BR112014007742A2 - câmara de combustão anular em uma turbomáquina - Google Patents

câmara de combustão anular em uma turbomáquina

Info

Publication number
BR112014007742A2
BR112014007742A2 BR112014007742A BR112014007742A BR112014007742A2 BR 112014007742 A2 BR112014007742 A2 BR 112014007742A2 BR 112014007742 A BR112014007742 A BR 112014007742A BR 112014007742 A BR112014007742 A BR 112014007742A BR 112014007742 A2 BR112014007742 A2 BR 112014007742A2
Authority
BR
Brazil
Prior art keywords
turbomachine
combustion chamber
annular combustion
injection systems
injector
Prior art date
Application number
BR112014007742A
Other languages
English (en)
Other versions
BR112014007742B1 (pt
Inventor
Jean Maurice Sandelis Denis
Alain Christophe Bourgois Sébastien
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 BR112014007742A2 publication Critical patent/BR112014007742A2/pt
Publication of BR112014007742B1 publication Critical patent/BR112014007742B1/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
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • F02C7/266—Electric
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Nozzles (AREA)

Abstract

1/1 resumo “câmara de combustão anular em uma turbomáquina” a invenção se refere a uma câmara anular de combustão de turbomáquina, que compreende duas paredes de revolução coaxiais interna (18) e externa (20), ligadas em suas extremidades a montante por uma parede anular de fundo de câmara atravessada por sistemas de injeção que compreendem cada um deles um injetor e pelo menos um turbilhonador destinado a produzir um fluxo de ar giratório que se mistura a jusante ao combustível em proveniência do injetor e pelo menos uma vela (42) de ignição montada em um orifício da parede de revolução externa (20) a jusante dos sistemas de injeção. a vela (42) está situada circunferencialmente entre dois sistemas de injeção (s1, s2) adjacentes que são configurados de maneira a produzir camadas de mistura ar/combustível que giram em sentidos opostos (b, c).
BR112014007742-8A 2011-10-26 2012-10-22 câmara anular de combustão de turbomáquina, e, turbomáquina BR112014007742B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1159715A FR2982010B1 (fr) 2011-10-26 2011-10-26 Chambre de combustion annulaire dans une turbomachine
FR1159715 2011-10-26
PCT/FR2012/052415 WO2013060974A2 (fr) 2011-10-26 2012-10-22 Chambre de combustion annulaire dans une turbomachine

Publications (2)

Publication Number Publication Date
BR112014007742A2 true BR112014007742A2 (pt) 2017-04-04
BR112014007742B1 BR112014007742B1 (pt) 2021-02-17

Family

ID=47191979

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112014007742-8A BR112014007742B1 (pt) 2011-10-26 2012-10-22 câmara anular de combustão de turbomáquina, e, turbomáquina

Country Status (8)

Country Link
US (1) US9581334B2 (pt)
EP (1) EP2771619B1 (pt)
CN (1) CN103874887B (pt)
BR (1) BR112014007742B1 (pt)
CA (1) CA2850259C (pt)
FR (1) FR2982010B1 (pt)
RU (1) RU2608513C2 (pt)
WO (1) WO2013060974A2 (pt)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2940389A1 (en) * 2014-05-02 2015-11-04 Siemens Aktiengesellschaft Combustor burner arrangement
US11415058B2 (en) * 2020-12-23 2022-08-16 Collins Engine Nozzles, Inc. Torch ignitors with tangential injection

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2647369A (en) * 1946-09-06 1953-08-04 Leduc Rene Combustion chamber for fluid fuel burning in an air stream of high velocity
US3373562A (en) * 1966-03-17 1968-03-19 Wingaersheek Turbine Co Inc Combustion chamber for gas turbines and the like having improved flame holder
US3834159A (en) * 1973-08-03 1974-09-10 Gen Electric Combustion apparatus
GB2198518B (en) * 1986-12-10 1990-08-01 Rolls Royce Plc Combustion apparatus for a gas turbine engine
US4991398A (en) * 1989-01-12 1991-02-12 United Technologies Corporation Combustor fuel nozzle arrangement
US5257500A (en) * 1992-07-27 1993-11-02 General Electric Company Aircraft engine ignition system
DE19520291A1 (de) * 1995-06-02 1996-12-05 Abb Management Ag Brennkammer
DE19549143A1 (de) * 1995-12-29 1997-07-03 Abb Research Ltd Gasturbinenringbrennkammer
GB2319078B (en) * 1996-11-08 1999-11-03 Europ Gas Turbines Ltd Combustor arrangement
US6487861B1 (en) * 2001-06-05 2002-12-03 General Electric Company Combustor for gas turbine engines with low air flow swirlers
FR2829228B1 (fr) * 2001-08-28 2005-07-15 Snecma Moteurs Chambre de combustion annulaire a double tete etagee
FR2859272B1 (fr) * 2003-09-02 2005-10-14 Snecma Moteurs Systeme d'injection air/carburant, dans une chambre de combustion de turbomachine, ayant des moyens de generation de plasmas froids
WO2005028960A2 (en) * 2003-09-05 2005-03-31 Delavan Inc. Pilot combustor for stabilizing combustion in gas turbine engines
US6968693B2 (en) * 2003-09-22 2005-11-29 General Electric Company Method and apparatus for reducing gas turbine engine emissions
EP1828684A1 (de) * 2004-12-23 2007-09-05 Alstom Technology Ltd Vormischbrenner mit mischstrecke
JP3958767B2 (ja) * 2005-03-18 2007-08-15 川崎重工業株式会社 ガスタービン燃焼器およびその着火方法
FR2897417A1 (fr) * 2006-02-10 2007-08-17 Snecma Sa Chambre de combustion annulaire d'une turbomachine
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
FR2909748B1 (fr) * 2006-12-07 2009-07-10 Snecma Sa Fond de chambre, procede de realisation de celui-ci, chambre de combustion le comportant et turboreacteur en etant equipe
FR2943119B1 (fr) * 2009-03-12 2011-03-25 Snecma Systemes d'injection de carburant dans une chambre de combustion de turbomachine

Also Published As

Publication number Publication date
WO2013060974A2 (fr) 2013-05-02
CA2850259C (fr) 2019-12-03
RU2608513C2 (ru) 2017-01-19
CN103874887B (zh) 2015-11-25
BR112014007742B1 (pt) 2021-02-17
CN103874887A (zh) 2014-06-18
US20150020501A1 (en) 2015-01-22
WO2013060974A3 (fr) 2013-12-19
EP2771619B1 (fr) 2015-12-16
FR2982010B1 (fr) 2013-11-08
CA2850259A1 (fr) 2013-05-02
RU2014121101A (ru) 2015-12-10
FR2982010A1 (fr) 2013-05-03
US9581334B2 (en) 2017-02-28
EP2771619A2 (fr) 2014-09-03

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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: 20 (VINTE) ANOS CONTADOS A PARTIR DE 22/10/2012, OBSERVADAS AS CONDICOES LEGAIS.