FR2451461A1 - Montage de groupe moteur de turbomachine - Google Patents

Montage de groupe moteur de turbomachine

Info

Publication number
FR2451461A1
FR2451461A1 FR8005121A FR8005121A FR2451461A1 FR 2451461 A1 FR2451461 A1 FR 2451461A1 FR 8005121 A FR8005121 A FR 8005121A FR 8005121 A FR8005121 A FR 8005121A FR 2451461 A1 FR2451461 A1 FR 2451461A1
Authority
FR
France
Prior art keywords
engine unit
engine
ring
assembly
casing
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
FR8005121A
Other languages
English (en)
French (fr)
Other versions
FR2451461B1 (enExample
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of FR2451461A1 publication Critical patent/FR2451461A1/fr
Application granted granted Critical
Publication of FR2451461B1 publication Critical patent/FR2451461B1/fr
Granted 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
    • 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
    • B64D27/404—Suspension arrangements specially adapted for supporting vertical loads
    • 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
    • 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
    • F02K1/74—Reversing at least one flow in relation to at least one other flow in a plural- flow engine

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
FR8005121A 1979-03-10 1980-03-07 Montage de groupe moteur de turbomachine Granted FR2451461A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB7908516A GB2044358B (en) 1979-03-10 1979-03-10 Gas turbine jet engine mounting

Publications (2)

Publication Number Publication Date
FR2451461A1 true FR2451461A1 (fr) 1980-10-10
FR2451461B1 FR2451461B1 (enExample) 1983-06-17

Family

ID=10503796

Family Applications (1)

Application Number Title Priority Date Filing Date
FR8005121A Granted FR2451461A1 (fr) 1979-03-10 1980-03-07 Montage de groupe moteur de turbomachine

Country Status (6)

Country Link
US (1) US4326682A (enExample)
JP (1) JPS55123318A (enExample)
DE (1) DE3008690A1 (enExample)
FR (1) FR2451461A1 (enExample)
GB (1) GB2044358B (enExample)
IT (1) IT1130018B (enExample)

