CA1029201A - Groupe ajutage et adduction auxiliaire pour moteur a turbine a gaz - Google Patents

Groupe ajutage et adduction auxiliaire pour moteur a turbine a gaz

Info

Publication number
CA1029201A
CA1029201A CA226,881A CA226881A CA1029201A CA 1029201 A CA1029201 A CA 1029201A CA 226881 A CA226881 A CA 226881A CA 1029201 A CA1029201 A CA 1029201A
Authority
CA
Canada
Prior art keywords
nozzle
gas turbine
turbine engine
auxiliary inlet
inlet arrangement
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.)
Expired
Application number
CA226,881A
Other languages
English (en)
Inventor
Augustus M. Helmintoller (Jr.)
Robert G. Beavers
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
Application granted granted Critical
Publication of CA1029201A publication Critical patent/CA1029201A/fr
Expired 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
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/66—Reversing fan flow using reversing fan blades

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
CA226,881A 1974-06-12 1975-05-14 Groupe ajutage et adduction auxiliaire pour moteur a turbine a gaz Expired CA1029201A (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US478702A US3897001A (en) 1974-06-12 1974-06-12 Nozzle and auxiliary inlet arrangement for gas turbine engine

Publications (1)

Publication Number Publication Date
CA1029201A true CA1029201A (fr) 1978-04-11

Family

ID=23901034

Family Applications (1)

Application Number Title Priority Date Filing Date
CA226,881A Expired CA1029201A (fr) 1974-06-12 1975-05-14 Groupe ajutage et adduction auxiliaire pour moteur a turbine a gaz

Country Status (2)

Country Link
US (1) US3897001A (fr)
CA (1) CA1029201A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2108806A1 (fr) 2008-04-10 2009-10-14 United Technologies Corporation Systèmes de moteur à turbine à gaz impliquant des buses variables avec des portes coulissantes

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4214703A (en) * 1979-03-23 1980-07-29 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Aircraft engine nozzle
US4410150A (en) * 1980-03-03 1983-10-18 General Electric Company Drag-reducing nacelle
DE3127257A1 (de) * 1981-07-10 1983-01-27 Vereinigte Flugtechnische Werke Gmbh, 2800 Bremen "verfahren zur verminderung des induzierten widestandes eines auftriebserzeugenden tragfluegels sowie vorrichtung zu seiner durchfuehrung"
US4860537A (en) * 1986-08-29 1989-08-29 Brandt, Inc. High bypass ratio counterrotating gearless front fan engine
US4790133A (en) * 1986-08-29 1988-12-13 General Electric Company High bypass ratio counterrotating turbofan engine
GB2198999B (en) * 1986-12-17 1990-08-29 Rolls Royce Plc Fluid propulsion engine with flow exit control device
FR2669679B1 (fr) * 1990-11-28 1994-04-29 Sud Ouest Conception Aeronauti Tuyere d'ejection de gaz pour moteur a reaction et moteur a reaction equipe d'une telle tuyere, en particulier moteur du type a flux separes.
DE4222947C2 (de) * 1992-07-11 1995-02-02 Deutsche Aerospace Strahltriebwerk
US5315821A (en) * 1993-02-05 1994-05-31 General Electric Company Aircraft bypass turbofan engine thrust reverser
GB2303179A (en) * 1995-07-08 1997-02-12 Rolls Royce Plc Vertical thrust gas turbine engine
GB2308866B (en) * 1996-01-04 1999-09-08 Rolls Royce Plc Ducted fan gas turbine engine with secondary duct
US6178740B1 (en) * 1999-02-25 2001-01-30 The Boeing Company Turbo fan engine nacelle exhaust system with concave primary nozzle plug
GB2430920B (en) * 2000-06-05 2007-10-24 Rolls Royce Plc Shrouded nozzle arrangement
US6763653B2 (en) * 2002-09-24 2004-07-20 General Electric Company Counter rotating fan aircraft gas turbine engine with aft booster
GB0603285D0 (en) * 2006-02-18 2006-03-29 Rolls Royce Plc A gas turbine engine
GB0618072D0 (en) 2006-09-14 2006-10-25 Rolls Royce Plc Aeroengine nozzle
US20100095650A1 (en) * 2006-10-12 2010-04-22 Schafer Bradley C Translating core cowl for a gas turbine engine
US7681399B2 (en) * 2006-11-14 2010-03-23 General Electric Company Turbofan engine cowl assembly and method of operating the same
US7886518B2 (en) * 2006-11-14 2011-02-15 General Electric Company Turbofan engine cowl assembly and method of operating the same
US8002520B2 (en) * 2007-01-17 2011-08-23 United Technologies Corporation Core reflex nozzle for turbofan engine
FR2916737B1 (fr) * 2007-06-01 2010-05-28 Airbus France Ensemble moteur pour aeronef a nacelle coulissante.
US8667802B2 (en) * 2010-05-06 2014-03-11 Spirit Aerosystems, Inc. Variable fan duct nozzle translatable core/inner cowl including two overlapping portions made of different materials
US10041442B2 (en) * 2010-06-11 2018-08-07 United Technologies Corporation Variable area fan nozzle
FR2972224B1 (fr) * 2011-03-04 2018-04-20 Safran Aircraft Engines Tuyere avec noyau aval presentant une forte courbure
US10502160B2 (en) * 2016-02-09 2019-12-10 General Electric Company Reverse thrust engine
FR3057620B1 (fr) 2016-10-18 2020-07-31 Safran Aircraft Engines Ensemble propulsif comprenant un conduit d'alimentation du generateur de gaz dans un carter inter-veine
US9926883B1 (en) * 2017-02-11 2018-03-27 Florida Turbine Technologies, Inc. Gas turbine engine with axial flow fan with twin stream impeller and variable area bypass nozzle

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3041823A (en) * 1952-09-18 1962-07-03 Snecma Control for varying the cross-sectional area of a nozzle
GB834907A (en) * 1956-10-23 1960-05-11 Rolls Royce Improvements in or relating to jet propulsion nozzles
US3002341A (en) * 1957-12-31 1961-10-03 Boeing Co Jet engine noise suppression nozzles
US2943444A (en) * 1958-04-28 1960-07-05 Ryan Aeronautical Co Combination thrust augmenter, sound suppressor and thrust reverser for jet engines
NL262125A (fr) * 1960-04-01
US3374631A (en) * 1965-08-16 1968-03-26 Mcdonnell Aircraft Corp Combination subsonic and supersonic propulsion system and apparatus
US3598319A (en) * 1969-07-14 1971-08-10 Gen Electric Propulsion nozzles
US3667680A (en) * 1970-04-24 1972-06-06 Boeing Co Jet engine exhaust nozzle system
US3807639A (en) * 1973-05-02 1974-04-30 Snecma Variable-geometry nozzles for jet propulsion engines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2108806A1 (fr) 2008-04-10 2009-10-14 United Technologies Corporation Systèmes de moteur à turbine à gaz impliquant des buses variables avec des portes coulissantes
US8356483B2 (en) 2008-04-10 2013-01-22 United Technologies Corp Gas turbine engine systems involving variable nozzles with sliding doors

Also Published As

Publication number Publication date
US3897001A (en) 1975-07-29

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