BR112015024058A2 - sistema de injeção de ar e combustível, câmara de combustão anular e motor de turbina - Google Patents

sistema de injeção de ar e combustível, câmara de combustão anular e motor de turbina

Info

Publication number
BR112015024058A2
BR112015024058A2 BR112015024058A BR112015024058A BR112015024058A2 BR 112015024058 A2 BR112015024058 A2 BR 112015024058A2 BR 112015024058 A BR112015024058 A BR 112015024058A BR 112015024058 A BR112015024058 A BR 112015024058A BR 112015024058 A2 BR112015024058 A2 BR 112015024058A2
Authority
BR
Brazil
Prior art keywords
air
fuel injection
annular
combustion chamber
turbine engine
Prior art date
Application number
BR112015024058A
Other languages
English (en)
Other versions
BR112015024058B1 (pt
Inventor
Guin Christian
Hernandez Didier
François Rullaud Matthieu
Original Assignee
Office National Detudes Rech Aerospatiales
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 Office National Detudes Rech Aerospatiales, Snecma filed Critical Office National Detudes Rech Aerospatiales
Publication of BR112015024058A2 publication Critical patent/BR112015024058A2/pt
Publication of BR112015024058B1 publication Critical patent/BR112015024058B1/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
    • F23R3/28—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • F23D11/105—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet at least one of the fluids being submitted to a swirling motion
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F02C7/22—Fuel supply systems
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • 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
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2206/00—Burners for specific applications
    • F23D2206/10—Turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11002—Liquid fuel burners with more than one nozzle
    • 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
    • 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
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E20/00—Combustion technologies with mitigation potential
    • Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Abstract

resumo “sistema de injeção de ar e combustível, câmara de combustão anular e motor de turbina” o principal propósito da invenção é um sistema de injeção de ar e combustível (24) para um domo de câmara de combustão de motor de turbina (10) que compreende pelo menos dois dispositivos de injeção de combustível, que incluem um injetor central (26) e um injetor anular periférico (43), dispostos ao redor do dito injetor central (26), e um canal anular interno de entrada de ar (71) no qual o injetor central (26) se abre para permitir a mistura entre o combustível proveniente do injetor central (26) e a entrada de ar no canal anular interno (71), e pelo menos um canal anular externo de entrada de ar (30 ; 30a, 30b) para permitir o enriquecimento dessa mistura com ar e para estabilizar a zona de combustão-piloto (p), sendo que o canal anular interno (71) e o dito pelo menos um canal anular externo (30 ; 30a, 30b) são separados por uma parede anular intermediária (70) que se estende ao redor do injetor central (26) e que tem um perfil interno convergente (70a).
BR112015024058-5A 2013-03-19 2014-03-14 Sistema de injeção de ar e combustível, câmara de combustão anular e motor de turbina BR112015024058B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1352442A FR3003632B1 (fr) 2013-03-19 2013-03-19 Systeme d'injection pour chambre de combustion de turbomachine comportant une paroi annulaire a profil interne convergent
FR1352442 2013-03-19
PCT/FR2014/050603 WO2014147325A1 (fr) 2013-03-19 2014-03-14 Systeme d'injection pour chambre de combustion de turbomachine comportant une paroi annulaire a profil interne convergent

Publications (2)

Publication Number Publication Date
BR112015024058A2 true BR112015024058A2 (pt) 2017-07-18
BR112015024058B1 BR112015024058B1 (pt) 2021-08-24

Family

ID=48225061

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112015024058-5A BR112015024058B1 (pt) 2013-03-19 2014-03-14 Sistema de injeção de ar e combustível, câmara de combustão anular e motor de turbina

Country Status (8)

Country Link
US (1) US10036552B2 (pt)
EP (1) EP2976572B1 (pt)
CN (1) CN105121960B (pt)
BR (1) BR112015024058B1 (pt)
CA (1) CA2907533C (pt)
FR (1) FR3003632B1 (pt)
RU (1) RU2645801C2 (pt)
WO (1) WO2014147325A1 (pt)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9939157B2 (en) * 2015-03-10 2018-04-10 General Electric Company Hybrid air blast fuel nozzle
FR3039254B1 (fr) * 2015-07-24 2021-10-08 Snecma Chambre de combustion comportant des dispositifs d'injection additionnels debouchant directement dans les zones de recirculation de coin, turbomachine la comprenant, et procede d'alimentation en carburant de celle-ci
US20170227224A1 (en) * 2016-02-09 2017-08-10 Solar Turbines Incorporated Fuel injector for combustion engine system, and engine operating method
US11067277B2 (en) 2016-10-07 2021-07-20 General Electric Company Component assembly for a gas turbine engine
FR3068113B1 (fr) * 2017-06-27 2019-08-23 Safran Helicopter Engines Injecteur de carburant a jet plat pour une turbomachine d'aeronef
DE102017217329A1 (de) * 2017-09-28 2019-03-28 Rolls-Royce Deutschland Ltd & Co Kg Düse mit axial überstehendem Luftleitelement für eine Brennkammer eines Triebwerks
CN110657452B (zh) * 2018-06-29 2020-10-27 中国航发商用航空发动机有限责任公司 低污染燃烧室及其燃烧控制方法
CN111255569B (zh) * 2020-01-13 2021-06-22 南京航空航天大学 一种模态转换联合变几何调节的内并联型进气道及控制方法