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WO1991005150A1 (en) * 1989-09-29 1991-04-18 Sundstrand Corporation, Inc. Geodesic engine mount structure
US5127606A (en) * 1990-11-16 1992-07-07 Allied-Signal Inc. Aircraft engine mount adapter and method
US5174525A (en) * 1991-09-26 1992-12-29 General Electric Company Structure for eliminating lift load bending in engine core of turbofan
US5275357A (en) * 1992-01-16 1994-01-04 General Electric Company Aircraft engine mount
US5320307A (en) * 1992-03-25 1994-06-14 General Electric Company Aircraft engine thrust mount
US5524847A (en) * 1993-09-07 1996-06-11 United Technologies Corporation Nacelle and mounting arrangement for an aircraft engine
US5452575A (en) * 1993-09-07 1995-09-26 General Electric Company Aircraft gas turbine engine thrust mount
US5443229A (en) * 1993-12-13 1995-08-22 General Electric Company Aircraft gas turbine engine sideways mount
US5467941A (en) * 1993-12-30 1995-11-21 The Boeing Company Pylon and engine installation for ultra-high by-pass turbo-fan engines
WO1996018538A1 (en) * 1994-12-12 1996-06-20 United Technologies Corporation A mounting arrangement for a gas turbine engine
DE69504209T2 (de) * 1994-12-23 1999-04-29 United Technologies Corp., Hartford, Conn. Befestigungsvorrichtung für ein gasturbinentriebwerk
FR2867157B1 (fr) * 2004-03-04 2006-06-02 Airbus France Systeme de montage interpose entre un moteur d'aeronef et une structure rigide d'un mat d'accrochage fixe sous une voilure de cet aeronef.
FR2867156B1 (fr) * 2004-03-04 2006-06-02 Airbus France Systeme de montage interpose entre un moteur d'aeronef et une structure rigide d'un mat d'accrochage fixe sous une voilure de cet aeronef.
FR2869874B1 (fr) * 2004-05-04 2006-06-23 Snecma Moteurs Sa Moteur d'avion avec des moyens de suspension a la structure d'un avion
EP1828567B1 (en) 2004-12-01 2011-10-12 United Technologies Corporation Diffuser aspiration for a tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
WO2006059999A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US7959532B2 (en) * 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
DE602004031986D1 (de) * 2004-12-01 2011-05-05 United Technologies Corp Gebläse-turbinen-rotoranordnung für einen spitzenturbinenmotor
WO2006059993A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
WO2006059974A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
WO2006059986A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
EP1828591B1 (en) * 2004-12-01 2010-07-21 United Technologies Corporation Peripheral combustor for tip turbine engine
US7878762B2 (en) * 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
US7874163B2 (en) * 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
WO2006059987A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Particle separator for tip turbine engine
EP1825111B1 (en) * 2004-12-01 2011-08-31 United Technologies Corporation Counter-rotating compressor case for a tip turbine engine
DE602004023769D1 (de) * 2004-12-01 2009-12-03 United Technologies Corp Gestapelte ringförmige bauteile für turbinenmotoren
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
WO2006060003A2 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
WO2006059988A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Modular tip turbine engine
US7937927B2 (en) * 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
WO2006110124A2 (en) * 2004-12-01 2006-10-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
WO2006060006A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine non-metallic tailcone
WO2006059970A2 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US7976273B2 (en) * 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
WO2006059971A2 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
EP1825112B1 (en) * 2004-12-01 2013-10-23 United Technologies Corporation Cantilevered tip turbine engine
WO2006060010A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Compressor inlet guide vane for tip turbine engine and corresponding control method
US20080219833A1 (en) * 2004-12-01 2008-09-11 United Technologies Corporation Inducer for a Fan Blade of a Tip Turbine Engine
US8757959B2 (en) * 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7921636B2 (en) * 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
US7883314B2 (en) * 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
WO2006059995A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Gearbox lubrication supply system for a tip turbine engine
EP1825114B1 (en) * 2004-12-01 2008-08-20 United Technologies Corporation Tip turbine engine with a heat exchanger
WO2006110122A2 (en) 2004-12-01 2006-10-19 United Technologies Corporation Inflatable bleed valve for a turbine engine and a method of operating therefore
WO2006060005A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Fan-turbine rotor assembly with integral inducer section for a tip turbine engine
WO2006060013A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US8365511B2 (en) * 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
EP1834067B1 (en) * 2004-12-01 2008-11-26 United Technologies Corporation Fan blade assembly for a tip turbine engine and method of assembly
WO2006059996A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US7934902B2 (en) * 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
DE602004031679D1 (de) * 2004-12-01 2011-04-14 United Technologies Corp Regenerative Kühlung einer Leit- und Laufschaufel für ein Tipturbinentriebwerk
DE602004031470D1 (de) * 2004-12-01 2011-03-31 United Technologies Corp Übergangskanal mit mitteln zur strömungsvektorbeeinflussung bei einer gasturbine
US8152469B2 (en) * 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
US9109537B2 (en) * 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
GB2422874A (en) * 2005-02-05 2006-08-09 Alstom Technology Ltd Gas turbine burner expansion bar structure
FR2903382B1 (fr) * 2006-07-10 2008-10-10 Airbus France Sas Dispositif d'accrochage d'un moteur d'aeronef comportant deux bielles de reprise de poussee a emboitement transversal
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US20140174056A1 (en) * 2008-06-02 2014-06-26 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
US8469309B2 (en) * 2008-12-24 2013-06-25 General Electric Company Monolithic structure for mounting aircraft engine
US8262050B2 (en) * 2008-12-24 2012-09-11 General Electric Company Method and apparatus for mounting and dismounting an aircraft engine
US8567202B2 (en) 2009-05-15 2013-10-29 Pratt & Whitney Canada Corp. Support links with lockable adjustment feature
US8313293B2 (en) * 2009-05-15 2012-11-20 Pratt & Whitney Canada Corp. Turbofan mounting system
US8979491B2 (en) 2009-05-15 2015-03-17 Pratt & Whitney Canada Corp. Turbofan mounting arrangement
US8621874B2 (en) * 2009-08-25 2014-01-07 Honeywell International Inc. Turbomachine core coupling assembly
US9114882B2 (en) * 2010-10-26 2015-08-25 United Technologies Corporation Fan case and mount ring snap fit assembly
DE102010001059A1 (de) * 2010-01-20 2011-07-21 Rolls-Royce Deutschland Ltd & Co KG, 15827 Zwischengehäuse für ein Gasturbinentriebwerk
KR101828921B1 (ko) * 2010-06-14 2018-02-13 로오드 코포레이션 헬리콥터 엔진 장착 시스템 및 방법
US8348191B2 (en) 2010-07-14 2013-01-08 Spirit Aerosystems, Inc. Fail-safe aircraft engine mounting apparatus
US9194296B2 (en) 2012-05-18 2015-11-24 Pratt & Whitney Canada Corp. Inner bypass duct wall attachment
US9212607B2 (en) 2012-07-18 2015-12-15 Spirit Aerosystems, Inc. Intermediate structure for independently de-mountable propulsion components
GB201906164D0 (en) * 2019-05-02 2019-06-19 Rolls Royce Plc Gas turbine engine

