FR2441725A1 - Turbine a gaz - Google Patents

Turbine a gaz

Info

Publication number
FR2441725A1
FR2441725A1 FR7928175A FR7928175A FR2441725A1 FR 2441725 A1 FR2441725 A1 FR 2441725A1 FR 7928175 A FR7928175 A FR 7928175A FR 7928175 A FR7928175 A FR 7928175A FR 2441725 A1 FR2441725 A1 FR 2441725A1
Authority
FR
France
Prior art keywords
bypass
gas turbine
nozzle
annular
turbine
Prior art date
Legal status (The legal status 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 status listed.)
Granted
Application number
FR7928175A
Other languages
English (en)
Other versions
FR2441725B1 (fr
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of FR2441725A1 publication Critical patent/FR2441725A1/fr
Application granted granted Critical
Publication of FR2441725B1 publication Critical patent/FR2441725B1/fr
Granted legal-status Critical Current

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
    • 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
    • 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
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means

Landscapes

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

Abstract

CETTE TURBINE EST DU TYPE COMPRENANT UN SYSTEME DE COMBUSTION CONSISTANT EN UNE CHAMBRE DE COMBUSTION ANNULAIRE, UNE RANGEE ANNULAIRE DE PAIRES DE PREMIERES ET DE SECONDES BUSES ESPACEES RADIALEMENT, UN COLLECTEUR D'ALIMENTATION EN CARBURANT COMPRENANT DES CONDUITES DE DERIVATION CONDUISANT AUX PAIRES RESPECTIVES DE BUSES. CHAQUE CONDUITE DE DERIVATION 19 EST RELIEE DIRECTEMENT A LA PREMIERE BUSE 15 D'UNE PAIRE RESPECTIVE, UNE SOUPAPE D'ARRET 21 EST PREVUE ENTRE CHAQUE CONDUITE DE DERIVATION 19 ET LADITE SECONDE BUSE RESPECTIVE 16.
FR7928175A 1978-11-20 1979-11-15 Turbine a gaz Granted FR2441725A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB7845179 1978-11-20

Publications (2)

Publication Number Publication Date
FR2441725A1 true FR2441725A1 (fr) 1980-06-13
FR2441725B1 FR2441725B1 (fr) 1982-09-10

Family

ID=10501165

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7928175A Granted FR2441725A1 (fr) 1978-11-20 1979-11-15 Turbine a gaz

Country Status (5)

Country Link
US (1) US4305255A (fr)
JP (1) JPS5575537A (fr)
DE (1) DE2946393C2 (fr)
FR (1) FR2441725A1 (fr)
GB (1) GB2036296B (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0689007A1 (fr) * 1994-06-22 1995-12-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Refroidissement de l'injecteur de décollage d'une chambre de combustion à deux têtes
EP0689006A1 (fr) 1994-06-22 1995-12-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Procédé et dispositif pour alimenter en carburant et refroidir l'injecteur de décollage d'une chambre de combustion à deux têtes
CN107023855A (zh) * 2017-05-25 2017-08-08 上海泛智能源装备有限公司 一种燃气轮机

