DE69104535D1 - Flugzeugtriebwerk mit hohem Nebenstromverhältnis und mit gegenläufigem Frontbläsertriebwerk. - Google Patents

Flugzeugtriebwerk mit hohem Nebenstromverhältnis und mit gegenläufigem Frontbläsertriebwerk.

Info

Publication number
DE69104535D1
DE69104535D1 DE69104535T DE69104535T DE69104535D1 DE 69104535 D1 DE69104535 D1 DE 69104535D1 DE 69104535 T DE69104535 T DE 69104535T DE 69104535 T DE69104535 T DE 69104535T DE 69104535 D1 DE69104535 D1 DE 69104535D1
Authority
DE
Germany
Prior art keywords
engine
counter
bypass ratio
front fan
high bypass
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 - Fee Related
Application number
DE69104535T
Other languages
English (en)
Other versions
DE69104535T2 (de
Inventor
Jacques Rene Bart
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Application granted granted Critical
Publication of DE69104535D1 publication Critical patent/DE69104535D1/de
Publication of DE69104535T2 publication Critical patent/DE69104535T2/de
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40—Arrangements for mounting power plants in aircraft
    • B64D27/402—Arrangements for mounting power plants in aircraft comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
DE69104535T 1990-04-19 1991-04-17 Flugzeugtriebwerk mit hohem Nebenstromverhältnis und mit gegenläufigem Frontbläsertriebwerk. Expired - Fee Related DE69104535T2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR9004991A FR2661213B1 (fr) 1990-04-19 1990-04-19 Moteur d'aviation a tres grand taux de dilution et du type dit contrafan avant.

Publications (2)

Publication Number Publication Date
DE69104535D1 true DE69104535D1 (de) 1994-11-17
DE69104535T2 DE69104535T2 (de) 1995-03-23

Family

ID=9395885

Family Applications (1)

Application Number Title Priority Date Filing Date
DE69104535T Expired - Fee Related DE69104535T2 (de) 1990-04-19 1991-04-17 Flugzeugtriebwerk mit hohem Nebenstromverhältnis und mit gegenläufigem Frontbläsertriebwerk.

Country Status (4)

Country Link
US (1) US5157915A (de)
EP (1) EP0453360B1 (de)
DE (1) DE69104535T2 (de)
FR (1) FR2661213B1 (de)

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US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
US8468795B2 (en) 2004-12-01 2013-06-25 United Technologies Corporation Diffuser aspiration for a tip turbine engine
US8033092B2 (en) * 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US7980054B2 (en) * 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
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US7976273B2 (en) * 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
WO2006059969A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Counter-rotating compressor case and assembly method for tip turbine engine
US20090169385A1 (en) * 2004-12-01 2009-07-02 Suciu Gabriel L Fan-turbine rotor assembly with integral inducer section for a tip turbine engine
DE602004016059D1 (de) 2004-12-01 2008-10-02 United Technologies Corp Tip-turbinentriebwerk mit wärmetauscher
WO2006060006A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine non-metallic tailcone
DE602004016065D1 (de) 2004-12-01 2008-10-02 United Technologies Corp Variable gebläseeinlassleitschaufelanordnung, turbinenmotor mit solch einer anordnung und entsprechendes steuerverfahren
US7854112B2 (en) * 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US8096753B2 (en) * 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
WO2006059993A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
WO2006059987A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Particle separator for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8087885B2 (en) * 2004-12-01 2012-01-03 United Technologies Corporation Stacked annular components for turbine engines
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WO2006059970A2 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
WO2006059994A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
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EP1825113B1 (de) * 2004-12-01 2012-10-24 United Technologies Corporation Gegenläufiges getriebe für ein tip-turbinen-triebwerk
EP1841960B1 (de) * 2004-12-01 2011-05-25 United Technologies Corporation Starter-generatorsystem für einen spitzenturbinenmotor
US20080219833A1 (en) * 2004-12-01 2008-09-11 United Technologies Corporation Inducer for a Fan Blade of a Tip Turbine Engine
EP1841959B1 (de) * 2004-12-01 2012-05-09 United Technologies Corporation Ausgewuchtete turbinenrotorlüfterschaufel für einen spitzenturbinenmotor
EP1828573B1 (de) * 2004-12-01 2010-06-16 United Technologies Corporation Hydraulische dichtung für ein getriebe eines spitzenturbinenmotors
EP1831520B1 (de) * 2004-12-01 2009-02-25 United Technologies Corporation Tip-turbinentriebwerk und entsprechendes betriebsverfahren
DE602004031986D1 (de) * 2004-12-01 2011-05-05 United Technologies Corp Gebläse-turbinen-rotoranordnung für einen spitzenturbinenmotor
DE602004029950D1 (de) * 2004-12-01 2010-12-16 United Technologies Corp Enggekoppelte getriebeanordnung für einen spitzenturbinenmotor
US9109537B2 (en) * 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US7435050B2 (en) * 2006-01-11 2008-10-14 United Technologies Corporation Split flange V-groove and anti-rotation mating system
GB0606982D0 (en) * 2006-04-07 2006-05-17 Rolls Royce Plc Aeroengine thrust reverser
FR2902406B1 (fr) * 2006-06-20 2008-07-18 Airbus France Sas Carenage pour mat de suspension d'un turbomoteur a une aile d'aeronef
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FR2905991B1 (fr) 2006-09-20 2012-01-13 Snecma Systeme propulsif integre comportant un moteur a turboreacteur a double flux.
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US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
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CN107963225B (zh) * 2017-11-30 2021-06-04 中国商用飞机有限责任公司 飞机发动机吊挂及其吊挂盒段
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FR2622507B1 (de) * 1987-10-28 1990-01-26 Snecma

Also Published As

Publication number Publication date
EP0453360A1 (de) 1991-10-23
FR2661213A1 (fr) 1991-10-25
US5157915A (en) 1992-10-27
DE69104535T2 (de) 1995-03-23
EP0453360B1 (de) 1994-10-12
FR2661213B1 (fr) 1992-07-03

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: SNECMA MOTEURS, PARIS, FR

8327 Change in the person/name/address of the patent owner

Owner name: SNECMA, PARIS, FR

8339 Ceased/non-payment of the annual fee