FR2424999A1 - Ensemble de deux turbosoufflantes interconnectees et procede pour leur fonctionnement - Google Patents

Ensemble de deux turbosoufflantes interconnectees et procede pour leur fonctionnement

Info

Publication number
FR2424999A1
FR2424999A1 FR7911014A FR7911014A FR2424999A1 FR 2424999 A1 FR2424999 A1 FR 2424999A1 FR 7911014 A FR7911014 A FR 7911014A FR 7911014 A FR7911014 A FR 7911014A FR 2424999 A1 FR2424999 A1 FR 2424999A1
Authority
FR
France
Prior art keywords
engine
blower
turbine
gas turbine
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.)
Withdrawn
Application number
FR7911014A
Other languages
English (en)
Inventor
Rollin George Giffin Iii
Onofre Tama Manuel Castells
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 FR2424999A1 publication Critical patent/FR2424999A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/34—Blade mountings
    • F04D29/36—Blade mountings adjustable
    • F04D29/362—Blade mountings adjustable during rotation
    • 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
    • F02K3/12—Plants including a gas turbine driving a compressor or a ducted fan characterised by having more than one gas turbine
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)

Abstract

ENSEMBLE DANS LEQUEL, EN CAS DE PANNE D'UNE TURBINE A GAZ D'UNE DES TURBOSOUFFLANTES, LES DEUX SOUFFLANTES SONT ENTRAINEES PAR LA TURBINE A GAZ RESTANTE DONT LA CAPACITE DE SURALIMENTATION EST CONSERVEE. IL COMPREND UN PREMIER ET UN SECOND MOTEUR A TURBOSOUFFLANTE 10, POSSEDANT CHACUN UNE TURBINE A GAZ 12 ET UN SYSTEME A BASSE PRESSION COMPRENANT UNE SOUFFLANTE 26, UN CANAL DE DERIVATION 16 ET UNE TURBINE 31; UN ARBRE TRANSVERSAL INTERCONNECTANT LES SYSTEMES A BASSE PRESSION DE TELLE FACON QUE LA TURBINE DU PREMIER MOTEUR PEUT ENTRAINER LA SOUFFLANTE DU SECOND MOTEUR; DANS CE SECOND MOTEUR, UN DISPOSITIF 58 POUR DEBRAYER DE SA TURBINE SA SOUFFLANTE; ET DANS LE CANAL DE DERIVATION DE CE PREMIER MOTEUR, UN DISPOSITIF A FLUX VARIABLE 29 CAPABLE DE FAIRE VARIER LE FLUX D'AIR DANS LE CANAL DE DERIVATION SANS MODIFIER SENSIBLEMENT LE FLUX ENVOYE DANS SA TURBINE A GAZ ASSOCIEE. APPLICATION AUX AVIONS A DECOLLAGE ET ATTERRISSAGE VERTICAL.
FR7911014A 1978-05-01 1979-05-02 Ensemble de deux turbosoufflantes interconnectees et procede pour leur fonctionnement Withdrawn FR2424999A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/901,934 US4254619A (en) 1978-05-01 1978-05-01 Partial span inlet guide vane for cross-connected engines

Publications (1)

Publication Number Publication Date
FR2424999A1 true FR2424999A1 (fr) 1979-11-30

Family

ID=25415093

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7911014A Withdrawn FR2424999A1 (fr) 1978-05-01 1979-05-02 Ensemble de deux turbosoufflantes interconnectees et procede pour leur fonctionnement

Country Status (6)

Country Link
US (1) US4254619A (fr)
JP (1) JPS54158511A (fr)
DE (1) DE2917587A1 (fr)
FR (1) FR2424999A1 (fr)
GB (1) GB2019945A (fr)
IT (1) IT1113916B (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2526491A1 (fr) * 1982-05-04 1983-11-10 Snecma Dispositif de reglage de la perte de charge d'au moins un des flux dans un turboreacteur multiflux
FR2572136A1 (fr) * 1984-10-22 1986-04-25 Gen Electric Moteur a turbo soufflante a flux melange
FR2695960A1 (fr) * 1992-09-23 1994-03-25 Snecma Moteur à cycle variable pour un avion à décollage vertical.
WO2014023891A1 (fr) * 2012-08-09 2014-02-13 Snecma Turbomachine comportant une pluralité d'aubes radiales fixes montées en amont de la soufflante
US9879561B2 (en) 2012-08-09 2018-01-30 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US9885291B2 (en) 2012-08-09 2018-02-06 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan

