FR2661947A1 - Procede et structure pour faire fonctionner automatiquement une vanne de dilution dans un turboreacteur a double flux. - Google Patents

Procede et structure pour faire fonctionner automatiquement une vanne de dilution dans un turboreacteur a double flux. Download PDF

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Publication number
FR2661947A1
FR2661947A1 FR9016485A FR9016485A FR2661947A1 FR 2661947 A1 FR2661947 A1 FR 2661947A1 FR 9016485 A FR9016485 A FR 9016485A FR 9016485 A FR9016485 A FR 9016485A FR 2661947 A1 FR2661947 A1 FR 2661947A1
Authority
FR
France
Prior art keywords
channel
dilution
flap
flow
fluid
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.)
Withdrawn
Application number
FR9016485A
Other languages
English (en)
French (fr)
Inventor
Stransky Larry Wayne
Boehm Valentine Robert Jr
Phillips Michael Allen
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 FR2661947A1 publication Critical patent/FR2661947A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Sampling And Sample Adjustment (AREA)
FR9016485A 1990-05-11 1990-12-28 Procede et structure pour faire fonctionner automatiquement une vanne de dilution dans un turboreacteur a double flux. Withdrawn FR2661947A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/522,024 US5184461A (en) 1990-05-11 1990-05-11 Method and apparatus for automatic bypass operation

Publications (1)

Publication Number Publication Date
FR2661947A1 true FR2661947A1 (fr) 1991-11-15

Family

ID=24079129

Family Applications (1)

Application Number Title Priority Date Filing Date
FR9016485A Withdrawn FR2661947A1 (fr) 1990-05-11 1990-12-28 Procede et structure pour faire fonctionner automatiquement une vanne de dilution dans un turboreacteur a double flux.

Country Status (6)

Country Link
US (1) US5184461A (OSRAM)
JP (1) JPH04228837A (OSRAM)
CA (1) CA2034465A1 (OSRAM)
DE (1) DE4100404A1 (OSRAM)
FR (1) FR2661947A1 (OSRAM)
GB (1) GB2243876A (OSRAM)

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US5048286A (en) * 1990-06-29 1991-09-17 General Electric Company Bypass valve door
US5287697A (en) * 1992-01-02 1994-02-22 General Electric Company Variable area bypass injector seal
US5315821A (en) * 1993-02-05 1994-05-31 General Electric Company Aircraft bypass turbofan engine thrust reverser
US5505587A (en) * 1995-01-05 1996-04-09 Northrop Grumman Corporation RAM air turbine generating apparatus
US6438941B1 (en) 2001-04-26 2002-08-27 General Electric Company Bifurcated splitter for variable bleed flow
GB0504272D0 (en) * 2005-03-02 2005-04-06 Rolls Royce Plc A turbine engine and a method of operating a turbine engine
US20060196164A1 (en) * 2005-03-03 2006-09-07 Donohue Thomas F Dual mode turbo engine
US7464536B2 (en) * 2005-07-07 2008-12-16 General Electric Company Methods and apparatus for assembling gas turbine engines
US7870741B2 (en) * 2007-05-25 2011-01-18 General Electric Company Turbine engine valve assembly and method of assembling the same
US7837436B2 (en) * 2007-05-25 2010-11-23 General Electric Company Method and apparatus for regulating fluid flow through a turbine engine
US8578716B2 (en) * 2008-03-22 2013-11-12 United Technologies Corporation Valve system for a gas turbine engine
US8800259B2 (en) * 2008-09-22 2014-08-12 Rolls-Royce North American Technologies, Inc. Thrust vector system
FR2937679B1 (fr) * 2008-10-24 2010-12-03 Snecma Dispositif de prelevement d'air de refroidissement dans une turbomachine
FR2955646B1 (fr) * 2010-01-26 2012-08-24 Ge Energy Products France Snc Systeme et procede de ventilation pour turbine
US9091215B2 (en) * 2011-06-28 2015-07-28 General Electric Company System for ventilating a gas turbine enclosure
US10125724B2 (en) 2012-01-17 2018-11-13 United Technologies Corporation Start system for gas turbine engines
US9371739B2 (en) * 2013-01-04 2016-06-21 Raytheon Company Power producing device with control mechanism
US9206912B2 (en) * 2013-01-23 2015-12-08 The Boeing Company Dual door fan air modulating valve
US9920710B2 (en) * 2013-05-07 2018-03-20 General Electric Company Multi-nozzle flow diverter for jet engine
US9915267B2 (en) * 2015-06-08 2018-03-13 Air Distribution Technologies Ip, Llc Fan inlet recirculation guide vanes
CN105545522B (zh) * 2015-12-29 2017-04-12 中国航空工业集团公司沈阳发动机设计研究所 一种模式选择阀门组件
DE102023127182A1 (de) * 2023-10-05 2025-04-10 MTU Aero Engines AG Strömungskanalvorrichtung

