FR2349740B1 - - Google Patents

Info

Publication number
FR2349740B1
FR2349740B1 FR7712605A FR7712605A FR2349740B1 FR 2349740 B1 FR2349740 B1 FR 2349740B1 FR 7712605 A FR7712605 A FR 7712605A FR 7712605 A FR7712605 A FR 7712605A FR 2349740 B1 FR2349740 B1 FR 2349740B1
Authority
FR
France
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.)
Expired
Application number
FR7712605A
Other languages
French (fr)
Other versions
FR2349740A1 (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.)
Boeing Co
Original Assignee
Boeing 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 Boeing Co filed Critical Boeing Co
Publication of FR2349740A1 publication Critical patent/FR2349740A1/fr
Application granted granted Critical
Publication of FR2349740B1 publication Critical patent/FR2349740B1/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
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/545—Ducts
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
FR7712605A 1976-04-26 1977-04-26 Berceau de turboreacteur a double flux a portes de contournement de stators Granted FR2349740A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/679,946 US4086761A (en) 1976-04-26 1976-04-26 Stator bypass system for turbofan engine

Publications (2)

Publication Number Publication Date
FR2349740A1 FR2349740A1 (fr) 1977-11-25
FR2349740B1 true FR2349740B1 (US20030157376A1-20030821-M00001.png) 1980-02-01

Family

ID=24729032

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7712605A Granted FR2349740A1 (fr) 1976-04-26 1977-04-26 Berceau de turboreacteur a double flux a portes de contournement de stators

Country Status (6)

Country Link
US (1) US4086761A (US20030157376A1-20030821-M00001.png)
JP (1) JPS52148806A (US20030157376A1-20030821-M00001.png)
DE (1) DE2718693C3 (US20030157376A1-20030821-M00001.png)
FR (1) FR2349740A1 (US20030157376A1-20030821-M00001.png)
GB (1) GB1535681A (US20030157376A1-20030821-M00001.png)
IT (1) IT1073219B (US20030157376A1-20030821-M00001.png)