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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
US4527388A (en) * 1982-07-12 1985-07-09 The Garrett Corporation Jet propulsion apparatus and methods
JPH0613855B2 (ja) * 1986-04-08 1994-02-23 三信工業株式会社 船舶用推進機の警告装置
US5683225A (en) * 1991-10-28 1997-11-04 General Electric Company Jet engine variable area turbine nozzle
US5281087A (en) * 1992-06-10 1994-01-25 General Electric Company Industrial gas turbine engine with dual panel variable vane assembly
US5890441A (en) * 1995-09-07 1999-04-06 Swinson Johnny Horizontal and vertical take off and landing unmanned aerial vehicle
GB2400411B (en) * 2003-04-10 2006-09-06 Rolls Royce Plc Turbofan arrangement
US20070018035A1 (en) * 2005-07-20 2007-01-25 Saiz Manuel M Lifting and Propulsion System For Aircraft With Vertical Take-Off and Landing
EP2074301B1 (fr) * 2006-10-12 2016-02-24 United Technologies Corporation Turboréacteur à double-flux avec une tuyère de poussée controlée pour décollage et atterrissage
US8015796B2 (en) * 2007-06-05 2011-09-13 United Technologies Corporation Gas turbine engine with dual fans driven about a central core axis
US20090212156A1 (en) * 2007-09-06 2009-08-27 Honeywell International, Inc. Aircraft engine system with gearbox unit
DE102008011643A1 (de) * 2008-02-28 2009-09-03 Rolls-Royce Deutschland Ltd & Co Kg Flugzeugantriebseinheit mit Multi-Fan-Ausgestaltung
DE102009009715A1 (de) * 2009-02-19 2010-08-26 Mtu Aero Engines Gmbh Verdichter mit Leitgitter mit radial veränderlicher Abströmung
GB201112577D0 (en) * 2011-07-22 2011-08-31 Rolls Royce Plc Method of inhibiting ice accretion within a turbine engine and control system therefor
US8708274B2 (en) * 2011-09-09 2014-04-29 United Technologies Corporation Transverse mounted gas turbine engine
US9267438B2 (en) 2011-10-11 2016-02-23 Pratt & Whitney Canada Corp. Starting of aircraft engine
US9188083B2 (en) * 2011-10-28 2015-11-17 United Technologies Corporation Gas turbine engine with auxiliary fan
US9429077B2 (en) 2011-12-06 2016-08-30 Pratt & Whitney Canada Corp. Multiple turboshaft engine control method and system for helicopters
US9352843B2 (en) 2012-12-31 2016-05-31 United Technologies Corporation Gas turbine engine having fan rotor driven by turbine exhaust and with a bypass
US10145301B2 (en) 2014-09-23 2018-12-04 Pratt & Whitney Canada Corp. Gas turbine engine inlet
US10378554B2 (en) * 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane
FR3033007B1 (fr) * 2015-02-19 2018-07-13 Safran Aircraft Engines Dispositif pour le reglage individuel d'une pluralite d'aubes radiales fixes a calage variable dans une turbomachine
US9957807B2 (en) 2015-04-23 2018-05-01 Pratt & Whitney Canada Corp. Rotor assembly with scoop
US9938848B2 (en) 2015-04-23 2018-04-10 Pratt & Whitney Canada Corp. Rotor assembly with wear member
FR3039228B1 (fr) * 2015-07-22 2020-01-03 Safran Aircraft Engines Aeronef comprenant un propulseur arriere carene avec stator d'entree comprenant une fonction soufflage
US9915149B2 (en) 2015-08-27 2018-03-13 Rolls-Royce North American Technologies Inc. System and method for a fluidic barrier on the low pressure side of a fan blade
US10280872B2 (en) 2015-08-27 2019-05-07 Rolls-Royce North American Technologies Inc. System and method for a fluidic barrier from the upstream splitter
US20170058831A1 (en) * 2015-08-27 2017-03-02 William Barry Bryan Gas turbine engine having radially-split inlet guide vanes
US10233869B2 (en) * 2015-08-27 2019-03-19 Rolls Royce North American Technologies Inc. System and method for creating a fluidic barrier from the leading edge of a fan blade
US10125622B2 (en) 2015-08-27 2018-11-13 Rolls-Royce North American Technologies Inc. Splayed inlet guide vanes
US10267159B2 (en) * 2015-08-27 2019-04-23 Rolls-Royce North America Technologies Inc. System and method for creating a fluidic barrier with vortices from the upstream splitter
US20170057649A1 (en) 2015-08-27 2017-03-02 Edward C. Rice Integrated aircraft propulsion system
US10718221B2 (en) 2015-08-27 2020-07-21 Rolls Royce North American Technologies Inc. Morphing vane
US9976514B2 (en) 2015-08-27 2018-05-22 Rolls-Royce North American Technologies, Inc. Propulsive force vectoring
US10267160B2 (en) 2015-08-27 2019-04-23 Rolls-Royce North American Technologies Inc. Methods of creating fluidic barriers in turbine engines
US10421554B2 (en) * 2015-10-05 2019-09-24 United Technologies Corporation Double propulsor imbedded in aircraft tail with single core engine
FR3043723B1 (fr) * 2015-11-13 2017-11-24 Snecma Ensemble de propulsion d'un aeronef comportant un generateur de gaz, deux soufflantes deportees et une manche d'entree d'air
US10344711B2 (en) * 2016-01-11 2019-07-09 Rolls-Royce Corporation System and method of alleviating blade flutter
US10724540B2 (en) 2016-12-06 2020-07-28 Pratt & Whitney Canada Corp. Stator for a gas turbine engine fan
US10690146B2 (en) 2017-01-05 2020-06-23 Pratt & Whitney Canada Corp. Turbofan nacelle assembly with flow disruptor
US10654577B2 (en) 2017-02-22 2020-05-19 General Electric Company Rainbow flowpath low pressure turbine rotor assembly
US11421627B2 (en) 2017-02-22 2022-08-23 General Electric Company Aircraft and direct drive engine under wing installation
US10414509B2 (en) 2017-02-23 2019-09-17 United Technologies Corporation Propulsor mounting for advanced body aircraft
US10815886B2 (en) * 2017-06-16 2020-10-27 General Electric Company High tip speed gas turbine engine
US10724435B2 (en) * 2017-06-16 2020-07-28 General Electric Co. Inlet pre-swirl gas turbine engine
US10794396B2 (en) 2017-06-16 2020-10-06 General Electric Company Inlet pre-swirl gas turbine engine
US10711797B2 (en) * 2017-06-16 2020-07-14 General Electric Company Inlet pre-swirl gas turbine engine
US10465539B2 (en) * 2017-08-04 2019-11-05 Pratt & Whitney Canada Corp. Rotor casing
FR3074847B1 (fr) * 2017-12-13 2020-09-04 Safran Aircraft Engines Module de soufflante
FR3095240B1 (fr) * 2019-04-17 2021-06-25 Safran Aircraft Engines Entrée d’air de nacelle de turboréacteur comprenant des aubes de redresseur
US11428160B2 (en) 2020-12-31 2022-08-30 General Electric Company Gas turbine engine with interdigitated turbine and gear assembly
CN112727635B (zh) * 2020-12-31 2022-04-26 中国航空发动机研究院 一种双外涵发动机
FR3126453A1 (fr) * 2021-08-25 2023-03-03 Safran Aircraft Engines Turboréacteur à aubes de guidage d’entrée
US11725526B1 (en) 2022-03-08 2023-08-15 General Electric Company Turbofan engine having nacelle with non-annular inlet

