FR2398891A1 - Turbomachine a cycle de fonctionnement regule - Google Patents

Turbomachine a cycle de fonctionnement regule

Info

Publication number
FR2398891A1
FR2398891A1 FR7821666A FR7821666A FR2398891A1 FR 2398891 A1 FR2398891 A1 FR 2398891A1 FR 7821666 A FR7821666 A FR 7821666A FR 7821666 A FR7821666 A FR 7821666A FR 2398891 A1 FR2398891 A1 FR 2398891A1
Authority
FR
France
Prior art keywords
turbomachine
operating cycle
compressor
combustion chamber
bypass channel
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
FR7821666A
Other languages
English (en)
Other versions
FR2398891B1 (fr
Inventor
Arthur Paul Adamson
Elmore Verne Sprunger
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of FR2398891A1 publication Critical patent/FR2398891A1/fr
Application granted granted Critical
Publication of FR2398891B1 publication Critical patent/FR2398891B1/fr
Granted legal-status Critical Current

Links

Classifications

    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
    • F02C6/003—Gas-turbine plants with heaters between turbine stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof

Abstract

Turbomachine capable de faire décoller et atterrir à la verticale un avion et également capable de fonctionner avec un bon rendement en régimes de croisière et d'attente. Elle comprend, un canal de dérivation 15 contigu à la chambre de combustion 17 et communiquant par fluide avec le compresseur 27; et un mélangeur 34, disposé en partie dans ce canal de dérivation, pour recevoir une partie d'air relativement froid issu du compresseur et une partie d'air relativement chaud qui sort de la chambre de combustion, et délivrer un fluide mélangé à la turbine aval 32. Application aux avions ADAV.
FR7821666A 1977-07-25 1978-07-21 Turbomachine a cycle de fonctionnement regule Granted FR2398891A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/818,473 US4222235A (en) 1977-07-25 1977-07-25 Variable cycle engine

Publications (2)

Publication Number Publication Date
FR2398891A1 true FR2398891A1 (fr) 1979-02-23
FR2398891B1 FR2398891B1 (fr) 1985-04-19

Family

ID=25225620

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7821666A Granted FR2398891A1 (fr) 1977-07-25 1978-07-21 Turbomachine a cycle de fonctionnement regule

Country Status (8)

Country Link
US (1) US4222235A (fr)
JP (1) JPS5440912A (fr)
AU (1) AU519600B2 (fr)
DE (1) DE2831802A1 (fr)
FR (1) FR2398891A1 (fr)
GB (1) GB1602699A (fr)
IL (1) IL54895A (fr)
IT (1) IT1097388B (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0255796A2 (fr) * 1986-08-04 1988-02-10 United Technologies Corporation Tuyère pour un réacteur d'avion
EP2930330A1 (fr) * 2014-04-09 2015-10-14 Rolls-Royce plc Moteur à turbine à gaz
FR3056556A1 (fr) * 2016-09-29 2018-03-30 Safran Aircraft Engines Aeronef a turbomachine integree au fuselage arriere comportant une helice entourant un carter d'echappement

