EP1939529A1 - Revêtement de chambre de combustion CMC à structure à double couche - Google Patents

Revêtement de chambre de combustion CMC à structure à double couche Download PDF

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Publication number
EP1939529A1
EP1939529A1 EP07122980A EP07122980A EP1939529A1 EP 1939529 A1 EP1939529 A1 EP 1939529A1 EP 07122980 A EP07122980 A EP 07122980A EP 07122980 A EP07122980 A EP 07122980A EP 1939529 A1 EP1939529 A1 EP 1939529A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
heat protection
carrier layer
layer
protection layer
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.)
Withdrawn
Application number
EP07122980A
Other languages
German (de)
English (en)
Inventor
Bernhard Heidenreich
Michael Kriescher
Stefan Hackemann
Berhard Kanka
Walter Luxem
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
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 Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Publication of EP1939529A1 publication Critical patent/EP1939529A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/007—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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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

Definitions

  • DE 19730751 A1 describes a combustion chamber lining, in which the heat protection layer is realized by ceramic components, which in turn rest directly on the entire surface of a carrier layer. Again, the back of the heat protection layer can not be cooled directly by cooling air.
  • US 2002/0184891 A1 describes a single layer heat protection layer which is relatively thick to limit susceptibility to vibration by sufficient rigidity.
  • the object of the present invention is thus to provide a combustion chamber lining for gas turbines which, in spite of the lowest possible weight, should have the greatest possible rigidity, the heat and heat resistant layer, if possible, being resistant both to the inside and the outside can be cooled.
  • the object underlying the invention is achieved in a first embodiment by a combustion chamber lining of gas turbines with a hot gas side facing gas-permeable heat protection layer (1) and one of the heat protection layer (1) by spacer elements (3) separate carrier layer (2).
  • the distance of the heat protection layer (1) to the carrier layer (2) is advantageously 3 to 30 mm, since in this area the circulation of the cooling air is particularly efficient and yet a particularly high rigidity and thus a low susceptibility to vibration can be achieved.
  • the combustion chamber lining is produced by joining the carrier layer (2) to the heat protection layer (1) if both the fiber material and the matrix material are SiC.
  • the liquid siliconization process liquid silicon infiltration, LSI
  • a C- and / or SiC-containing joining paste can be used with particular preference, as is known from US Pat DE 19636223 A1 is known or the PIP or LPI method (polymer infiltration and pyrolysis or liquid polymer infiltration) with SiC-forming, polymeric precursors.
  • gaseous SiC precursors in the CVI process Cerhemical Vapor Infiltration).
  • the carrier layer (2) and the heat protection layer (1) are made in one piece by winding fibers onto a mold, the fibers being coated with a ceramic slurry or ceramic-forming polymeric precursors such as e.g. Poycarbosilanes, polycarbosilazanes, polysiloxanes or MADB / PBS, or carbon-forming, polymeric precursors (for example, phenolic resins) are soaked.
  • a ceramic slurry or ceramic-forming polymeric precursors such as e.g. Poycarbosilanes, polycarbosilazanes, polysiloxanes or MADB / PBS, or carbon-forming, polymeric precursors (for example, phenolic resins) are soaked.
EP07122980A 2006-12-22 2007-12-12 Revêtement de chambre de combustion CMC à structure à double couche Withdrawn EP1939529A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102006060857.7A DE102006060857B4 (de) 2006-12-22 2006-12-22 CMC-Brennkammerauskleidung in Doppelschichtbauweise

Publications (1)

Publication Number Publication Date
EP1939529A1 true EP1939529A1 (fr) 2008-07-02

Family

ID=39257719

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07122980A Withdrawn EP1939529A1 (fr) 2006-12-22 2007-12-12 Revêtement de chambre de combustion CMC à structure à double couche

Country Status (2)

