FR2445439A1 - Moteur a turbosoufflante perfectionne - Google Patents

Moteur a turbosoufflante perfectionne

Info

Publication number
FR2445439A1
FR2445439A1 FR7931676A FR7931676A FR2445439A1 FR 2445439 A1 FR2445439 A1 FR 2445439A1 FR 7931676 A FR7931676 A FR 7931676A FR 7931676 A FR7931676 A FR 7931676A FR 2445439 A1 FR2445439 A1 FR 2445439A1
Authority
FR
France
Prior art keywords
gas generator
engine
channel
blower
turbocharger engine
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
FR7931676A
Other languages
English (en)
Other versions
FR2445439B1 (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.)
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 FR2445439A1 publication Critical patent/FR2445439A1/fr
Application granted granted Critical
Publication of FR2445439B1 publication Critical patent/FR2445439B1/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
    • 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
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

Moteur comportant un dispositif permettant un redémarrage à l'air du moteur. Il comprend un générateur de gaz 13, 21, une soufflante 12, 14, 16 et un canal de dérivation 24 formé entre une nacelle 23 et le carter 26 du générateur de gaz, des aubes d'obturation 29 montées tout autour du canal 24 de façon à pouvoir être sélectivement déplacées entre une position ouverte qui permet l'écoulement non entravé du flux secondaire et une position fermée dans laquelle le canal 24 est complètement obturé de façon que la quasi-totalité de l'air refoulé par la soufflante s'écoule dans le générateur de gaz pour accroître le rapport des pressions de ce dernier et, notamment, faciliter son démarrage en vol après extinction. Application aux turbosoufflantes d'avion.
FR7931676A 1978-12-27 1979-12-26 Moteur a turbosoufflante perfectionne Expired FR2445439B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US05/973,766 US4292802A (en) 1978-12-27 1978-12-27 Method and apparatus for increasing compressor inlet pressure

Publications (2)

Publication Number Publication Date
FR2445439A1 true FR2445439A1 (fr) 1980-07-25
FR2445439B1 FR2445439B1 (fr) 1986-03-21

Family

ID=25521204

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7931676A Expired FR2445439B1 (fr) 1978-12-27 1979-12-26 Moteur a turbosoufflante perfectionne

Country Status (6)

Country Link
US (1) US4292802A (fr)
JP (1) JPS55104532A (fr)
DE (1) DE2951962A1 (fr)
FR (1) FR2445439B1 (fr)
GB (1) GB2038947B (fr)
IT (1) IT1126668B (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2936559A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine faisant partie de corps differents.
FR2936560A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par cremaillere
FR2936558A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison a barillet.
FR2936556A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine, notamment par guignols.
FR2936557A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison par pistes de guidage.
FR2936565A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine notamment, par guignols articules.
FR2936561A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came
EP2864613A1 (fr) * 2012-06-20 2015-04-29 United Technologies Corporation Mécanisme d'entraînement à quatre barres pour système de purge