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US4337616A (en) * 1980-04-14 1982-07-06 General Motors Corporation Fuel air ratio controlled fuel splitter
SE423742B (sv) * 1980-09-29 1982-05-24 United Motor & Transmissions A Gasturbinanleggning for automotiv drift
EP0059490B1 (fr) * 1981-03-04 1984-12-12 BBC Aktiengesellschaft Brown, Boveri & Cie. Chambre de combustion annulaire avec brûleur annulaire pour turbines à gaz
US4638636A (en) * 1984-06-28 1987-01-27 General Electric Company Fuel nozzle
US4742685A (en) * 1986-11-04 1988-05-10 Ex-Cell-O Corporation Fuel distributing and metering assembly
US5036657A (en) * 1987-06-25 1991-08-06 General Electric Company Dual manifold fuel system
US4903478A (en) * 1987-06-25 1990-02-27 General Electric Company Dual manifold fuel system
US4991398A (en) * 1989-01-12 1991-02-12 United Technologies Corporation Combustor fuel nozzle arrangement
US5156002A (en) * 1990-03-05 1992-10-20 Rolf J. Mowill Low emissions gas turbine combustor
US5099644A (en) * 1990-04-04 1992-03-31 General Electric Company Lean staged combustion assembly
US5284019A (en) * 1990-06-12 1994-02-08 The United States Of America As Represented By The Secretary Of The Air Force Double dome, single anular combustor with daisy mixer
US5197289A (en) * 1990-11-26 1993-03-30 General Electric Company Double dome combustor
US5197278A (en) * 1990-12-17 1993-03-30 General Electric Company Double dome combustor and method of operation
US5423178A (en) * 1992-09-28 1995-06-13 Parker-Hannifin Corporation Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle
DE59208715D1 (de) * 1992-11-09 1997-08-21 Asea Brown Boveri Gasturbinen-Brennkammer
US5289685A (en) * 1992-11-16 1994-03-01 General Electric Company Fuel supply system for a gas turbine engine
US6220034B1 (en) 1993-07-07 2001-04-24 R. Jan Mowill Convectively cooled, single stage, fully premixed controllable fuel/air combustor
US5628182A (en) * 1993-07-07 1997-05-13 Mowill; R. Jan Star combustor with dilution ports in can portions
US5638674A (en) * 1993-07-07 1997-06-17 Mowill; R. Jan Convectively cooled, single stage, fully premixed controllable fuel/air combustor with tangential admission
US5572862A (en) * 1993-07-07 1996-11-12 Mowill Rolf Jan Convectively cooled, single stage, fully premixed fuel/air combustor for gas turbine engine modules
US5377483A (en) * 1993-07-07 1995-01-03 Mowill; R. Jan Process for single stage premixed constant fuel/air ratio combustion
US5613357A (en) * 1993-07-07 1997-03-25 Mowill; R. Jan Star-shaped single stage low emission combustor system
US5442922A (en) * 1993-12-09 1995-08-22 United Technologies Corporation Fuel staging system
DE19524213A1 (de) * 1995-07-03 1997-01-09 Abb Management Ag Brennstoffzuführung für Gasturbinen mit Ringbrennkammer
GB2312250A (en) * 1996-04-18 1997-10-22 Rolls Royce Plc Staged gas turbine fuel system with a single supply manifold, to which the main burners are connected through valves.
US5924276A (en) * 1996-07-17 1999-07-20 Mowill; R. Jan Premixer with dilution air bypass valve assembly
US5771696A (en) * 1996-10-21 1998-06-30 General Electric Company Internal manifold fuel injection assembly for gas turbine
GB9708662D0 (en) * 1997-04-30 1997-06-18 Rolls Royce Plc Fuel injector
US5983642A (en) * 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
DE19825335A1 (de) * 1998-06-05 1999-12-09 Abb Patent Gmbh Verfahren zum Betrieb einer Gasturbine
US6925809B2 (en) 1999-02-26 2005-08-09 R. Jan Mowill Gas turbine engine fuel/air premixers with variable geometry exit and method for controlling exit velocities
US6481209B1 (en) * 2000-06-28 2002-11-19 General Electric Company Methods and apparatus for decreasing combustor emissions with swirl stabilized mixer
DE60217768T2 (de) 2001-07-18 2007-11-15 Rolls-Royce Plc Kraftstofffördervorrichtung
US6915638B2 (en) * 2002-03-28 2005-07-12 Parker-Hannifin Corporation Nozzle with fluted tube
US6968699B2 (en) * 2003-05-08 2005-11-29 General Electric Company Sector staging combustor
US7506511B2 (en) * 2003-12-23 2009-03-24 Honeywell International Inc. Reduced exhaust emissions gas turbine engine combustor
US7854120B2 (en) * 2006-03-03 2010-12-21 Pratt & Whitney Canada Corp. Fuel manifold with reduced losses
US7743612B2 (en) * 2006-09-22 2010-06-29 Pratt & Whitney Canada Corp. Internal fuel manifold and fuel inlet connection
US7992390B2 (en) * 2008-09-23 2011-08-09 Pratt & Whitney Canada Corp. External rigid fuel manifold
EP2189720A1 (fr) * 2008-11-21 2010-05-26 Siemens Aktiengesellschaft Agencement de brûleur
EP2362142A1 (fr) * 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Agencement de brûleur
ES2389482T3 (es) 2010-02-19 2012-10-26 Siemens Aktiengesellschaft Sistema de quemador
US8613197B2 (en) 2010-08-05 2013-12-24 General Electric Company Turbine combustor with fuel nozzles having inner and outer fuel circuits
US9958093B2 (en) 2010-12-08 2018-05-01 Parker-Hannifin Corporation Flexible hose assembly with multiple flow passages
US9194297B2 (en) 2010-12-08 2015-11-24 Parker-Hannifin Corporation Multiple circuit fuel manifold
US8429915B1 (en) * 2011-10-17 2013-04-30 General Electric Company Injector having multiple fuel pegs
FR2994217B1 (fr) * 2012-08-06 2018-05-04 Safran Helicopter Engines Rampe d'injection modulaire a double circuit
US10619855B2 (en) * 2012-09-06 2020-04-14 United Technologies Corporation Fuel delivery system with a cavity coupled fuel injector
US9772054B2 (en) 2013-03-15 2017-09-26 Parker-Hannifin Corporation Concentric flexible hose assembly
US9995220B2 (en) 2013-12-20 2018-06-12 Pratt & Whitney Canada Corp. Fluid manifold for gas turbine engine and method for delivering fuel to a combustor using same
US10364751B2 (en) * 2015-08-03 2019-07-30 Delavan Inc Fuel staging
CN106678875B (zh) * 2016-07-12 2019-08-09 北京航空航天大学 一种主燃级采用喷油管供油的低排放燃烧室
US11053862B2 (en) 2017-09-25 2021-07-06 Delavan Inc. Electronic fuel control for gas turbine engines
US10605171B2 (en) * 2018-04-10 2020-03-31 Delavan Inc. Fuel nozzle manifold systems for turbomachines
US11421883B2 (en) 2020-09-11 2022-08-23 Raytheon Technologies Corporation Fuel injector assembly with a helical swirler passage for a turbine engine
US11754287B2 (en) 2020-09-11 2023-09-12 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US11649964B2 (en) 2020-12-01 2023-05-16 Raytheon Technologies Corporation Fuel injector assembly for a turbine engine
US11808455B2 (en) * 2021-11-24 2023-11-07 Rtx Corporation Gas turbine engine combustor with integral fuel conduit(s)
US11846249B1 (en) 2022-09-02 2023-12-19 Rtx Corporation Gas turbine engine with integral bypass duct

