DE60221743D1 - Verdünnungsluftlöcher verwendende Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff - Google Patents

Verdünnungsluftlöcher verwendende Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff

Info

Publication number
DE60221743D1
DE60221743D1 DE60221743T DE60221743T DE60221743D1 DE 60221743 D1 DE60221743 D1 DE 60221743D1 DE 60221743 T DE60221743 T DE 60221743T DE 60221743 T DE60221743 T DE 60221743T DE 60221743 D1 DE60221743 D1 DE 60221743D1
Authority
DE
Germany
Prior art keywords
mounting
air holes
matrix composite
ceramic matrix
turbine combustor
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 - Lifetime
Application number
DE60221743T
Other languages
English (en)
Other versions
DE60221743T2 (de
Inventor
Didier Hernandez
Gwenaelle Calvez
Alexandre Forestier
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
Publication of DE60221743D1 publication Critical patent/DE60221743D1/de
Application granted granted Critical
Publication of DE60221743T2 publication Critical patent/DE60221743T2/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/06—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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • 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
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
DE60221743T 2001-06-06 2002-06-04 Verdünnungsluftlöcher verwendende Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff Expired - Lifetime DE60221743T2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0107366 2001-06-06
FR0107366A FR2825784B1 (fr) 2001-06-06 2001-06-06 Accrochage de chambre de combustion cmc de turbomachine utilisant les trous de dilution

Publications (2)

Publication Number Publication Date
DE60221743D1 true DE60221743D1 (de) 2007-09-27
DE60221743T2 DE60221743T2 (de) 2008-06-05

Family

ID=8863989

Family Applications (1)

Application Number Title Priority Date Filing Date
DE60221743T Expired - Lifetime DE60221743T2 (de) 2001-06-06 2002-06-04 Verdünnungsluftlöcher verwendende Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff

Country Status (5)

Country Link
US (1) US6668559B2 (de)
EP (1) EP1265037B1 (de)
JP (1) JP3947429B2 (de)
DE (1) DE60221743T2 (de)
FR (1) FR2825784B1 (de)

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FR2871846B1 (fr) * 2004-06-17 2006-09-29 Snecma Moteurs Sa Chambre de combustion en cmc de turbine a gaz supportee dans un carter metallique par des organes de liaison en cmc
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US7559203B2 (en) * 2005-09-16 2009-07-14 Pratt & Whitney Canada Corp. Cooled support boss for a combustor in a gas turbine engine
US8038389B2 (en) * 2006-01-04 2011-10-18 General Electric Company Method and apparatus for assembling turbine nozzle assembly
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FR2896575B1 (fr) * 2006-01-26 2013-01-18 Snecma Chambre de combustion annulaire d'une turbomachine
FR2897418B1 (fr) 2006-02-10 2013-03-01 Snecma Chambre de combustion annulaire d'une turbomachine
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US20090067917A1 (en) * 2007-09-07 2009-03-12 The Boeing Company Bipod Flexure Ring
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FR2935753B1 (fr) * 2008-09-08 2011-07-01 Snecma Propulsion Solide Liaisons souples a butee pour fixation de piece en cmc
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US9335051B2 (en) * 2011-07-13 2016-05-10 United Technologies Corporation Ceramic matrix composite combustor vane ring assembly
JP6162949B2 (ja) * 2011-12-16 2017-07-12 ゼネラル・エレクトリック・カンパニイ Ｃｍｃライナの強化冷却のための一体化バッフルシステム
US9038395B2 (en) * 2012-03-29 2015-05-26 Honeywell International Inc. Combustors with quench inserts
FR2988777B1 (fr) * 2012-03-29 2014-04-25 Snecma Propulsion Solide Integration de pieces d'arriere-corps de moteur aeronautique
US9360215B2 (en) * 2012-04-02 2016-06-07 United Technologies Corporation Combustor having a beveled grommet
EP2696036A1 (de) 2012-08-09 2014-02-12 MTU Aero Engines GmbH Klemmring für eine Strömungsmaschine
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US9689572B2 (en) * 2013-02-06 2017-06-27 General Electric Company Variable volume combustor with a conical liner support
WO2015047509A2 (en) * 2013-08-30 2015-04-02 United Technologies Corporation Vena contracta swirling dilution passages for gas turbine engine combustor
WO2015030927A1 (en) * 2013-08-30 2015-03-05 United Technologies Corporation Contoured dilution passages for a gas turbine engine combustor
WO2015038274A1 (en) 2013-09-11 2015-03-19 General Electric Company Spring loaded and sealed ceramic matrix composite combustor liner
EP3052862A4 (de) * 2013-10-04 2016-11-02 United Technologies Corp Brennkammertafel mit mehreren befestigungen
EP3077640B1 (de) * 2013-12-06 2021-06-02 Raytheon Technologies Corporation Brennkammerlöschöffnungskühlung
EP2927595B1 (de) * 2014-04-02 2019-11-13 United Technologies Corporation Schutzmanschettenanordnung und verfahren zum entwurf
EP2957833B1 (de) * 2014-06-17 2018-10-24 Rolls-Royce Corporation Brennkammeranordnung mit rinnen
FR3022613B1 (fr) * 2014-06-24 2019-04-19 Safran Helicopter Engines Bossage pour chambre de combustion.
FR3022480A1 (fr) * 2014-06-24 2015-12-25 Turbomeca Machine pour sertir un bossage de chambre de combustion.
US10132498B2 (en) * 2015-01-20 2018-11-20 United Technologies Corporation Thermal barrier coating of a combustor dilution hole
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US10168051B2 (en) * 2015-09-02 2019-01-01 General Electric Company Combustor assembly for a turbine engine
DE102015225107A1 (de) 2015-12-14 2017-06-14 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit Schindelbefestigung mittels Rastelementen
US10281153B2 (en) * 2016-02-25 2019-05-07 General Electric Company Combustor assembly
US10378771B2 (en) * 2016-02-25 2019-08-13 General Electric Company Combustor assembly
EP3290806B1 (de) * 2016-09-05 2021-06-23 Ansaldo Energia Switzerland AG Brennkammereinrichtung für ein gasturbinentriebwerk und gasturbinentriebwerk mit einer solchen brennkammereinrichtung
US10393381B2 (en) * 2017-01-27 2019-08-27 General Electric Company Unitary flow path structure
US10247019B2 (en) 2017-02-23 2019-04-02 General Electric Company Methods and features for positioning a flow path inner boundary within a flow path assembly
US10753283B2 (en) * 2017-03-20 2020-08-25 Pratt & Whitney Canada Corp. Combustor heat shield cooling hole arrangement
US20180283695A1 (en) * 2017-04-03 2018-10-04 United Technologies Corporation Combustion panel grommet
US11054136B2 (en) 2018-11-30 2021-07-06 Pratt & Whitney Canada Corp. Interface for double-skin combustor liner
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US11215367B2 (en) * 2019-10-03 2022-01-04 Raytheon Technologies Corporation Mounting a ceramic component to a non-ceramic component in a gas turbine engine
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Also Published As

Publication number Publication date
JP2002364850A (ja) 2002-12-18
US20020184889A1 (en) 2002-12-12
DE60221743T2 (de) 2008-06-05
JP3947429B2 (ja) 2007-07-18
EP1265037B1 (de) 2007-08-15
EP1265037A1 (de) 2002-12-11
FR2825784A1 (fr) 2002-12-13
US6668559B2 (en) 2003-12-30
FR2825784B1 (fr) 2003-08-29

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Legal Events

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