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US4461145A (en) * 1982-10-08 1984-07-24 The United States Of America As Represented By The Secretary Of The Air Force Stall elimination and restart enhancement device
US5417055A (en) * 1988-06-28 1995-05-23 Rolls-Royce Plc Valve for diverting fluid flows in turbomachines
US5305599A (en) * 1991-04-10 1994-04-26 General Electric Company Pressure-ratio control of gas turbine engine
US5259187A (en) * 1993-02-05 1993-11-09 General Electric Company Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes
US6272838B1 (en) * 1999-02-25 2001-08-14 Alliedsignal, Inc. Method and apparatus for controlling the inlet duct leading to an auxiliary power unit
US6174130B1 (en) * 1999-06-30 2001-01-16 General Electric Company Movable shaft assembly
JP4599652B2 (ja) * 2000-04-17 2010-12-15 株式会社Ｉｈｉ ジェットエンジンの制御方法及び制御装置
US6471469B2 (en) 2000-11-30 2002-10-29 General Electric Company Methods and apparatus for sealing gas turbine engine variable nozzles
US7733818B2 (en) 2000-12-22 2010-06-08 Terahop Networks, Inc. Intelligent node communication using network formation messages in a mobile Ad hoc network
US6471471B1 (en) 2001-04-04 2002-10-29 General Electric Company Methods and apparatus for adjusting gas turbine engine variable vanes
US6786036B2 (en) * 2001-04-27 2004-09-07 Matthew Scott Kight Bimodal fan, heat exchanger and bypass air supercharging for piston or rotary driven turbine
US6682299B2 (en) 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement
US6658854B2 (en) 2002-02-01 2003-12-09 General Electric Co. Methods and apparatus for retaining gas turbine engine nozzle basesheets
US6745570B2 (en) 2002-02-01 2004-06-08 General Electric Co. Methods and apparatus for sealing gas turbine engine nozzles using a flap system
US6742324B2 (en) * 2002-09-13 2004-06-01 General Electric Company Methods and apparatus for supporting variable bypass valve systems
US7188481B2 (en) * 2002-10-30 2007-03-13 Honeywell International Inc. Adjustable damper actuator
GB0314123D0 (en) * 2003-06-18 2003-07-23 Rolls Royce Plc A gas turbine engine
EP1505263A1 (fr) * 2003-08-08 2005-02-09 Siemens Aktiengesellschaft Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération
US7302793B2 (en) * 2003-10-29 2007-12-04 General Electric Company Methods and apparatus to reduce turbine engine nozzle basesheet stresses
US7097421B2 (en) 2004-10-08 2006-08-29 United Technologies Corporation Vernier duct blocker
US7861533B2 (en) 2006-04-21 2011-01-04 Pratt & Whitney Canada Corp Relighting a turbofan engine
WO2008045068A1 (fr) 2006-10-12 2008-04-17 United Technologies Corporation Turboréacteur à double flux à tuyère de soufflante à géométrie variable et générateur de corps inférieur permettant une alimentation d'urgence et procédé d'alimentation d'urgence
EP2074298B1 (fr) * 2006-10-12 2013-03-13 United Technologies Corporation Redémarrage de moteur à turbine à gaz assisté par buse à section variable
US8313280B2 (en) * 2006-10-12 2012-11-20 United Technologies Corporation Method and device to avoid turbo instability in a gas turbine engine
US8347633B2 (en) * 2007-07-27 2013-01-08 United Technologies Corporation Gas turbine engine with variable geometry fan exit guide vane system
US8459035B2 (en) 2007-07-27 2013-06-11 United Technologies Corporation Gas turbine engine with low fan pressure ratio
US8511058B2 (en) * 2007-11-29 2013-08-20 United Technologies Corporation Convertible gas turbine propulsion system
US8084982B2 (en) 2008-11-18 2011-12-27 Honeywell International Inc. HVAC actuator with output torque compensation
US8961114B2 (en) 2010-11-22 2015-02-24 General Electric Company Integrated variable geometry flow restrictor and heat exchanger
US20130174534A1 (en) * 2012-01-05 2013-07-11 General Electric Company System and device for controlling fluid flow through a gas turbine exhaust
US20130192195A1 (en) 2012-01-31 2013-08-01 Eric J. Wehmeier Gas turbine engine with compressor inlet guide vane positioned for starting
FR2994452B1 (fr) * 2012-08-09 2016-12-23 Snecma Turbomachine comportant une pluralite d'aubes radiales fixes montees en amont de la soufflante
US20140137538A1 (en) * 2012-11-16 2014-05-22 United Technologies Corporation Fast Response Bypass Engine
ZA201309530B (en) * 2012-12-21 2014-07-30 Elta Group Africa (Pty) Ltd Axial flow fan construction
US10215070B2 (en) * 2015-06-29 2019-02-26 General Electric Company Power generation system exhaust cooling
US10060316B2 (en) 2015-06-29 2018-08-28 General Electric Company Power generation system exhaust cooling
US10030558B2 (en) 2015-06-29 2018-07-24 General Electric Company Power generation system exhaust cooling
US20160376909A1 (en) * 2015-06-29 2016-12-29 General Electric Company Power generation system exhaust cooling
US20170058831A1 (en) * 2015-08-27 2017-03-02 William Barry Bryan Gas turbine engine having radially-split inlet guide vanes
US11391298B2 (en) 2015-10-07 2022-07-19 General Electric Company Engine having variable pitch outlet guide vanes
US10316759B2 (en) 2016-05-31 2019-06-11 General Electric Company Power generation system exhaust cooling
US20180149114A1 (en) * 2016-11-30 2018-05-31 Sikorsky Aircraft Corporation Low infrared signature exhaust through active film cooling active mixing and acitve vane rotation
US10619649B2 (en) * 2017-04-04 2020-04-14 United Technologies Corporation Bellcrank assembly for gas turbine engine and method
US10174763B1 (en) * 2018-08-02 2019-01-08 Florida Turbine Technologies, Inc Variable pitch fan for gas turbine engine
US11286865B2 (en) * 2018-09-14 2022-03-29 Rolls-Royce North American Technologies Inc. Gas turbine engine with variable pitch fan and variable pitch compressor geometry
CN110685817A (zh) * 2019-10-11 2020-01-14 上海朝临动力科技有限公司 涡扇发动机及航空器