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US3474970A (en) * 1967-03-15 1969-10-28 Parker Hannifin Corp Air assist nozzle
GB1114728A (en) * 1967-03-20 1968-05-22 Rolls Royce Burner e.g. for a gas turbine engine combustion chamber
US3684186A (en) 1970-06-26 1972-08-15 Ex Cell O Corp Aerating fuel nozzle
US4562698A (en) * 1980-12-02 1986-01-07 Ex-Cell-O Corporation Variable area means for air systems of air blast type fuel nozzle assemblies
CN1011152B (zh) * 1987-12-25 1991-01-09 航空发动机的结构和研究国营公司 喷射装置隔板的控制机构
US4996837A (en) * 1987-12-28 1991-03-05 Sundstrand Corporation Gas turbine with forced vortex fuel injection
US5833141A (en) * 1997-05-30 1998-11-10 General Electric Company Anti-coking dual-fuel nozzle for a gas turbine combustor
US6272840B1 (en) * 2000-01-13 2001-08-14 Cfd Research Corporation Piloted airblast lean direct fuel injector
US20020162333A1 (en) * 2001-05-02 2002-11-07 Honeywell International, Inc., Law Dept. Ab2 Partial premix dual circuit fuel injector
US6543235B1 (en) * 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US6718770B2 (en) * 2002-06-04 2004-04-13 General Electric Company Fuel injector laminated fuel strip
US6986255B2 (en) 2002-10-24 2006-01-17 Rolls-Royce Plc Piloted airblast lean direct fuel injector with modified air splitter
JP4065947B2 (ja) * 2003-08-05 2008-03-26 独立行政法人 宇宙航空研究開発機構 ガスタービン燃焼器用燃料・空気プレミキサー
RU2287110C2 (ru) * 2004-11-15 2006-11-10 Виктор Ташеевич Чумак Способ интенсификации процесса сжигания газа и горелочное устройство для его реализации
US8511097B2 (en) 2005-03-18 2013-08-20 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine combustor and ignition method of igniting fuel mixture in the same
JP4364911B2 (ja) * 2007-02-15 2009-11-18 川崎重工業株式会社 ガスタービンエンジンの燃焼器
FR2919898B1 (fr) 2007-08-10 2014-08-22 Snecma Injecteur multipoint pour turbomachine
FR2921464B1 (fr) 2007-09-24 2014-03-28 Snecma Agencement de systemes d'injection dans un fond de chambre de combustion d'un moteur d'aeronef
US8286433B2 (en) * 2007-10-26 2012-10-16 Solar Turbines Inc. Gas turbine fuel injector with removable pilot liquid tube
GB0820560D0 (en) * 2008-11-11 2008-12-17 Rolls Royce Plc Fuel injector
FR2945854B1 (fr) 2009-05-19 2015-08-07 Snecma Vrille melangeuse pour un injecteur de carburant dans une chambre de combustion d'une turbine a gaz et dispositif de combustion correspondant
FR2951246B1 (fr) 2009-10-13 2011-11-11 Snecma Injecteur multi-point pour une chambre de combustion de turbomachine
FR2952166B1 (fr) 2009-11-05 2012-01-06 Snecma Dispositif melangeur de carburant pour chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air
FR2956897B1 (fr) 2010-02-26 2012-07-20 Snecma Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection d'air ameliorant le melange air-carburant
FR2958015B1 (fr) * 2010-03-24 2013-07-05 Snecma Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection de carburant entre deux flux d'air coaxiaux
FR2964725B1 (fr) 2010-09-14 2012-10-12 Snecma Carenage aerodynamique pour fond de chambre de combustion
EP2436979A1 (en) * 2010-09-30 2012-04-04 Siemens Aktiengesellschaft Burner for a gas turbine
FR2968410B1 (fr) * 2010-12-07 2012-11-16 Nexans Cassette de lovage de fibres et de maintien d'epissures
JP5772245B2 (ja) 2011-06-03 2015-09-02 川崎重工業株式会社 燃料噴射装置
US9182124B2 (en) * 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same

Also Published As

Publication number Publication date
EP2976572A1 (fr) 2016-01-27
FR3003632B1 (fr) 2016-10-14
WO2014147325A1 (fr) 2014-09-25
CA2907533C (fr) 2020-11-24
FR3003632A1 (fr) 2014-09-26
RU2015144484A (ru) 2017-04-28
US10036552B2 (en) 2018-07-31
EP2976572B1 (fr) 2018-05-09
US20160281991A1 (en) 2016-09-29
RU2645801C2 (ru) 2018-02-28
CA2907533A1 (fr) 2014-09-25
CN105121960B (zh) 2018-01-05
BR112015024058B1 (pt) 2021-08-24
CN105121960A (zh) 2015-12-02

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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 14/03/2014, OBSERVADAS AS CONDICOES LEGAIS.