DE60012289D1 - Brennkammer für eine Gasturbine - Google Patents

Brennkammer für eine Gasturbine

Info

Publication number
DE60012289D1
DE60012289D1 DE60012289T DE60012289T DE60012289D1 DE 60012289 D1 DE60012289 D1 DE 60012289D1 DE 60012289 T DE60012289 T DE 60012289T DE 60012289 T DE60012289 T DE 60012289T DE 60012289 D1 DE60012289 D1 DE 60012289D1
Authority
DE
Germany
Prior art keywords
combustion chamber
gas turbine
turbine
gas
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.)
Expired - Lifetime
Application number
DE60012289T
Other languages
English (en)
Other versions
DE60012289T2 (de
Inventor
Hisham Salman Alkabie
Robin Thomas David Mcmillan
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.)
Siemens AG
Original Assignee
Alstom Power UK Holdings Ltd
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 Alstom Power UK Holdings Ltd filed Critical Alstom Power UK Holdings Ltd
Publication of DE60012289D1 publication Critical patent/DE60012289D1/de
Application granted granted Critical
Publication of DE60012289T2 publication Critical patent/DE60012289T2/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
    • F23R3/002—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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

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)
DE60012289T 1999-12-01 2000-11-27 Brennkammer für eine Gasturbine Expired - Lifetime DE60012289T2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9928242 1999-12-01
GB9928242A GB2356924A (en) 1999-12-01 1999-12-01 Cooling wall structure for combustor

Publications (2)

Publication Number Publication Date
DE60012289D1 true DE60012289D1 (de) 2004-08-26
DE60012289T2 DE60012289T2 (de) 2005-07-28

Family

ID=10865395

Family Applications (1)

Application Number Title Priority Date Filing Date
DE60012289T Expired - Lifetime DE60012289T2 (de) 1999-12-01 2000-11-27 Brennkammer für eine Gasturbine

Country Status (6)

Country Link
US (1) US6546731B2 (de)
EP (1) EP1104871B1 (de)
JP (1) JP4554802B2 (de)
DE (1) DE60012289T2 (de)
ES (1) ES2223410T3 (de)
GB (1) GB2356924A (de)

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DE10214573A1 (de) * 2002-04-02 2003-10-16 Rolls Royce Deutschland Brennkammer einer Gasturbine mit Starterfilmkühlung
US7086232B2 (en) * 2002-04-29 2006-08-08 General Electric Company Multihole patch for combustor liner of a gas turbine engine
US20050098685A1 (en) * 2002-06-21 2005-05-12 Darko Segota Method and system for regulating pressure and optimizing fluid flow about a fuselage similar body
US7048505B2 (en) 2002-06-21 2006-05-23 Darko Segota Method and system for regulating fluid flow over an airfoil or a hydrofoil
US7296411B2 (en) * 2002-06-21 2007-11-20 Darko Segota Method and system for regulating internal fluid flow within an enclosed or semi-enclosed environment
US7475853B2 (en) * 2002-06-21 2009-01-13 Darko Segota Method and system for regulating external fluid flow over an object's surface, and particularly a wing and diffuser
US6964170B2 (en) * 2003-04-28 2005-11-15 Pratt & Whitney Canada Corp. Noise reducing combustor
US7036316B2 (en) 2003-10-17 2006-05-02 General Electric Company Methods and apparatus for cooling turbine engine combustor exit temperatures
US6868675B1 (en) 2004-01-09 2005-03-22 Honeywell International Inc. Apparatus and method for controlling combustor liner carbon formation
US20050241316A1 (en) * 2004-04-28 2005-11-03 Honeywell International Inc. Uniform effusion cooling method for a can combustion chamber
US7137241B2 (en) * 2004-04-30 2006-11-21 Power Systems Mfg, Llc Transition duct apparatus having reduced pressure loss
US7531048B2 (en) * 2004-10-19 2009-05-12 Honeywell International Inc. On-wing combustor cleaning using direct insertion nozzle, wash agent, and procedure
EP1650503A1 (de) * 2004-10-25 2006-04-26 Siemens Aktiengesellschaft Verfahren zur Kühlung eines Hitzeschildelements und Hitzeschildelement
US20070028595A1 (en) * 2005-07-25 2007-02-08 Mongia Hukam C High pressure gas turbine engine having reduced emissions
US7827801B2 (en) * 2006-02-09 2010-11-09 Siemens Energy, Inc. Gas turbine engine transitions comprising closed cooled transition cooling channels
US7856830B2 (en) * 2006-05-26 2010-12-28 Pratt & Whitney Canada Corp. Noise reducing combustor
US7628020B2 (en) * 2006-05-26 2009-12-08 Pratt & Whitney Canada Cororation Combustor with improved swirl
DE102006042124B4 (de) * 2006-09-07 2010-04-22 Man Turbo Ag Gasturbinenbrennkammer
US7926284B2 (en) * 2006-11-30 2011-04-19 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
JP5296320B2 (ja) * 2007-01-30 2013-09-25 ゼネラル・エレクトリック・カンパニイ 逆流噴射機構を有するシステム及び燃料及び空気を噴射する方法
US7886517B2 (en) * 2007-05-09 2011-02-15 Siemens Energy, Inc. Impingement jets coupled to cooling channels for transition cooling
US7617684B2 (en) * 2007-11-13 2009-11-17 Opra Technologies B.V. Impingement cooled can combustor
US9046269B2 (en) * 2008-07-03 2015-06-02 Pw Power Systems, Inc. Impingement cooling device
US20100037620A1 (en) * 2008-08-15 2010-02-18 General Electric Company, Schenectady Impingement and effusion cooled combustor component
US20100170257A1 (en) * 2009-01-08 2010-07-08 General Electric Company Cooling a one-piece can combustor and related method
US8438856B2 (en) 2009-03-02 2013-05-14 General Electric Company Effusion cooled one-piece can combustor
US20100257863A1 (en) * 2009-04-13 2010-10-14 General Electric Company Combined convection/effusion cooled one-piece can combustor
US20100272953A1 (en) * 2009-04-28 2010-10-28 Honeywell International Inc. Cooled hybrid structure for gas turbine engine and method for the fabrication thereof
GB0912715D0 (en) 2009-07-22 2009-08-26 Rolls Royce Plc Cooling arrangement
US8590314B2 (en) * 2010-04-09 2013-11-26 General Electric Company Combustor liner helical cooling apparatus
US8647053B2 (en) 2010-08-09 2014-02-11 Siemens Energy, Inc. Cooling arrangement for a turbine component
US9157328B2 (en) 2010-12-24 2015-10-13 Rolls-Royce North American Technologies, Inc. Cooled gas turbine engine component
GB201105790D0 (en) * 2011-04-06 2011-05-18 Rolls Royce Plc A cooled double walled article
JP5821550B2 (ja) 2011-11-10 2015-11-24 株式会社Ihi 燃焼器ライナ
EP2644995A1 (de) 2012-03-27 2013-10-02 Siemens Aktiengesellschaft Verbesserte Lochanordnung von Auskleidungen einer Brennkammer eines Gasturbinenmotors mit niedriger Verbrennungsdynamik und niedrigen Emissionen
US9052111B2 (en) 2012-06-22 2015-06-09 United Technologies Corporation Turbine engine combustor wall with non-uniform distribution of effusion apertures
US8834154B2 (en) * 2012-11-28 2014-09-16 Mitsubishi Heavy Industries, Ltd. Transition piece of combustor, and gas turbine having the same
DE102012025375A1 (de) * 2012-12-27 2014-07-17 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Anordnung von Prallkühllöchern und Effusionslöchern in einer Brennkammerwand einer Gasturbine
US10968829B2 (en) * 2013-12-06 2021-04-06 Raytheon Technologies Corporation Cooling an igniter body of a combustor wall
GB201412460D0 (en) * 2014-07-14 2014-08-27 Rolls Royce Plc An Annular Combustion Chamber Wall Arrangement
US10094564B2 (en) * 2015-04-17 2018-10-09 Pratt & Whitney Canada Corp. Combustor dilution hole cooling system
GB201518345D0 (en) * 2015-10-16 2015-12-02 Rolls Royce Combustor for a gas turbine engine
DE102016219424A1 (de) * 2016-10-06 2018-04-12 Rolls-Royce Deutschland Ltd & Co Kg Brennkammeranordnung einer Gasturbine sowie Fluggasturbine
US10697635B2 (en) 2017-03-20 2020-06-30 Raytheon Technologies Corporation Impingement cooled components having integral thermal transfer features
US11028705B2 (en) * 2018-03-16 2021-06-08 Doosan Heavy Industries Construction Co., Ltd. Transition piece having cooling rings
KR102593506B1 (ko) * 2018-09-11 2023-10-24 한화에어로스페이스 주식회사 가스 터빈 장치의 케이스 구조체
DE102019105442A1 (de) 2019-03-04 2020-09-10 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Herstellung eines Triebwerksbauteils mit einer Kühlkanalanordnung und Triebwerksbauteil