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US2503006A (en) * 1945-04-24 1950-04-04 Edward A Stalker Gas turbine engine with controllable auxiliary jet
GB1195961A (en) * 1966-12-05 1970-06-24 Rolls Royce Variable Pitch Aerofoil Blades.
US3449914A (en) * 1967-12-21 1969-06-17 United Aircraft Corp Variable flow turbofan engine
GB1309721A (en) * 1971-01-08 1973-03-14 Secr Defence Fan
US4112677A (en) * 1977-01-31 1978-09-12 Avco Corporation Thrust spoiler for turbofan engine
US4116405A (en) * 1977-03-28 1978-09-26 Grumman Aerospace Corporation Airplane

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2526491A1 (fr) * 1982-05-04 1983-11-10 Snecma Dispositif de reglage de la perte de charge d'au moins un des flux dans un turboreacteur multiflux
EP0094296A1 (fr) * 1982-05-04 1983-11-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Dispositif de réglage de la perte de charge d'au moins un des flux dans un turboréacteur multiflux
FR2572136A1 (fr) * 1984-10-22 1986-04-25 Gen Electric Moteur a turbo soufflante a flux melange
FR2695960A1 (fr) * 1992-09-23 1994-03-25 Snecma Moteur à cycle variable pour un avion à décollage vertical.
WO2014023891A1 (fr) * 2012-08-09 2014-02-13 Snecma Turbomachine comportant une pluralité d'aubes radiales fixes montées en amont de la soufflante
FR2994452A1 (fr) * 2012-08-09 2014-02-14 Snecma Turbomachine comportant une pluralite d'aubes radiales fixes montees en amont de la soufflante
US9835044B2 (en) 2012-08-09 2017-12-05 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US9879561B2 (en) 2012-08-09 2018-01-30 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US9885291B2 (en) 2012-08-09 2018-02-06 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan

Also Published As

Publication number Publication date
GB2019945A (en) 1979-11-07
IT7922194A0 (it) 1979-04-27
US4254619A (en) 1981-03-10
IT1113916B (it) 1986-01-27
JPS54158511A (en) 1979-12-14
DE2917587A1 (de) 1979-11-08

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Legal Events

Date Code Title Description
ST Notification of lapse