR2909748B1 (https=)
RU (1) RU2435108C2 (https=)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2918443B1 (fr) * 2007-07-04 2009-10-30 Snecma Sa Chambre de combustion comportant des deflecteurs de protection thermique de fond de chambre et moteur a turbine a gaz en etant equipe
FR2920525B1 (fr) * 2007-08-31 2014-06-13 Snecma Separateur pour alimentation de l'air de refroidissement d'une turbine
FR2921462B1 (fr) * 2007-09-21 2012-08-24 Snecma Chambre de combustion annulaire de moteur a turbine a gaz
FR2948988B1 (fr) 2009-08-04 2011-12-09 Snecma Chambre de combustion de turbomachine comprenant des orifices d'entree d'air ameliores
DE102010023816A1 (de) 2010-06-15 2011-12-15 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammeranordnung
DE102011108887A1 (de) 2011-07-28 2013-01-31 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenzentripetalringbrennkammer sowie Verfahren zur Strömungsführung
FR2982010B1 (fr) * 2011-10-26 2013-11-08 Snecma Chambre de combustion annulaire dans une turbomachine
US10234141B2 (en) * 2016-04-28 2019-03-19 United Technoloigies Corporation Ceramic and ceramic matrix composite attachment methods and systems

Family Cites Families (31)

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US2560223A (en) 1948-02-04 1951-07-10 Wright Aeronautical Corp Double air-swirl baffle construction for fuel burners
US2560207A (en) 1948-02-04 1951-07-10 Wright Aeronautical Corp Annular combustion chamber with circumferentially spaced double air-swirl burners
GB774592A (en) * 1954-05-18 1957-05-15 Havilland Engine Co Ltd Adjustable propulsion nozzles
US4454711A (en) * 1981-10-29 1984-06-19 Avco Corporation Self-aligning fuel nozzle assembly
US4567730A (en) * 1983-10-03 1986-02-04 General Electric Company Shielded combustor
US4843825A (en) * 1988-05-16 1989-07-04 United Technologies Corporation Combustor dome heat shield
US4914918A (en) * 1988-09-26 1990-04-10 United Technologies Corporation Combustor segmented deflector
US4934145A (en) * 1988-10-12 1990-06-19 United Technologies Corporation Combustor bulkhead heat shield assembly
FR2673454B1 (fr) * 1991-02-28 1995-01-13 Snecma Chambre de combustion comportant une paroi de fond comprenant une pluralite de troncs de cones partiels.
US5289687A (en) * 1992-03-30 1994-03-01 General Electric Company One-piece cowl for a double annular combustor
US5419115A (en) * 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
DE4427222A1 (de) * 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Hitzeschild für eine Gasturbinen-Brennkammer
US5581999A (en) 1994-12-15 1996-12-10 United Technologies Corporation Bulkhead liner with raised lip
US6070830A (en) * 1997-09-29 2000-06-06 General Electric Company Faceted exhaust nozzle
US6438958B1 (en) * 2000-02-28 2002-08-27 General Electric Company Apparatus for reducing heat load in combustor panels
US6557349B1 (en) * 2000-04-17 2003-05-06 General Electric Company Method and apparatus for increasing heat transfer from combustors
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
US7121095B2 (en) * 2003-08-11 2006-10-17 General Electric Company Combustor dome assembly of a gas turbine engine having improved deflector plates
US7093441B2 (en) * 2003-10-09 2006-08-22 United Technologies Corporation Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume
US7051532B2 (en) * 2003-10-17 2006-05-30 General Electric Company Methods and apparatus for film cooling gas turbine engine combustors
US7506511B2 (en) * 2003-12-23 2009-03-24 Honeywell International Inc. Reduced exhaust emissions gas turbine engine combustor
US6983599B2 (en) * 2004-02-12 2006-01-10 General Electric Company Combustor member and method for making a combustor assembly
US7140185B2 (en) * 2004-07-12 2006-11-28 United Technologies Corporation Heatshielded article
FR2888631B1 (fr) * 2005-07-18 2010-12-10 Snecma Turbomachine a distribution angulaire de l'air
FR2897145B1 (fr) * 2006-02-08 2013-01-18 Snecma Chambre de combustion annulaire de turbomachine a fixations alternees.
FR2897417A1 (fr) * 2006-02-10 2007-08-17 Snecma Sa Chambre de combustion annulaire d'une turbomachine
US8596071B2 (en) * 2006-05-05 2013-12-03 General Electric Company Method and apparatus for assembling a gas turbine engine
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US20100095680A1 (en) * 2008-10-22 2010-04-22 Honeywell International Inc. Dual wall structure for use in a combustor of a gas turbine engine

Also Published As

Publication number Publication date
CA2613268A1 (fr) 2008-06-07
JP4974295B2 (ja) 2012-07-11
RU2007145372A (ru) 2009-06-20
FR2909748B1 (fr) 2009-07-10
EP1930659A1 (fr) 2008-06-11
US20080134661A1 (en) 2008-06-12
RU2435108C2 (ru) 2011-11-27
JP2008145098A (ja) 2008-06-26
US7954327B2 (en) 2011-06-07
EP1930659B1 (fr) 2017-06-07
FR2909748A1 (fr) 2008-06-13

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