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US2873576A (en) * 1952-02-06 1959-02-17 Rolls Royce Means for controlling the rotational speed of the low-pressure compressor rotor of gas turbine engines
US2934895A (en) * 1958-09-15 1960-05-03 Curtiss Wright Corp Dual cycle engine distributor construction
FR1218064A (fr) * 1957-12-30 1960-05-09 Rolls Royce Perfectionnements aux moteurs à turbine à gaz
FR1535872A (fr) * 1966-12-22 1968-08-09 Gen Electric Système de commande pour compresseurs à écoulement axial en particulier pour les moteurs à turbines à gaz
FR2273954A1 (fr) * 1974-06-07 1976-01-02 United Technologies Corp Systeme de controle pour propulseur a ventilateur a pas variable et reversible
FR2405367A1 (fr) * 1977-10-07 1979-05-04 Mtu Muenchen Gmbh Turbine a gaz combinee pour engin volant ayant des caracteristiques v/stol

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FR2094662A5 (fr) * 1970-06-29 1972-02-04 Szydlowski Joseph
US3779665A (en) * 1972-09-22 1973-12-18 Gen Electric Combined variable angle stator and windmill control system
CA1020365A (en) * 1974-02-25 1977-11-08 James E. Johnson Modulating bypass variable cycle turbofan engine
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US2873576A (en) * 1952-02-06 1959-02-17 Rolls Royce Means for controlling the rotational speed of the low-pressure compressor rotor of gas turbine engines
FR1218064A (fr) * 1957-12-30 1960-05-09 Rolls Royce Perfectionnements aux moteurs à turbine à gaz
US2934895A (en) * 1958-09-15 1960-05-03 Curtiss Wright Corp Dual cycle engine distributor construction
FR1535872A (fr) * 1966-12-22 1968-08-09 Gen Electric Système de commande pour compresseurs à écoulement axial en particulier pour les moteurs à turbines à gaz
FR2273954A1 (fr) * 1974-06-07 1976-01-02 United Technologies Corp Systeme de controle pour propulseur a ventilateur a pas variable et reversible
FR2405367A1 (fr) * 1977-10-07 1979-05-04 Mtu Muenchen Gmbh Turbine a gaz combinee pour engin volant ayant des caracteristiques v/stol