Country Link
EP (1) EP1939529A1 (fr)
DE (1) DE102006060857B4 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101254170B1 (ko) 2010-11-30 2013-04-18 두산중공업 주식회사 가스터빈의 연소기 라이너 및 그의 제조방법
EP3054218A1 (fr) * 2015-02-04 2016-08-10 Rolls-Royce plc Chambre de combustion et segment de la chambre de combustion
EP3018415A3 (fr) * 2014-11-07 2016-08-17 United Technologies Corporation Refroidissement de trou de dilution de chambre de combustion
EP3073196A1 (fr) * 2015-03-26 2016-09-28 United Technologies Corporation Canal de refroidissement de paroi de chambre de combustion
EP3130853A1 (fr) * 2015-08-13 2017-02-15 Rolls-Royce plc Chambre de combustion et segment de chambre de combustion
US10436446B2 (en) 2013-09-11 2019-10-08 General Electric Company Spring loaded and sealed ceramic matrix composite combustor liner

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008010294A1 (de) * 2008-02-21 2009-08-27 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit keramischem Flammenrohr

Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4838031A (en) * 1987-08-06 1989-06-13 Avco Corporation Internally cooled combustion chamber liner
DE4114768A1 (de) 1990-05-17 1991-11-21 Siemens Ag Keramischer hitzeschild fuer eine heissgasfuehrende struktur
US5113660A (en) 1990-06-27 1992-05-19 The United States Of America As Represented By The Secretary Of The Air Force High temperature combustor liner
US5291731A (en) 1993-03-23 1994-03-08 The United States Of America As Represented By The Secretary Of The Navy Torpedo with external combustion engine having an expansion chamber
US5291732A (en) 1993-02-08 1994-03-08 General Electric Company Combustor liner support assembly
DE19502730A1 (de) 1995-01-28 1996-08-01 Abb Management Ag Keramische Auskleidung
US5553455A (en) 1987-12-21 1996-09-10 United Technologies Corporation Hybrid ceramic article
DE19730751A1 (de) 1996-07-24 1998-01-29 Siemens Ag Keramisches Bauteil für eine Wärmeschutzschicht sowie Wärmeschutzschicht
DE19636223A1 (de) 1996-09-06 1998-03-12 Deutsch Zentr Luft & Raumfahrt Verfahren zum dauerhaften Verbinden von wenigstens zwei Bauteilkomponenten zu einem Festkörper
DE19727407A1 (de) 1997-06-27 1999-01-07 Siemens Ag Hitzeschild
EP1128131A1 (fr) 2000-02-23 2001-08-29 Siemens Aktiengesellschaft Bouclier thermique, chambre de combustion et turbine à gaz
EP1152191A2 (fr) 2000-05-05 2001-11-07 General Electric Company Chambre de combustion ayant une chemise de chambre de combustion faite de matériau composite à matrice céramique
EP1235032A2 (fr) 2001-02-26 2002-08-28 United Technologies Corporation Chambre de combustion à faible émission pour turbines à gaz
US20020184891A1 (en) 2001-06-06 2002-12-12 Snecma Moteurs Architecture for a combustion chamber made of ceramic matrix material
EP0943867B1 (fr) 1998-03-17 2002-12-18 ALSTOM (Switzerland) Ltd Revêtement céramique pour une chambre de combustion
DE102004009262A1 (de) 2003-03-04 2005-03-10 Snecma Propulsion Solide S A Verfahren zur Herstellung eines mehrfach perforierten Teils aus einem Verbundwerkstoff mit Keramikmatrize
EP1528322A2 (fr) 2003-10-23 2005-05-04 United Technologies Corporation Chambre de combustion

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10155420A1 (de) * 2001-11-12 2003-05-22 Rolls Royce Deutschland Hitzeschildanordnung mit Dichtungselement