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US5694767A (en) * 1981-11-02 1997-12-09 General Electric Company Variable slot bypass injector system
US4463552A (en) * 1981-12-14 1984-08-07 United Technologies Corporation Combined surge bleed and dust removal system for a fan-jet engine
US4504030A (en) * 1982-12-06 1985-03-12 United Technologies Corporation Cooling means
FR2550821B1 (fr) * 1983-08-18 1985-11-08 Snecma Dispositif variateur du flux secondaire d'un turboreacteur multiflux
FR2569783B1 (fr) * 1984-09-06 1986-09-12 Snecma Structure d'anneau et dispositif de decharge de compresseur comportant cet anneau
FR2569785B1 (fr) * 1984-09-06 1986-09-12 Snecma Disposit
GB2194592B (en) * 1986-08-27 1990-07-04 Rolls Royce Plc Fluid outlet duct
US4825644A (en) * 1987-11-12 1989-05-02 United Technologies Corporation Ventilation system for a nacelle
GB2224080B (en) * 1988-10-22 1993-04-07 Rolls Royce Plc Fluid outlet duct
US5112191A (en) * 1989-04-11 1992-05-12 General Electric Company Rotating cowling
GB2261918B (en) * 1991-11-27 1994-09-28 Rolls Royce Plc Changeover valve
US5342167A (en) * 1992-10-09 1994-08-30 Airflow Research And Manufacturing Corporation Low noise fan
US5758488A (en) * 1993-05-11 1998-06-02 Roderick Thomson Core flow expansion chamber device system for reduction of jet turbine engine noise
DE4326799A1 (de) * 1993-08-10 1995-02-16 Abb Management Ag Vorrichtung zur Sekundärluftentnahme aus einem Axialverdichter
US5404713A (en) * 1993-10-04 1995-04-11 General Electric Company Spillage drag and infrared reducing flade engine
US5431533A (en) * 1993-10-15 1995-07-11 United Technologies Corporation Active vaned passage casing treatment
CA2133793A1 (en) * 1994-10-06 1996-04-07 William E. Carscallen Inter compressor duct variable geometry annular diffuser/bleed valve
US5505587A (en) * 1995-01-05 1996-04-09 Northrop Grumman Corporation RAM air turbine generating apparatus
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
DE10042933A1 (de) * 2000-08-31 2002-03-14 Rolls Royce Deutschland Vorrichtung zum Kühlen des Gehäuses einer Fluggasturbine
FR2823532B1 (fr) 2001-04-12 2003-07-18 Snecma Moteurs Systeme de decharge pour turboreacteur ou turbopropulseur a commande simplifiee
FR2831608B1 (fr) 2001-10-31 2004-01-02 Snecma Moteurs Dispositif de decharge dans un turbo reacteur a double flux
GB2383093A (en) * 2001-12-12 2003-06-18 Rolls Royce Plc Flow turbulence reduction downstream of diverted flow
JP4893110B2 (ja) 2006-05-31 2012-03-07 株式会社Ｉｈｉ 軸流流体装置
US8256225B2 (en) * 2006-10-12 2012-09-04 United Technologies Corporation Gas turbine engine with a variable exit area fan nozzle, nacelle assembly of such a engine, and corresponding operating method
US7850419B2 (en) * 2006-11-30 2010-12-14 Pratt & Whitney Canada Corp. Bleed valve actuating system for a gas turbine engine
US20080258016A1 (en) * 2007-04-23 2008-10-23 Gukeisen Robert L Nacelle assembly without lower bi-fi splitter
WO2008147260A1 (en) * 2007-05-25 2008-12-04 Volvo Aero Corporation A device for moving a plurality of hatches in a gas turbine engine
US7871242B2 (en) * 2007-05-31 2011-01-18 United Technologies Corporation Single actuator controlled rotational flow balance system
US7966827B2 (en) * 2007-05-31 2011-06-28 United Technologies Corporation Gas turbine engine with fan variable area nozzle having a rotational valve system
US8082726B2 (en) * 2007-06-26 2011-12-27 United Technologies Corporation Tangential anti-swirl air supply
US9701415B2 (en) 2007-08-23 2017-07-11 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US10167813B2 (en) 2007-08-23 2019-01-01 United Technologies Corporation Gas turbine engine with fan variable area nozzle to reduce fan instability
US9494084B2 (en) 2007-08-23 2016-11-15 United Technologies Corporation Gas turbine engine with fan variable area nozzle for low fan pressure ratio
DE102010023702A1 (de) * 2010-06-14 2011-12-15 Rolls-Royce Deutschland Ltd & Co Kg Fluggasturbine mit Zapfluftführung
FR2970302B1 (fr) * 2011-01-11 2015-07-17 Snecma Turboreacteur a double flux
US8919784B2 (en) * 2011-06-29 2014-12-30 United Technologies Corporation Fan duct blocker actuation tab seal
FR2982904B1 (fr) * 2011-11-18 2015-01-30 Snecma Moyeu de carter pour turboreacteur d'aeronef comprenant des moyens de commande de vannes de decharge ameliores
US20140216056A1 (en) * 2012-09-28 2014-08-07 United Technologies Corporation Heat exchange module for a turbine engine
US9920710B2 (en) 2013-05-07 2018-03-20 General Electric Company Multi-nozzle flow diverter for jet engine
US10400710B2 (en) 2013-05-07 2019-09-03 General Electric Company Secondary nozzle for jet engine
US10233867B2 (en) 2013-07-05 2019-03-19 United Technologies Corporation Gas turbine engine system for modulating flow of fan by-pass air and core engine air
US9657647B2 (en) * 2013-10-15 2017-05-23 The Boeing Company Methods and apparatus to adjust bleed ports on an aircraft engine
CN104675556B (zh) * 2014-12-26 2016-02-10 南京航空航天大学 叶尖喷气驱动风扇的大涵道比涡扇发动机
US9862482B2 (en) * 2015-09-04 2018-01-09 The Boeing Company Variable geometry flush boundary diverter
US10151217B2 (en) 2016-02-11 2018-12-11 General Electric Company Turbine frame cooling systems and methods of assembly for use in a gas turbine engine
FR3052806B1 (fr) * 2016-06-20 2018-07-13 Safran Aircraft Engines Procede et dispositif de test d'integrite d'un systeme de regulation de debit de fluide pour une turbomachine
FR3059367B1 (fr) * 2016-11-25 2018-11-23 Safran Aircraft Engines Turbomachine a double flux equipee d'un systeme de decharge
FR3059365B1 (fr) 2016-11-25 2018-11-23 Safran Aircraft Engines Turbomachine a double flux equipee d'un systeme de decharge
GB2580128B (en) * 2018-12-21 2021-12-01 Gkn Aerospace Sweden Ab Plenum resonance prevention arrangement
FR3095005B1 (fr) * 2019-04-09 2021-03-19 Safran Aircraft Engines Turbomachine pour un aeronef
CN114087088B (zh) * 2020-08-24 2023-05-30 中国航发商用航空发动机有限责任公司 航空发动机试验机匣和航空发动机试验系统
EP4123151A1 (en) * 2021-07-20 2023-01-25 Rolls-Royce plc Variable pitch fan thrust reverser
US20230212989A1 (en) * 2022-01-05 2023-07-06 General Electric Company Bleed valve assemblies
US20240044288A1 (en) * 2022-08-02 2024-02-08 Pratt & Whitney Canada Corp. Porous cover for a takeoff port of a gas turbine engine

