BR0201430A - Métodos e aparelho para resfriar combustores de motor de turbina a gás - Google Patents

Métodos e aparelho para resfriar combustores de motor de turbina a gás

Info

Publication number
BR0201430A
BR0201430A BR0201430-0A BR0201430A BR0201430A BR 0201430 A BR0201430 A BR 0201430A BR 0201430 A BR0201430 A BR 0201430A BR 0201430 A BR0201430 A BR 0201430A
Authority
BR
Brazil
Prior art keywords
deflector
gas turbine
methods
cooling
turbine engine
Prior art date
Application number
BR0201430-0A
Other languages
English (en)
Other versions
BR0201430B1 (pt
Inventor
Craig Douglas Young
Paul Edward Sabla
Steven Clayton Vise
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of BR0201430A publication Critical patent/BR0201430A/pt
Publication of BR0201430B1 publication Critical patent/BR0201430B1/pt

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/78—Cooling burner parts
    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

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)

Abstract

"MéTODOS E APARELHO PARA RESFRIAR COMBUSTORES DE MOTOR DE TURBINA A GáS". Uma montagem de defletor cone de alargamento (75) para um combustor de motor de turbina a gás (16) que facilita estender uma vida útil do combustor em uma maneira barata e segura é descrita. A montagem de uma peça inclui uma parte de defletor (76) e uma parte de cone de alargamento (78). A parte de defletor inclui uma abertura integral (168) que se estende através da parte de defletor para receber fluido de resfriamento na mesma. A abertura de resfriamento se estende circunferencialmente dentro da parte de defletor. O fluido de resfriamento descarregado da abertura de resfriamento é usada para resfriar por impacto uma parte da parte de cone de alargamento para facilitar reduzir uma temperatura de operação e estender uma vida útil do combustor.
BRPI0201430-0A 2001-04-27 2002-04-26 métodos e aparelho para resfriar combustores de motor de turbina a gás. BR0201430B1 (pt)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US09/844,411 US6530227B1 (en) 2001-04-27 2001-04-27 Methods and apparatus for cooling gas turbine engine combustors

Publications (2)

Publication Number Publication Date
BR0201430A true BR0201430A (pt) 2003-06-10
BR0201430B1 BR0201430B1 (pt) 2011-04-05

Family

ID=25292656

Family Applications (1)

Application Number Title Priority Date Filing Date
BRPI0201430-0A BR0201430B1 (pt) 2001-04-27 2002-04-26 métodos e aparelho para resfriar combustores de motor de turbina a gás.

Country Status (6)

Country Link
US (1) US6530227B1 (pt)
EP (1) EP1258681B1 (pt)
JP (1) JP4137502B2 (pt)
BR (1) BR0201430B1 (pt)
CA (1) CA2383463C (pt)
DE (1) DE60218565T2 (pt)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1312865A1 (de) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Ringbrennkammer für eine Gasturbine
US6655027B2 (en) * 2002-01-15 2003-12-02 General Electric Company Methods for assembling gas turbine engine combustors
US7007480B2 (en) * 2003-04-09 2006-03-07 Honeywell International, Inc. Multi-axial pivoting combustor liner in gas turbine engine
US6923002B2 (en) * 2003-08-28 2005-08-02 General Electric Company Combustion liner cap assembly for combustion dynamics reduction
US20070095071A1 (en) * 2003-09-29 2007-05-03 Kastrup David A Apparatus for assembling gas turbine engine combustors
US7013649B2 (en) * 2004-05-25 2006-03-21 General Electric Company Gas turbine engine combustor mixer
FR2894327B1 (fr) * 2005-12-05 2008-05-16 Snecma Sa Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2897107B1 (fr) * 2006-02-09 2013-01-18 Snecma Paroi transversale de chambre de combustion munie de trous de multiperforation
FR2899314B1 (fr) * 2006-03-30 2008-05-09 Snecma Sa Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2903172B1 (fr) * 2006-06-29 2008-10-17 Snecma Sa Agencement pour chambre de combustion de turbomachine ayant un defecteur a collerette
FR2903171B1 (fr) * 2006-06-29 2008-10-17 Snecma Sa Agencement a liaison par crabot pour chambre de combustion de turbomachine
FR2903169B1 (fr) * 2006-06-29 2011-11-11 Snecma Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
US8205426B2 (en) * 2006-07-31 2012-06-26 General Electric Company Method and apparatus for operating gas turbine engines
US7654091B2 (en) * 2006-08-30 2010-02-02 General Electric Company Method and apparatus for cooling gas turbine engine combustors
FR2910115B1 (fr) * 2006-12-19 2012-11-16 Snecma Deflecteur pour fond de chambre de combustion, chambre de combustion en etant equipee et turboreacteur les comportant
DE102007050276A1 (de) * 2007-10-18 2009-04-23 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner für ein Gasturbinentriebwerk
US20100242484A1 (en) * 2009-03-31 2010-09-30 Baha Mahmoud Suleiman Apparatus and method for cooling gas turbine engine combustors
US9127842B2 (en) * 2009-05-27 2015-09-08 Siemens Aktiengesellschaft Burner, operating method and assembly method
JP5924618B2 (ja) * 2012-06-07 2016-05-25 川崎重工業株式会社 燃料噴射装置
US9021812B2 (en) 2012-07-27 2015-05-05 Honeywell International Inc. Combustor dome and heat-shield assembly
US10077714B2 (en) * 2015-11-06 2018-09-18 Rolls-Royce Plc Repairable fuel injector
US10690347B2 (en) * 2017-02-01 2020-06-23 General Electric Company CMC combustor deflector
US10801726B2 (en) * 2017-09-21 2020-10-13 General Electric Company Combustor mixer purge cooling structure
FR3082284B1 (fr) * 2018-06-07 2020-12-11 Safran Aircraft Engines Chambre de combustion pour une turbomachine
US11280492B2 (en) 2018-08-23 2022-03-22 General Electric Company Combustor assembly for a turbo machine
GB202211589D0 (en) 2022-08-09 2022-09-21 Rolls Royce Plc A combustor assembly