Patent Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4838031A (en) * 1987-08-06 1989-06-13 Avco Corporation Internally cooled combustion chamber liner
US5553455A (en) 1987-12-21 1996-09-10 United Technologies Corporation Hybrid ceramic article
DE4114768A1 (de) 1990-05-17 1991-11-21 Siemens Ag Keramischer hitzeschild fuer eine heissgasfuehrende struktur
US5113660A (en) 1990-06-27 1992-05-19 The United States Of America As Represented By The Secretary Of The Air Force High temperature combustor liner
US5291732A (en) 1993-02-08 1994-03-08 General Electric Company Combustor liner support assembly
US5291731A (en) 1993-03-23 1994-03-08 The United States Of America As Represented By The Secretary Of The Navy Torpedo with external combustion engine having an expansion chamber
DE19502730A1 (de) 1995-01-28 1996-08-01 Abb Management Ag Keramische Auskleidung
DE19730751A1 (de) 1996-07-24 1998-01-29 Siemens Ag Keramisches Bauteil für eine Wärmeschutzschicht sowie Wärmeschutzschicht
DE19636223A1 (de) 1996-09-06 1998-03-12 Deutsch Zentr Luft & Raumfahrt Verfahren zum dauerhaften Verbinden von wenigstens zwei Bauteilkomponenten zu einem Festkörper
DE19727407A1 (de) 1997-06-27 1999-01-07 Siemens Ag Hitzeschild
EP0943867B1 (fr) 1998-03-17 2002-12-18 ALSTOM (Switzerland) Ltd Revêtement céramique pour une chambre de combustion
EP1128131A1 (fr) 2000-02-23 2001-08-29 Siemens Aktiengesellschaft Bouclier thermique, chambre de combustion et turbine à gaz
EP1152191A2 (fr) 2000-05-05 2001-11-07 General Electric Company Chambre de combustion ayant une chemise de chambre de combustion faite de matériau composite à matrice céramique
EP1235032A2 (fr) 2001-02-26 2002-08-28 United Technologies Corporation Chambre de combustion à faible émission pour turbines à gaz
US20020184891A1 (en) 2001-06-06 2002-12-12 Snecma Moteurs Architecture for a combustion chamber made of ceramic matrix material
DE102004009262A1 (de) 2003-03-04 2005-03-10 Snecma Propulsion Solide S A Verfahren zur Herstellung eines mehrfach perforierten Teils aus einem Verbundwerkstoff mit Keramikmatrize
EP1528322A2 (fr) 2003-10-23 2005-05-04 United Technologies Corporation Chambre de combustion

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
J. KIMMEL; J. PRICE ET AL., PROCEEDINGS OF ASME TURBO EXPO 2003 POWER FOR LAND, June 2003 (2003-06-01)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101254170B1 (ko) 2010-11-30 2013-04-18 두산중공업 주식회사 가스터빈의 연소기 라이너 및 그의 제조방법
US10436446B2 (en) 2013-09-11 2019-10-08 General Electric Company Spring loaded and sealed ceramic matrix composite combustor liner
EP3018415A3 (fr) * 2014-11-07 2016-08-17 United Technologies Corporation Refroidissement de trou de dilution de chambre de combustion
EP3054218A1 (fr) * 2015-02-04 2016-08-10 Rolls-Royce plc Chambre de combustion et segment de la chambre de combustion
US20160258624A1 (en) * 2015-02-04 2016-09-08 Rolls-Royce Plc Combustion chamber and a combustion chamber segment
US10502421B2 (en) * 2015-02-04 2019-12-10 Rolls-Royce Plc Combustion chamber and a combustion chamber segment
EP3073196A1 (fr) * 2015-03-26 2016-09-28 United Technologies Corporation Canal de refroidissement de paroi de chambre de combustion
US10480787B2 (en) 2015-03-26 2019-11-19 United Technologies Corporation Combustor wall cooling channel formed by additive manufacturing
EP3130853A1 (fr) * 2015-08-13 2017-02-15 Rolls-Royce plc Chambre de combustion et segment de chambre de combustion
US10634350B2 (en) 2015-08-13 2020-04-28 Rolls-Royce Plc Combustion chamber and a combustion chamber segment

Also Published As

Publication number Publication date
DE102006060857A1 (de) 2008-06-26
DE102006060857B4 (de) 2014-02-13

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