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR945035A (fr) * 1946-02-25 1949-04-22 Lucas Ltd Joseph Perfectionnements aux dispositifs de réglage de combustible liquide
US2590853A (en) * 1945-10-16 1952-04-01 Gen Electric Liquid fuel metering and spraying system
FR1028959A (fr) * 1949-11-14 1953-05-29 Rolls Royce Perfectionnements aux appareillages d'alimentation en combustible pour moteurs à turbine à gaz
US2724239A (en) * 1952-04-21 1955-11-22 Samuel S Fox Fuel flow distributing and manifold pressurizing valve for dual orifice fuel injection nozzles
US3247967A (en) * 1963-04-17 1966-04-26 Bendix Corp Flow divider valve
FR1490068A (fr) * 1966-08-19 1967-07-28 Gen Electric Distributeur de carburant à gicleurs multiples
FR1536611A (fr) * 1966-09-09 1968-08-16 Philips Nv Procédé pour l'oxydation anodique de l'aluminium et de ses alliages
FR2186601A1 (fr) * 1972-05-31 1974-01-11 Gen Electric

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3159971A (en) * 1961-02-24 1964-12-08 Parker Hannifin Corp Resilient nozzle mount
US4157012A (en) * 1977-03-24 1979-06-05 General Electric Company Gaseous fuel delivery system
SE411791B (sv) * 1977-05-20 1980-02-04 Alfa Laval Ab Reglerventil innefattande en membranvegg och en vid membranveggens centrala del fest ventilkropp
US4194358A (en) * 1977-12-15 1980-03-25 General Electric Company Double annular combustor configuration

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2590853A (en) * 1945-10-16 1952-04-01 Gen Electric Liquid fuel metering and spraying system
FR945035A (fr) * 1946-02-25 1949-04-22 Lucas Ltd Joseph Perfectionnements aux dispositifs de réglage de combustible liquide
FR1028959A (fr) * 1949-11-14 1953-05-29 Rolls Royce Perfectionnements aux appareillages d'alimentation en combustible pour moteurs à turbine à gaz
US2724239A (en) * 1952-04-21 1955-11-22 Samuel S Fox Fuel flow distributing and manifold pressurizing valve for dual orifice fuel injection nozzles
US3247967A (en) * 1963-04-17 1966-04-26 Bendix Corp Flow divider valve
FR1490068A (fr) * 1966-08-19 1967-07-28 Gen Electric Distributeur de carburant à gicleurs multiples
FR1536611A (fr) * 1966-09-09 1968-08-16 Philips Nv Procédé pour l'oxydation anodique de l'aluminium et de ses alliages
FR2186601A1 (fr) * 1972-05-31 1974-01-11 Gen Electric

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5577386A (en) * 1994-06-20 1996-11-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. System for cooling a high power fuel injector of a dual injector
EP0689007A1 (fr) * 1994-06-22 1995-12-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Refroidissement de l'injecteur de décollage d'une chambre de combustion à deux têtes
EP0689006A1 (fr) 1994-06-22 1995-12-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Procédé et dispositif pour alimenter en carburant et refroidir l'injecteur de décollage d'une chambre de combustion à deux têtes
FR2721693A1 (fr) * 1994-06-22 1995-12-29 Snecma Procédé et dispositif pour alimenter en carburant et refroidir l'injecteur de décollage d'une chambre de combustion à deux têtes.
FR2721694A1 (fr) * 1994-06-22 1995-12-29 Snecma Refroidissement de l'injecteur de décollage d'une chambre de combustion à deux têtes.
US5568721A (en) * 1994-06-22 1996-10-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. System for supplying fuel to and cooling a fuel injector of a dual head combustion chamber
CN107023855A (zh) * 2017-05-25 2017-08-08 上海泛智能源装备有限公司 一种燃气轮机

Also Published As

Publication number Publication date
GB2036296A (en) 1980-06-25
DE2946393C2 (de) 1982-05-13
GB2036296B (en) 1982-12-01
DE2946393A1 (de) 1980-05-22
JPS5575537A (en) 1980-06-06
US4305255A (en) 1981-12-15
FR2441725B1 (fr) 1982-09-10

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Legal Events

Date Code Title Description
ST Notification of lapse