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GB1530594A (en) * 1974-12-13 1978-11-01 Rolls Royce Perforate laminated material
US4168348A (en) 1974-12-13 1979-09-18 Rolls-Royce Limited Perforated laminated material
US4118146A (en) * 1976-08-11 1978-10-03 United Technologies Corporation Coolable wall
GB2033071B (en) 1978-10-28 1982-07-21 Rolls Royce Sheet metal laminate
GB2049152B (en) * 1979-05-01 1983-05-18 Rolls Royce Perforate laminated material
JPS5872822A (ja) * 1981-10-26 1983-04-30 Hitachi Ltd ガスタ−ビン燃焼器の冷却構造
US4422300A (en) * 1981-12-14 1983-12-27 United Technologies Corporation Prestressed combustor liner for gas turbine engine
JPH0660740B2 (ja) 1985-04-05 1994-08-10 工業技術院長 ガスタービンの燃焼器
GB2176274B (en) * 1985-06-07 1989-02-01 Ruston Gas Turbines Ltd Combustor for gas turbine engine
GB2192705B (en) 1986-07-18 1990-06-06 Rolls Royce Plc Porous sheet structure for a combustion chamber
US5435139A (en) 1991-03-22 1995-07-25 Rolls-Royce Plc Removable combustor liner for gas turbine engine combustor
US5216886A (en) * 1991-08-14 1993-06-08 The United States Of America As Represented By The Secretary Of The Air Force Segmented cell wall liner for a combustion chamber
JPH08135968A (ja) * 1994-11-08 1996-05-31 Toshiba Corp ガスタービン燃焼器
US5782294A (en) * 1995-12-18 1998-07-21 United Technologies Corporation Cooled liner apparatus
US5758504A (en) * 1996-08-05 1998-06-02 Solar Turbines Incorporated Impingement/effusion cooled combustor liner

Also Published As

Publication number Publication date
EP1104871A1 (de) 2001-06-06
US6546731B2 (en) 2003-04-15
US20010004835A1 (en) 2001-06-28
GB2356924A (en) 2001-06-06
JP2001227359A (ja) 2001-08-24
GB9928242D0 (en) 2000-01-26
JP4554802B2 (ja) 2010-09-29
EP1104871B1 (de) 2004-07-21
ES2223410T3 (es) 2005-03-01
DE60012289T2 (de) 2005-07-28

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: SIEMENS AG, 80333 MUENCHEN, DE