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US2699648A (en) * 1950-10-03 1955-01-18 Gen Electric Combustor sectional liner structure with annular inlet nozzles
GB1539136A (en) * 1976-07-07 1979-01-24 Snecma Gas turbine combustion chambers
FR2585770B1 (fr) * 1985-08-02 1989-07-13 Snecma Dispositif d'injection a bol elargi pour chambre de combustion de turbomachine
US4870818A (en) * 1986-04-18 1989-10-03 United Technologies Corporation Fuel nozzle guide structure and retainer for a gas turbine engine
US4686823A (en) * 1986-04-28 1987-08-18 United Technologies Corporation Sliding joint for an annular combustor
US4934145A (en) * 1988-10-12 1990-06-19 United Technologies Corporation Combustor bulkhead heat shield assembly
CA2056592A1 (en) 1990-12-21 1992-06-22 Phillip D. Napoli Multi-hole film cooled combustor liner with slotted film starter
US5142871A (en) * 1991-01-22 1992-09-01 General Electric Company Combustor dome plate support having uniform thickness arcuate apex with circumferentially spaced coolant apertures
CA2070518C (en) 1991-07-01 2001-10-02 Adrian Mark Ablett Combustor dome assembly
US5154060A (en) 1991-08-12 1992-10-13 General Electric Company Stiffened double dome combustor
JP2597800B2 (ja) * 1992-06-12 1997-04-09 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジン用燃焼器
US5323604A (en) 1992-11-16 1994-06-28 General Electric Company Triple annular combustor for gas turbine engine
DE19508111A1 (de) * 1995-03-08 1996-09-12 Bmw Rolls Royce Gmbh Hitzeschild-Anordnung für eine Gasturbinen-Brennkammer
FR2751731B1 (fr) * 1996-07-25 1998-09-04 Snecma Ensemble bol-deflecteur pour chambre de combustion de turbomachine
US6212870B1 (en) * 1998-09-22 2001-04-10 General Electric Company Self fixturing combustor dome assembly
US6442940B1 (en) * 2001-04-27 2002-09-03 General Electric Company Gas-turbine air-swirler attached to dome and combustor in single brazing operation

Also Published As

Publication number Publication date
JP2002339762A (ja) 2002-11-27
DE60218565T2 (de) 2007-11-22
CA2383463C (en) 2009-02-03
DE60218565D1 (de) 2007-04-19
BR0201430B1 (pt) 2011-04-05
US6530227B1 (en) 2003-03-11
JP4137502B2 (ja) 2008-08-20
EP1258681A3 (en) 2003-04-09
CA2383463A1 (en) 2002-10-27
EP1258681B1 (en) 2007-03-07
EP1258681A2 (en) 2002-11-20

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Legal Events

Date Code Title Description
B06A Patent application procedure suspended [chapter 6.1 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 26/04/2002, OBSERVADAS AS CONDICOES LEGAIS.

B21F Lapse acc. art. 78, item iv - on non-payment of the annual fees in time
B24J Lapse because of non-payment of annual fees (definitively: art 78 iv lpi, resolution 113/2013 art. 12)