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102171417A (zh) * 2008-09-30 2011-08-31 斯奈克玛 用于控制涡轮发动机中变几何装置的系统
RU2503824C2 (ru) * 2008-09-30 2014-01-10 Снекма Система управления оборудованием с изменяемой геометрией газотурбинного двигателя, содержащая, в частности, барабанное соединение
FR2936559A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine faisant partie de corps differents.
FR2936556A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine, notamment par guignols.
FR2936557A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison par pistes de guidage.
FR2936565A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine notamment, par guignols articules.
FR2936561A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par mecanisme a came
WO2010037949A1 (fr) * 2008-09-30 2010-04-08 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine
WO2010037751A1 (fr) 2008-09-30 2010-04-08 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison par pistes de guidage
WO2010037750A1 (fr) 2008-09-30 2010-04-08 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison a barillet
WO2010037749A1 (fr) 2008-09-30 2010-04-08 Snecma Systeme de commande d'equipements a geometrie variable d'une turbomachine, notamment par guignols
CN102171418A (zh) * 2008-09-30 2011-08-31 斯奈克玛 控制包括筒形连杆的燃气涡轮发动机的变几何设备的系统
FR2936558A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'equipements a geometrie variable d'un moteur a turbine a gaz comportant notamment une liaison a barillet.
US8328500B2 (en) 2008-09-30 2012-12-11 Snecma System for controlling variable-geometry equipments of a turbomachine, particularly by articulated bellcranks
US8690520B2 (en) 2008-09-30 2014-04-08 Snecma System for controlling variable geometry equipment of a gas turbine engine especially comprising a guiding track connection
US8337140B2 (en) 2008-09-30 2012-12-25 Snecma System for controlling at least two variable-geometry equipments of a gas turbine engine, particularly by rack
US8591173B2 (en) 2008-09-30 2013-11-26 Snecma System for controlling variable geometry apparatuses in a turbine engine
CN102171418B (zh) * 2008-09-30 2013-12-04 斯奈克玛 控制包括筒形连杆的燃气涡轮发动机的变几何设备的系统
CN102171415B (zh) * 2008-09-30 2013-12-11 斯奈克玛 一种特别是通过钟形曲柄控制涡轮发动机可变几何设备的系统
FR2936560A1 (fr) * 2008-09-30 2010-04-02 Snecma Systeme de commande d'au moins deux equipements a geometrie variable d'un moteur a turbine a gaz, notamment par cremaillere
RU2507402C2 (ru) * 2008-09-30 2014-02-20 Снекма Система управления оборудованием с изменяемой геометрией газотурбинного двигателя, содержащей, в частности, соединение с помощью направляющих дорожек
US8333546B2 (en) 2008-09-30 2012-12-18 Snecma System for controlling at least two variable-geometry equipments of a gas turbine engine, particularly by cam mechanism
US8690521B2 (en) 2008-09-30 2014-04-08 Snecma System for controlling variable geometry equipment for a turbine engine, especially by bellcranks
US8740547B2 (en) 2008-09-30 2014-06-03 Snecma System for controlling variable geometry equipment of a gas turbine engine particularly comprising a barrel link
CN102171417B (zh) * 2008-09-30 2015-05-20 斯奈克玛 用于控制涡轮发动机中变几何装置的系统
EP2864613A1 (fr) * 2012-06-20 2015-04-29 United Technologies Corporation Mécanisme d'entraînement à quatre barres pour système de purge
EP2864613A4 (fr) * 2012-06-20 2015-07-15 United Technologies Corp Mécanisme d'entraînement à quatre barres pour système de purge

Also Published As

Publication number Publication date
IT7928331A0 (it) 1979-12-21
US4292802A (en) 1981-10-06
DE2951962C2 (fr) 1992-07-09
GB2038947B (en) 1983-02-09
GB2038947A (en) 1980-07-30
JPS55104532A (en) 1980-08-11
IT1126668B (it) 1986-05-21
DE2951962A1 (de) 1980-07-17
FR2445439B1 (fr) 1986-03-21

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