Nothing Special   »   [go: up one dir, main page]

DE602005010923D1 - Zweibläser Mantelstromtriebwerk ausgerüstet mit schwenkbaren Leitschaufeln - Google Patents

Zweibläser Mantelstromtriebwerk ausgerüstet mit schwenkbaren Leitschaufeln

Info

Publication number
DE602005010923D1
DE602005010923D1 DE602005010923T DE602005010923T DE602005010923D1 DE 602005010923 D1 DE602005010923 D1 DE 602005010923D1 DE 602005010923 T DE602005010923 T DE 602005010923T DE 602005010923 T DE602005010923 T DE 602005010923T DE 602005010923 D1 DE602005010923 D1 DE 602005010923D1
Authority
DE
Germany
Prior art keywords
bladed
double
turbofan engine
engine equipped
swiveling vanes
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.)
Active
Application number
DE602005010923T
Other languages
English (en)
Inventor
Jacques Bart
Fabienne Lacorre
Yann Lebret
Rousseau Vanessa Le
Patrick Morel
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of DE602005010923D1 publication Critical patent/DE602005010923D1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F02K3/072—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 with counter-rotating, e.g. fan rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • 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)
DE602005010923T 2004-02-12 2005-01-27 Zweibläser Mantelstromtriebwerk ausgerüstet mit schwenkbaren Leitschaufeln Active DE602005010923D1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0401384A FR2866387B1 (fr) 2004-02-12 2004-02-12 Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante

Publications (1)

Publication Number Publication Date
DE602005010923D1 true DE602005010923D1 (de) 2008-12-24

Family

ID=34707994

Family Applications (1)

Application Number Title Priority Date Filing Date
DE602005010923T Active DE602005010923D1 (de) 2004-02-12 2005-01-27 Zweibläser Mantelstromtriebwerk ausgerüstet mit schwenkbaren Leitschaufeln

Country Status (10)

Country Link
US (1) US7299621B2 (de)
EP (1) EP1566522B1 (de)
JP (1) JP4237712B2 (de)
CN (1) CN1654804B (de)
CA (1) CA2495992C (de)
DE (1) DE602005010923D1 (de)
ES (1) ES2317168T3 (de)
FR (1) FR2866387B1 (de)
RU (1) RU2364740C2 (de)
UA (1) UA83995C2 (de)