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE879280C (de) * 1940-04-16 1953-06-11 Kuehnle Ag Axialgeblaese oder Axialpumpe
DE889506C (de) * 1940-09-25 1953-09-10 Versuchsanstalt Fuer Luftfahrt Stroemungsmaschine mit Grenzschichtabsaugung
FR1286886A (fr) * 1961-01-27 1962-03-09 Nord Aviation Dispositif d'inversion de poussée pour propulseurs comportant un turbo-réacteur àdouble flux
GB864519A (en) * 1958-08-05 1961-04-06 Rolls Royce Improved annular fluid control valve device
US3344606A (en) * 1961-09-27 1967-10-03 United Aircraft Corp Recover bleed air turbojet
FR1402436A (fr) * 1964-07-24 1965-06-11 Rolls Royce Perfectionnements aux machines à écoulement gazeux
BE756363A (fr) * 1969-09-30 1971-03-01 Gen Electric Systeme d'echappement pour compresseurs de moteurs a turbine a gaz
GB1291943A (en) * 1970-02-11 1972-10-04 Secr Defence Improvements in or relating to ducted fans
GB1342590A (en) * 1970-07-17 1974-01-03 Secr Defence Suppression of noise in gas turbine engines
GB1365491A (en) * 1971-01-02 1974-09-04 Dowty Rotol Ltd Gas turbine ducted fan engines and fans therefor
DE2247400C2 (de) * 1972-09-27 1975-01-16 Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Vorrichtung zum Abblasen von verdichteter Luft aus einem Verdichter eines Gasturbinenstrahltriebwerks
US3809490A (en) * 1973-05-02 1974-05-07 United Aircraft Corp Compressor surge sensor
US4012165A (en) * 1975-12-08 1977-03-15 United Technologies Corporation Fan structure

Also Published As

Publication number Publication date
DE2718693B2 (de) 1980-07-31
US4086761A (en) 1978-05-02
GB1535681A (en) 1978-12-13
IT1073219B (it) 1985-04-13
DE2718693A1 (de) 1977-11-10
JPS52148806A (en) 1977-12-10
FR2349740A1 (fr) 1977-11-25
DE2718693C3 (de) 1981-04-09

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Legal Events

Date Code Title Description
ST Notification of lapse