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ZA801724B (en) * 1979-04-01 1981-03-25 Stamicarbon Catalytic titanium compound,process for the manufacture thereof,and process for the polymerization of lakenes-1 with application of such a titanium component
US4446696A (en) * 1981-06-29 1984-05-08 General Electric Company Compound propulsor
US4791783A (en) * 1981-11-27 1988-12-20 General Electric Company Convertible aircraft engine
US4569199A (en) * 1982-09-29 1986-02-11 The Boeing Company Turboprop engine and method of operating the same
US5694768A (en) * 1990-02-23 1997-12-09 General Electric Company Variable cycle turbofan-ramjet engine
US5381655A (en) * 1993-05-10 1995-01-17 General Electric Company Admission mixing duct assembly
GB2307008A (en) * 1995-11-13 1997-05-14 Fred Moseley Gas turbine engine with two stage combustion
CN1105827C (zh) * 1995-12-20 2003-04-16 谢逢申 移出式超扇发动机
US5809772A (en) * 1996-03-29 1998-09-22 General Electric Company Turbofan engine with a core driven supercharged bypass duct
US5806303A (en) * 1996-03-29 1998-09-15 General Electric Company Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle
GB2313580B (en) * 1996-05-31 2000-02-23 Astovl Limited An aircraft power plant
US6385959B1 (en) 1999-08-24 2002-05-14 MONTOYA CéSAR AGUILERA Gas turbine engine with increased fuel efficiency and method for accomplishing the same
FR2826056B1 (fr) 2001-06-14 2003-12-19 Snecma Moteurs Dispositif de propulsion a cycle variable par transmission mecanique pour avion supersonique
US6837038B2 (en) * 2001-10-16 2005-01-04 United Technologies Corporation Variable cycle boost propulsor
US6792745B2 (en) * 2002-08-09 2004-09-21 The Boeing Company High bypass multi-fan engine
US7216475B2 (en) * 2003-11-21 2007-05-15 General Electric Company Aft FLADE engine
US7540450B2 (en) * 2004-07-16 2009-06-02 Pratt & Whitney Canada Corp. Aircraft propulsion system
US7134271B2 (en) * 2004-11-05 2006-11-14 General Electric Company Thrust vectoring aft FLADE engine
US8336289B2 (en) 2007-08-30 2012-12-25 United Technologies Corporation Gas turbine engine systems and related methods involving multiple gas turbine cores
DE102008011643A1 (de) 2008-02-28 2009-09-03 Rolls-Royce Deutschland Ltd & Co Kg Flugzeugantriebseinheit mit Multi-Fan-Ausgestaltung
US8387357B2 (en) * 2008-08-12 2013-03-05 Pratt & Whitney Recuperated bypass turbine engine
DE102008062813A1 (de) * 2008-12-23 2010-07-15 Rolls-Royce Deutschland Ltd & Co Kg Flugzeug mit einer Heck-Propeller-Triebwerksanordnung
US8382436B2 (en) 2009-01-06 2013-02-26 General Electric Company Non-integral turbine blade platforms and systems
US8262345B2 (en) 2009-02-06 2012-09-11 General Electric Company Ceramic matrix composite turbine engine
DE102010009477A1 (de) * 2010-02-26 2011-09-01 Rolls-Royce Deutschland Ltd & Co Kg Fluggasturbinenantrieb
US8701381B2 (en) * 2010-11-24 2014-04-22 Rolls-Royce Corporation Remote shaft driven open rotor propulsion system with electrical power generation
US9188083B2 (en) * 2011-10-28 2015-11-17 United Technologies Corporation Gas turbine engine with auxiliary fan
US8935912B2 (en) 2011-12-09 2015-01-20 United Technologies Corporation Gas turbine engine with variable overall pressure ratio
WO2013102113A2 (fr) 2011-12-30 2013-07-04 Rolls-Royce North American Technologies Inc. Moteurs à turbine à gaz comprenant des turbines à vitesse variable
FR2998012B1 (fr) * 2012-11-09 2018-07-13 Safran Helicopter Engines Assemblage de compression pour turbomachine
US10036317B2 (en) * 2013-03-05 2018-07-31 Industrial Turbine Company (Uk) Limited Capacity control of turbine by the use of a reheat combustor in multi shaft engine
US9624829B2 (en) 2013-03-05 2017-04-18 Industrial Turbine Company (Uk) Limited Cogen heat load matching through reheat and capacity match
US9752500B2 (en) * 2013-03-14 2017-09-05 Pratt & Whitney Canada Corp. Gas turbine engine with transmission and method of adjusting rotational speed
US20160363003A1 (en) * 2014-08-15 2016-12-15 Gen Electric Mechanical drive architectures with hybrid-type low-loss bearings and low-density materials
US20160047335A1 (en) * 2014-08-15 2016-02-18 General Electric Company Mechanical drive architectures with mono-type low-loss bearings and low-density materials
US10711702B2 (en) * 2015-08-18 2020-07-14 General Electric Company Mixed flow turbocore
FR3041934B1 (fr) * 2015-10-05 2018-07-13 Safran Aircraft Engines Ensemble de propulsion d'un aeronef
GB201518929D0 (en) * 2015-10-27 2015-12-09 Rolls Royce Plc Gas turbine engine
US10737801B2 (en) * 2016-10-31 2020-08-11 Rolls-Royce Corporation Fan module with rotatable vane ring power system
US10618667B2 (en) 2016-10-31 2020-04-14 Rolls-Royce Corporation Fan module with adjustable pitch blades and power system
GB201619960D0 (en) * 2016-11-25 2017-01-11 Rolls Royce Plc Gas turbine engine
GB201811401D0 (en) * 2018-07-12 2018-08-29 Rolls Royce Plc Supersonic aircraft propulsion installation
US11879415B2 (en) * 2020-07-13 2024-01-23 Rafael Mártinez-Vilanova Piñó Jet engine for aircraft
US11781479B2 (en) * 2021-05-06 2023-10-10 Rtx Corporation Turbofan gas turbine engine with combusted compressor bleed flow
CN113323769A (zh) * 2021-06-07 2021-08-31 北京航空航天大学 一种基于多涵道进气级间燃烧室的变循环发动机构型