Families Citing this family (54)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0314123D0 (en) * 2003-06-18 2003-07-23 Rolls Royce Plc A gas turbine engine
DE102004042739A1 (de) * 2004-09-03 2006-03-09 Mtu Aero Engines Gmbh Fan für ein Flugtriebwerk sowie Flugtriebwerk
US7882694B2 (en) * 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
FR2889863B1 (fr) * 2005-08-22 2007-11-02 Snecma Compresseur comportant une pluralite de caissons reconstituant un volume annulaire de separation de flux dans une turbomachine.
US7490461B2 (en) * 2005-10-19 2009-02-17 General Electric Company Gas turbine engine assembly and methods of assembling same
US7685808B2 (en) * 2005-10-19 2010-03-30 General Electric Company Gas turbine engine assembly and methods of assembling same
US7841165B2 (en) * 2006-10-31 2010-11-30 General Electric Company Gas turbine engine assembly and methods of assembling same
US9359960B2 (en) * 2007-06-28 2016-06-07 United Technologies Corporation Gas turbines with multiple gas flow paths
US8161728B2 (en) * 2007-06-28 2012-04-24 United Technologies Corp. Gas turbines with multiple gas flow paths
US8104265B2 (en) * 2007-06-28 2012-01-31 United Technologies Corporation Gas turbines with multiple gas flow paths
US20120222398A1 (en) * 2007-07-27 2012-09-06 Smith Peter G Gas turbine engine with geared architecture
FR2921973B1 (fr) * 2007-10-04 2011-04-29 Snecma Carter intermediaire de turboreacteur et turboreacteur
EP2123884B1 (de) * 2008-05-13 2015-03-04 Rolls-Royce Corporation Doppelkupplungseinheit
US20140174056A1 (en) 2008-06-02 2014-06-26 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
US8128021B2 (en) 2008-06-02 2012-03-06 United Technologies Corporation Engine mount system for a turbofan gas turbine engine
EP2177735A3 (de) * 2008-10-20 2012-02-15 Rolls-Royce North American Technologies, Inc. Turbofan
FR2942273B1 (fr) * 2009-02-18 2011-06-10 Snecma Moteur double flux a roues de turbine contrarotatives
GB0910955D0 (en) 2009-06-25 2009-08-05 Rolls Royce Plc Adjustable camber aerofoil
US8176725B2 (en) * 2009-09-09 2012-05-15 United Technologies Corporation Reversed-flow core for a turbofan with a fan drive gear system
US9631558B2 (en) 2012-01-03 2017-04-25 United Technologies Corporation Geared architecture for high speed and small volume fan drive turbine
US9239012B2 (en) 2011-06-08 2016-01-19 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
FR2977635B1 (fr) * 2011-07-04 2017-03-24 Snecma Dispositif d'arbre d'entrainement d'une turbomachine
US9506402B2 (en) 2011-07-29 2016-11-29 United Technologies Corporation Three spool engine bearing configuration
EP2802745A4 (de) * 2012-01-09 2015-10-21 United Technologies Corp Gasturbinenmotor mit verzahnter architektur
US10018119B2 (en) * 2012-04-02 2018-07-10 United Technologies Corporation Geared architecture with inducer for gas turbine engine
US10036351B2 (en) 2012-04-02 2018-07-31 United Technologies Corporation Geared turbofan with three co-rotating turbines
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US9074485B2 (en) 2012-04-25 2015-07-07 United Technologies Corporation Geared turbofan with three turbines all counter-rotating
US10036350B2 (en) 2012-04-30 2018-07-31 United Technologies Corporation Geared turbofan with three turbines all co-rotating
US20150308351A1 (en) 2012-05-31 2015-10-29 United Technologies Corporation Fundamental gear system architecture
US8572943B1 (en) 2012-05-31 2013-11-05 United Technologies Corporation Fundamental gear system architecture
US8756908B2 (en) 2012-05-31 2014-06-24 United Technologies Corporation Fundamental gear system architecture
FR2994452B1 (fr) * 2012-08-09 2016-12-23 Snecma Turbomachine comportant une pluralite d'aubes radiales fixes montees en amont de la soufflante
CN103867337B (zh) * 2012-12-11 2016-02-03 中航商用航空发动机有限责任公司 大涵道比变循环发动机
WO2014133645A2 (en) * 2013-02-20 2014-09-04 Rolls-Royce North American Technologies Inc. Gas turbine engine having configurable bypass passage
FR3003303B1 (fr) * 2013-03-15 2017-06-30 Snecma Turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion
EP3004595B1 (de) * 2013-06-03 2020-09-02 United Technologies Corporation Anordnung aus einem turbofan-triebwerklager und einem getriebe
US9777642B2 (en) 2014-11-21 2017-10-03 General Electric Company Gas turbine engine and method of assembling the same
US10077660B2 (en) 2014-12-03 2018-09-18 General Electric Company Turbine engine assembly and method of manufacturing
CN104500269B (zh) * 2014-12-11 2016-04-20 南京航空航天大学 带内环空气涡轮的自驱动风扇大涵道比涡扇发动机
US10669946B2 (en) 2015-06-05 2020-06-02 Raytheon Technologies Corporation Geared architecture for a gas turbine engine
FR3039227B1 (fr) * 2015-07-22 2019-12-27 Safran Aircraft Engines Aeronef comprenant un propulseur arriere carene avec stator d’entree a volets mobiles
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
FR3043714B1 (fr) * 2015-11-16 2017-12-22 Snecma Partie avant de turbomachine d'aeronef comprenant une soufflante unique entrainee par un reducteur, ainsi que des aubes directrices de sortie structurales agencees en partie en amont d'un bec de separation
US10563593B2 (en) * 2016-01-04 2020-02-18 Rolls-Royce North American Technologies, Inc. System and method of transferring power in a gas turbine engine
US10794281B2 (en) 2016-02-02 2020-10-06 General Electric Company Gas turbine engine having instrumented airflow path components
US20170218842A1 (en) * 2016-02-02 2017-08-03 General Electric Company Adjusting Airflow Distortion in Gas Turbine Engine
US11073090B2 (en) 2016-03-30 2021-07-27 General Electric Company Valved airflow passage assembly for adjusting airflow distortion in gas turbine engine
US10753278B2 (en) 2016-03-30 2020-08-25 General Electric Company Translating inlet for adjusting airflow distortion in gas turbine engine
BE1025299B9 (fr) * 2017-06-09 2020-05-04 Safran Aero Boosters Sa Compresseur a geometrie variable de turbomachine axiale
US10961921B2 (en) 2018-09-19 2021-03-30 Pratt & Whitney Canada Corp. Model-based control system and method for a turboprop engine
FR3118094A1 (fr) * 2020-12-23 2022-06-24 Safran Aube de stator avec portion mobile, module de turbomachine equipe d’une telle aube de stator et turbomachine correspondante
WO2024121464A1 (fr) * 2022-12-05 2024-06-13 Safran Aircraft Engines Turbomachine d'aéronef a triple flux

