BR112012024179A2 - câmara de combustão de turbomáquina que tem um compressor centrífugo sem defletor - Google Patents

câmara de combustão de turbomáquina que tem um compressor centrífugo sem defletor

Info

Publication number
BR112012024179A2
BR112012024179A2 BR112012024179A BR112012024179A BR112012024179A2 BR 112012024179 A2 BR112012024179 A2 BR 112012024179A2 BR 112012024179 A BR112012024179 A BR 112012024179A BR 112012024179 A BR112012024179 A BR 112012024179A BR 112012024179 A2 BR112012024179 A2 BR 112012024179A2
Authority
BR
Brazil
Prior art keywords
combustion chamber
chamber
deflector
nozzle
centrifugal compressor
Prior art date
Application number
BR112012024179A
Other languages
English (en)
Other versions
BR112012024179B1 (pt
Inventor
Thierry Cortes
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 BR112012024179A2 publication Critical patent/BR112012024179A2/pt
Publication of BR112012024179B1 publication Critical patent/BR112012024179B1/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
    • F23R3/02—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
    • 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
    • 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
    • F23R3/02—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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • F23R2900/03041—Effusion 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

câmara de combustão de turbomáquina que tem um compressor centrífugo sem defletor. trata-se de uma câmara de combustão anular para uma turbomáquina que compreende uma parede externa (11) e uma parede interna (12) que são orientadas substancial e axialmente em relação ao eixo geométrico de rotação de turbomáquina, sendo que a dita câmara de combustão é fechada a montante por uma parede de extremidade de câmara (13) orientada substancialmente e radialmente, sendo que a dita câmara (1) é suprida com ar comprimido vindo partir de um compressor por meio de um bocal (3), a direção de saída do qual é descolada radialmente em relação ao eixo geométrico mediano (10) da câmara de combustão (1), sendo que a dita parede de extremidade de câmara tem orifícios de suprimento de ar de resfriamento inclinados na direção normal para a dita parede de extremidade de câmara (13). é caracterizada pelo fato de que o número de orifícios orientados radialmente na direção oposta a essa em que a saída do dito bocal está localizada é maior que o número de orifícios orientados radialmente na direção de saída do dito bocal.
BR112012024179-6A 2010-03-26 2011-03-23 câmara de combustão anular para turbomáquina e turbomáquina BR112012024179B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1052244 2010-03-26
FR1052244A FR2958013B1 (fr) 2010-03-26 2010-03-26 Chambre de combustion de turbomachine a compresseur centrifuge sans deflecteur
PCT/FR2011/050622 WO2011117543A1 (fr) 2010-03-26 2011-03-23 Chambre de combustion de turbomachine a compresseur centrifuge sans deflecteur

Publications (2)

Publication Number Publication Date
BR112012024179A2 true BR112012024179A2 (pt) 2016-07-05
BR112012024179B1 BR112012024179B1 (pt) 2020-08-25

Family

ID=43244828

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112012024179-6A BR112012024179B1 (pt) 2010-03-26 2011-03-23 câmara de combustão anular para turbomáquina e turbomáquina

Country Status (8)

Country Link
US (1) US9383106B2 (pt)
EP (1) EP2553340B1 (pt)
CN (1) CN102812297B (pt)
BR (1) BR112012024179B1 (pt)
CA (1) CA2794243C (pt)
FR (1) FR2958013B1 (pt)
RU (1) RU2563424C2 (pt)
WO (1) WO2011117543A1 (pt)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2996284B1 (fr) 2012-10-02 2019-03-15 Safran Aircraft Engines Fond de chambre annulaire pour chambre de combustion de turbomachine d'aeronef, muni de perforations permettant un refroidissement par flux giratoire
KR101471612B1 (ko) 2013-07-01 2014-12-12 남부대학교산학협력단 광학렌즈 기반 태양위치 추적정밀도 측정시스템
CN103541877B (zh) * 2013-11-13 2016-03-02 深圳智慧能源技术有限公司 太阳能燃气轮机
CN103557076B (zh) * 2013-11-13 2016-03-02 深圳智慧能源技术有限公司 蓄热式燃气轮机
US10330884B2 (en) * 2017-02-20 2019-06-25 Rosemount Aerospace Inc. Mounting of optical elements for imaging in air vehicles
CN109668173B (zh) * 2019-01-14 2019-11-26 西安增材制造国家研究院有限公司 一种蒸发管式紧凑型燃烧室
CN113739208B (zh) * 2021-09-09 2022-08-26 成都中科翼能科技有限公司 一种用于低污染燃气轮机的混合冷却火焰筒

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2444477A1 (de) 1974-09-18 1976-04-01 Blau Kg Kraftfahrzeugtech Verschlussdeckel mit zur sicherung nach aussen zu abgedichtet eingesetztem riegelschloss
RU2027111C1 (ru) * 1991-10-23 1995-01-20 Акционерное общество закрытого типа "Минитокс" Камера сгорания
US5307637A (en) * 1992-07-09 1994-05-03 General Electric Company Angled multi-hole film cooled single wall combustor dome plate
FR2714154B1 (fr) * 1993-12-22 1996-01-19 Snecma Chambre de combustion comportant une paroi munie d'une multiperforation.
FR2770283B1 (fr) * 1997-10-29 1999-11-19 Snecma Chambre de combustion pour turbomachine
FR2856467B1 (fr) * 2003-06-18 2005-09-02 Snecma Moteurs Chambre de combustion annulaire de turbomachine
US7308794B2 (en) * 2004-08-27 2007-12-18 Pratt & Whitney Canada Corp. Combustor and method of improving manufacturing accuracy thereof
US7260936B2 (en) * 2004-08-27 2007-08-28 Pratt & Whitney Canada Corp. Combustor having means for directing air into the combustion chamber in a spiral pattern
US7451600B2 (en) * 2005-07-06 2008-11-18 Pratt & Whitney Canada Corp. Gas turbine engine combustor with improved cooling
FR2897107B1 (fr) * 2006-02-09 2013-01-18 Snecma Paroi transversale de chambre de combustion munie de trous de multiperforation
US7628020B2 (en) * 2006-05-26 2009-12-08 Pratt & Whitney Canada Cororation Combustor with improved swirl
US8171736B2 (en) * 2007-01-30 2012-05-08 Pratt & Whitney Canada Corp. Combustor with chamfered dome
US8006497B2 (en) * 2008-05-30 2011-08-30 Honeywell International Inc. Diffusers, diffusion systems, and methods for controlling airflow through diffusion systems
FR2941287B1 (fr) 2009-01-19 2011-03-25 Snecma Paroi de chambre de combustion de turbomachine a une seule rangee annulaire d'orifices d'entree d'air primaire et de dilution

Also Published As

Publication number Publication date
US20130008166A1 (en) 2013-01-10
FR2958013A1 (fr) 2011-09-30
CN102812297B (zh) 2015-05-13
EP2553340B1 (fr) 2014-12-17
CA2794243A1 (fr) 2011-09-29
CA2794243C (fr) 2017-05-16
RU2563424C2 (ru) 2015-09-20
BR112012024179B1 (pt) 2020-08-25
CN102812297A (zh) 2012-12-05
EP2553340A1 (fr) 2013-02-06
FR2958013B1 (fr) 2014-06-20
US9383106B2 (en) 2016-07-05
RU2012144323A (ru) 2014-05-10
WO2011117543A1 (fr) 2011-09-29

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Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according art. 34 industrial property law
B06U Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure
B09A Decision: intention to grant
B16A Patent or certificate of addition of invention granted

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 23/03/2011, OBSERVADAS AS CONDICOES LEGAIS.