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GB588097A (en) * 1944-04-22 1947-05-14 Power Jets Res & Dev Ltd Improvements in or relating to internal combustion turbine power plants
US3368352A (en) * 1965-01-30 1968-02-13 Rolls Royce Gas turbine engines
US3632224A (en) * 1970-03-02 1972-01-04 Gen Electric Adjustable-blade turbine
US3677012A (en) * 1962-05-31 1972-07-18 Gen Electric Composite cycle turbomachinery
DE2157611C (de) * 1971-11-20 1973-06-14 Motoren und Turbinen Union München GmbH, 8000 München Mehrstrom Gasturbinentriebwerk mit mehreren Wellen
GB1338499A (en) * 1971-12-03 1973-11-21 Rolls Royce Gas turbine engine
US3938328A (en) * 1971-11-08 1976-02-17 The Boeing Company Multicycle engine

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US2409177A (en) * 1942-04-01 1946-10-15 Allis Chalmers Mfg Co Jet propulsion apparatus
US2465099A (en) * 1943-11-20 1949-03-22 Allis Chalmers Mfg Co Propulsion means comprising an internal-combustion engine and a propulsive jet
US2619795A (en) * 1947-01-20 1952-12-02 Gen Electric Aircraft booster jet power unit
DE1077919B (de) * 1958-02-14 1960-03-17 Johann Endres Dr Ing Mehrkreis-Turbolader-Strahltriebwerk fuer Flugzeugantrieb mit getrennter Anordnung der Kreise
DE1081277B (de) * 1958-08-16 1960-05-05 Johann Endres Dr Ing Zweistrombrennkammer fuer Gasturbinen, insbesondere Gasturbinen-Strahltriebwerke
CH246174A (de) * 1959-06-24 1946-12-15 Eidg Flugzeugwerk Rückstosstriebwerk für Verkehrsmittel, insbesondere Flugzeuge.
US3016698A (en) * 1959-07-02 1962-01-16 Gen Motors Corp Bypass engine
US4025221A (en) * 1973-05-22 1977-05-24 United Turbine AB and Co., Kommanditbolag Automotive gas turbine power plant

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB588097A (en) * 1944-04-22 1947-05-14 Power Jets Res & Dev Ltd Improvements in or relating to internal combustion turbine power plants
US3677012A (en) * 1962-05-31 1972-07-18 Gen Electric Composite cycle turbomachinery
US3368352A (en) * 1965-01-30 1968-02-13 Rolls Royce Gas turbine engines
US3632224A (en) * 1970-03-02 1972-01-04 Gen Electric Adjustable-blade turbine
US3938328A (en) * 1971-11-08 1976-02-17 The Boeing Company Multicycle engine
DE2157611C (de) * 1971-11-20 1973-06-14 Motoren und Turbinen Union München GmbH, 8000 München Mehrstrom Gasturbinentriebwerk mit mehreren Wellen
GB1338499A (en) * 1971-12-03 1973-11-21 Rolls Royce Gas turbine engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0255796A2 (fr) * 1986-08-04 1988-02-10 United Technologies Corporation Tuyère pour un réacteur d'avion
EP0255796A3 (fr) * 1986-08-04 1989-04-26 United Technologies Corporation Tuyère pour un réacteur d'avion
EP2930330A1 (fr) * 2014-04-09 2015-10-14 Rolls-Royce plc Moteur à turbine à gaz
US10072572B2 (en) 2014-04-09 2018-09-11 Rolls-Royce Plc Gas turbine engine
FR3056556A1 (fr) * 2016-09-29 2018-03-30 Safran Aircraft Engines Aeronef a turbomachine integree au fuselage arriere comportant une helice entourant un carter d'echappement

Also Published As

Publication number Publication date
IL54895A (en) 1982-12-31
AU519600B2 (en) 1981-12-10
US4222235A (en) 1980-09-16
IT7826025A0 (it) 1978-07-24
DE2831802C2 (fr) 1990-07-05
IT1097388B (it) 1985-08-31
DE2831802A1 (de) 1979-02-15
JPS6153545B2 (fr) 1986-11-18
JPS5440912A (en) 1979-03-31
FR2398891B1 (fr) 1985-04-19
AU3710278A (en) 1979-12-20
GB1602699A (en) 1981-11-11

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