Citations (5)

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US3019600A (en) * 1959-08-03 1962-02-06 United Aircraft Corp Turbo-fan engine thrust reverser
GB2046363A (en) * 1979-03-30 1980-11-12 Gen Electric Turbomachine cooling air control
GB2172056A (en) * 1985-03-04 1986-09-10 Gen Electric Means and method for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas turbine engine
US4781214A (en) * 1987-03-09 1988-11-01 Scaramucci John P Swing check valve disc
EP0374004A1 (fr) * 1988-12-15 1990-06-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Vanne de décharge de compresseur de turboréacteur

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US3367579A (en) * 1965-12-08 1968-02-06 Air Force Usa Supersonic convergent-divergent jet exhaust nozzle
DE1944472A1 (de) * 1969-09-02 1971-03-18 Messerschmitt Boelkow Blohm Doppelwandige Verschlussklappe fuer eine Hilfseinlaufoeffnung eines Strahltriebwerkes
GB1360238A (en) * 1972-07-17 1974-07-17 Secr Defence Ducted fan gas turbine power plants
FR2260697B1 (OSRAM) * 1974-02-11 1976-06-25 Snecma
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US4175384A (en) * 1977-08-02 1979-11-27 General Electric Company Individual bypass injector valves for a double bypass variable cycle turbofan engine
DE2740904A1 (de) * 1977-09-10 1979-03-22 Motoren Turbinen Union Vorrichtung zur betaetigung von absperrorganen in gasturbinentriebwerken, insbesondere gasturbinenstrahltriebwerken
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DE2834860A1 (de) * 1978-08-09 1980-03-13 Motoren Turbinen Union Verstellbarer stroemungsteiler fuer stroemungsmaschinen, insbesondere gasturbinenstrahltriebwerke
SU956354A1 (ru) * 1978-12-28 1982-09-07 Предприятие П/Я В-2481 Устройство дл защиты силовой установки самолета от попадани посторонних предметов
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US4715779A (en) * 1984-12-13 1987-12-29 United Technologies Corporation Bleed valve for axial flow compressor
US4813229A (en) * 1985-03-04 1989-03-21 General Electric Company Method for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas
GB2192940B (en) * 1986-07-25 1990-10-31 Rolls Royce Plc A variable area aircraft air intake
US4825644A (en) * 1987-11-12 1989-05-02 United Technologies Corporation Ventilation system for a nacelle

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3019600A (en) * 1959-08-03 1962-02-06 United Aircraft Corp Turbo-fan engine thrust reverser
GB2046363A (en) * 1979-03-30 1980-11-12 Gen Electric Turbomachine cooling air control
GB2172056A (en) * 1985-03-04 1986-09-10 Gen Electric Means and method for controlling augmentor liner coolant flow pressure in a mixed flow, variable cycle gas turbine engine
US4781214A (en) * 1987-03-09 1988-11-01 Scaramucci John P Swing check valve disc
EP0374004A1 (fr) * 1988-12-15 1990-06-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Vanne de décharge de compresseur de turboréacteur

Also Published As

Publication number Publication date
DE4100404C2 (OSRAM) 1993-08-12
GB2243876A (en) 1991-11-13
GB9100511D0 (en) 1991-02-20
JPH04228837A (ja) 1992-08-18
US5184461A (en) 1993-02-09
DE4100404A1 (de) 1991-11-14
CA2034465A1 (en) 1991-11-12

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