BR112012014057A2 - câmara de combustão para motor de turbina. - Google Patents

câmara de combustão para motor de turbina.

Info

Publication number
BR112012014057A2
BR112012014057A2 BR112012014057A BR112012014057A BR112012014057A2 BR 112012014057 A2 BR112012014057 A2 BR 112012014057A2 BR 112012014057 A BR112012014057 A BR 112012014057A BR 112012014057 A BR112012014057 A BR 112012014057A BR 112012014057 A2 BR112012014057 A2 BR 112012014057A2
Authority
BR
Brazil
Prior art keywords
combustion chamber
turbine engine
wall
turbine
chamber
Prior art date
Application number
BR112012014057A
Other languages
English (en)
Other versions
BR112012014057B1 (pt
Inventor
Caroline Jacqueline Denise Berdou
Laurent Bernard Cameriano
Original Assignee
Snecma
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 filed Critical Snecma
Publication of BR112012014057A2 publication Critical patent/BR112012014057A2/pt
Publication of BR112012014057B1 publication Critical patent/BR112012014057B1/pt

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
    • F23R3/42—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
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05004—Special materials for walls or lining
    • 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
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine 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
    • F23R2900/00018—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

Abstract

câmara de combustão para motor de turbina. a invenção refere-se a uma câmara de combustão (1) para uma turbina tal como um turbo reator ou turbopropulsor de avião, compreendendo paredes anulares internas e externas (3,4) de revolução, ligadas por uma parede anular do fundo da câmara (5). a parede interna (3) é constituída por uma única camada de material cuja espessura e/ou a natureza varia ao longo do eixo longitudinal e/ou a direção circunferencial da referida parede (3).
BR112012014057-4A 2009-12-11 2010-12-02 câmara de combustão para turbomáquina e turbomáquina BR112012014057B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0906009A FR2953907B1 (fr) 2009-12-11 2009-12-11 Chambre de combustion pour turbomachine
FR0906009 2009-12-11
PCT/FR2010/052600 WO2011070273A1 (fr) 2009-12-11 2010-12-02 Chambre de combustion pour turbomachine

Publications (2)

Publication Number Publication Date
BR112012014057A2 true BR112012014057A2 (pt) 2016-04-12
BR112012014057B1 BR112012014057B1 (pt) 2020-12-08

Family

ID=42668056

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012014057-4A BR112012014057B1 (pt) 2009-12-11 2010-12-02 câmara de combustão para turbomáquina e turbomáquina

Country Status (10)

Country Link
US (1) US9897316B2 (pt)
EP (1) EP2510284B1 (pt)
JP (1) JP5718935B2 (pt)
CN (1) CN102782410B (pt)
BR (1) BR112012014057B1 (pt)
CA (1) CA2782661C (pt)
FR (1) FR2953907B1 (pt)
IN (1) IN2012DN05031A (pt)
RU (1) RU2551471C2 (pt)
WO (1) WO2011070273A1 (pt)

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US20140216044A1 (en) * 2012-12-17 2014-08-07 United Technologoes Corporation Gas turbine engine combustor heat shield with increased film cooling effectiveness
US10260748B2 (en) * 2012-12-21 2019-04-16 United Technologies Corporation Gas turbine engine combustor with tailored temperature profile
WO2014160299A1 (en) 2013-03-14 2014-10-02 United Technologies Corporation Combustor panel with increased durability
EP3660401B1 (en) * 2013-05-23 2021-10-06 Raytheon Technologies Corporation Gas turbine engine combustor liner panel
EP3044441B1 (en) * 2013-09-13 2022-07-27 Raytheon Technologies Corporation Shielding pockets for case holes
WO2015077067A1 (en) * 2013-11-21 2015-05-28 United Technologies Corporation Axisymmetric offset of three-dimensional contoured endwalls
US10281152B2 (en) 2013-12-19 2019-05-07 United Technologies Corporation Thermal mechanical dimple array for a combustor wall assembly
DE102014204476A1 (de) 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine
DE102014204481A1 (de) * 2014-03-11 2015-09-17 Rolls-Royce Deutschland Ltd & Co Kg Brennkammer einer Gasturbine
DE102014226707A1 (de) * 2014-12-19 2016-06-23 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit veränderter Wandstärke
US10451280B2 (en) * 2015-02-16 2019-10-22 United Technologies Corporation Combustor panel having material transition region
FR3035707B1 (fr) * 2015-04-29 2019-11-01 Safran Aircraft Engines Chambre de combustion coudee d'une turbomachine
US10222065B2 (en) * 2016-02-25 2019-03-05 General Electric Company Combustor assembly for a gas turbine engine
US10816202B2 (en) 2017-11-28 2020-10-27 General Electric Company Combustor liner for a gas turbine engine and an associated method thereof
US11255543B2 (en) 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
CN114484504A (zh) * 2022-01-19 2022-05-13 中国航发沈阳发动机研究所 一种易于修理的火焰筒