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1305302A (de) * 1970-04-28 1973-01-31
US4791783A (en) * 1981-11-27 1988-12-20 General Electric Company Convertible aircraft engine
GB2155110A (en) * 1984-03-02 1985-09-18 Gen Electric High bypass ratio counter-rotating turbofan engine
US4860537A (en) * 1986-08-29 1989-08-29 Brandt, Inc. High bypass ratio counterrotating gearless front fan engine
GB2194292A (en) * 1986-08-29 1988-03-02 Gen Electric High bypass ratio counterrotating turbofan engine
GB8630754D0 (en) * 1986-12-23 1987-02-04 Rolls Royce Plc Turbofan gas turbine engine
US5160251A (en) * 1991-05-13 1992-11-03 General Electric Company Lightweight engine turbine bearing support assembly for withstanding radial and axial loads
US5388964A (en) * 1993-09-14 1995-02-14 General Electric Company Hybrid rotor blade
US5806303A (en) * 1996-03-29 1998-09-15 General Electric Company Turbofan engine with a core driven supercharged bypass duct and fixed geometry nozzle
US6732502B2 (en) * 2002-03-01 2004-05-11 General Electric Company Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor

Also Published As

Publication number Publication date
RU2005103706A (ru) 2006-07-20
ES2317168T3 (es) 2009-04-16
CN1654804A (zh) 2005-08-17
FR2866387A1 (fr) 2005-08-19
EP1566522A1 (de) 2005-08-24
US7299621B2 (en) 2007-11-27
CA2495992A1 (fr) 2005-08-12
JP2005226644A (ja) 2005-08-25
US20050241291A1 (en) 2005-11-03
CN1654804B (zh) 2011-06-01
UA83995C2 (ru) 2008-09-10
RU2364740C2 (ru) 2009-08-20
FR2866387B1 (fr) 2008-03-14
EP1566522B1 (de) 2008-11-12
JP4237712B2 (ja) 2009-03-11
CA2495992C (fr) 2011-11-22

Similar Documents

Publication Publication Date Title
DE602005010923D1 (de) Zweibläser Mantelstromtriebwerk ausgerüstet mit schwenkbaren Leitschaufeln
DE602005003759D1 (de) Gegenläufiges Turbinentriebwerk
DE602005007391D1 (de) Gasturbinentriebwerk
GB0406174D0 (en) Turbine engine arrangement
GB2405181B (en) Turbomachine with low noise emissions for aircraft
DE502005010604D1 (de) Strömungsarbeitsmaschine
DE602006021273D1 (de) Verbrennungsmotor
EP1843045A4 (de) Mantelstrom-triebwerk
FR2898641B1 (fr) Habillage de carter dans un turboreacteur
FR2873096B1 (fr) Avion multimoteur
GB0401189D0 (en) Turbine engine arrangements
DE602005001029D1 (de) Turbinenblatt mit Mantel
DE602005001528D1 (de) Gasturbinentriebwerk
DE602005000974D1 (de) Turbomaschine mit gegenläufigem Gebläse
DE602005011089D1 (de) Motorhaube
FR2871517B1 (fr) Turbomachine avec moyens de retenue axiale du rotor
NO20053175D0 (no) Drivstoffadditiver.
SE0401279L (sv) Motorstyrning
DE602005017501D1 (de) Verbrennungsmotor
NO20054964L (no) Drivstoffdryppfanger
DE602005012560D1 (de) Nachbrenner mit gesicherter Zündung
DE602005006051D1 (de) Kraftstoffpumpe
FI20050004A0 (fi) Moottorilaitteisto
GB2411210B (en) Gas turbine engine rotatable component.
GB0402563D0 (en) Wing engine

Legal Events

Date Code Title Description
8364 No opposition during term of opposition