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CH637181A5 (de) * 1977-04-21 1983-07-15 Michael Christian Ludowici Fassadenverkleidung.
US4206865A (en) * 1978-11-14 1980-06-10 United Technologies Corporation Formed louver for burner liner
US4485630A (en) * 1982-12-08 1984-12-04 General Electric Company Combustor liner
US4628694A (en) * 1983-12-19 1986-12-16 General Electric Company Fabricated liner article and method
US5329773A (en) * 1989-08-31 1994-07-19 Alliedsignal Inc. Turbine combustor cooling system
JP3091892B2 (ja) 1992-06-08 2000-09-25 科学技術庁航空宇宙技術研究所長 スペースプレーンとその製造方法
RU2064600C1 (ru) * 1994-04-22 1996-07-27 Конструкторское бюро машиностроения Способ образования теплозащитного покрытия ракетного двигателя твердого топлива
US6314716B1 (en) * 1998-12-18 2001-11-13 Solar Turbines Incorporated Serial cooling of a combustor for a gas turbine engine
US6351949B1 (en) * 1999-09-03 2002-03-05 Allison Advanced Development Company Interchangeable combustor chute
US6434821B1 (en) * 1999-12-06 2002-08-20 General Electric Company Method of making a combustion chamber liner
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US6554562B2 (en) * 2001-06-15 2003-04-29 Honeywell International, Inc. Combustor hot streak alignment for gas turbine engine
US6681577B2 (en) * 2002-01-16 2004-01-27 General Electric Company Method and apparatus for relieving stress in a combustion case in a gas turbine engine
RU2260156C2 (ru) * 2003-08-25 2005-09-10 Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" Жаровая труба камеры сгорания
US7007481B2 (en) * 2003-09-10 2006-03-07 General Electric Company Thick coated combustor liner
GB2420614B (en) * 2004-11-30 2009-06-03 Alstom Technology Ltd Tile and exo-skeleton tile structure
FR2897143B1 (fr) * 2006-02-08 2012-10-05 Snecma Chambre de combustion d'une turbomachine
US7669422B2 (en) * 2006-07-26 2010-03-02 General Electric Company Combustor liner and method of fabricating same
FR2920525B1 (fr) * 2007-08-31 2014-06-13 Snecma Separateur pour alimentation de l'air de refroidissement d'une turbine
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FR2929690B1 (fr) * 2008-04-03 2012-08-17 Snecma Propulsion Solide Chambre de combustion sectorisee en cmc pour turbine a gaz
FR2930628B1 (fr) 2008-04-24 2010-04-30 Snecma Chambre annulaire de combustion pour turbomachine

Also Published As

Publication number Publication date
JP2013513777A (ja) 2013-04-22
IN2012DN05031A (pt) 2015-10-02
CN102782410A (zh) 2012-11-14
FR2953907A1 (fr) 2011-06-17
CA2782661A1 (fr) 2011-06-16
FR2953907B1 (fr) 2012-11-02
CN102782410B (zh) 2015-04-22
CA2782661C (fr) 2017-05-30
BR112012014057B1 (pt) 2020-12-08
EP2510284B1 (fr) 2018-08-29
US9897316B2 (en) 2018-02-20
EP2510284A1 (fr) 2012-10-17
RU2551471C2 (ru) 2015-05-27
RU2012129209A (ru) 2014-01-20
JP5718935B2 (ja) 2015-05-13
WO2011070273A1 (fr) 2011-06-16
US20120240584A1 (en) 2012-09-27

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Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 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: 10 (DEZ) ANOS CONTADOS A PARTIR DE 08/12/2020, OBSERVADAS AS CONDICOES LEGAIS.