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR930687A (fr) * 1945-07-21 1948-02-02 Power Jets Res & Dev Ltd Perfectionnements apportés aux dispositifs à réaction par jet
US2539960A (en) * 1946-05-22 1951-01-30 Bristol Aeroplane Co Ltd Mounting structure for gas-turbine power plants for aircraft
FR1095672A (fr) * 1953-01-15 1955-06-06 Rolls Royce Perfectionnements aux installations et unités de propulsion à reaction d'aérodynes
US2720370A (en) * 1950-12-04 1955-10-11 Hasbrouck Augustus Resilient engine mounting system, including flexible self-compensating joints
FR1275966A (fr) * 1959-12-18 1961-11-10 Gen Electric Inverseur de poussée
US3352114A (en) * 1965-07-17 1967-11-14 Rolls Royce Mounting means for separately supporting a gas turbine engine and a jet pipe in an engine pod
FR2102187A1 (enExample) * 1970-08-11 1972-04-07 Secretaire Etat Royaume
US3675418A (en) * 1970-11-19 1972-07-11 United Aircraft Corp Jet engine force frame
US3856239A (en) * 1972-08-25 1974-12-24 Mtu Muenchen Gmbh Apparatus for thrust reversal
US4044973A (en) * 1975-12-29 1977-08-30 The Boeing Company Nacelle assembly and mounting structures for a turbofan jet propulsion engine
GB1504290A (en) * 1975-08-01 1978-03-15 Rolls Royce Gas turbine engine mounting systems
GB2010969A (en) * 1977-12-22 1979-07-04 Rolls Royce Mounting for Gas Turbine Jet Propulsion Engine

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DE1506083A1 (de) * 1965-03-16 1969-10-23 Rolls Royce Triebwerkseinbau in Flugzeugen
US3601340A (en) * 1969-05-28 1971-08-24 Rohr Corp Method and apparatus for augmenting and reversing thrust and reducing nozzle base drag and noise of an aircraft jet engine
US4185798A (en) * 1978-03-13 1980-01-29 Rohr Industries, Inc. Thrust reverser-cascade two door pre-exit

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR930687A (fr) * 1945-07-21 1948-02-02 Power Jets Res & Dev Ltd Perfectionnements apportés aux dispositifs à réaction par jet
US2539960A (en) * 1946-05-22 1951-01-30 Bristol Aeroplane Co Ltd Mounting structure for gas-turbine power plants for aircraft
US2720370A (en) * 1950-12-04 1955-10-11 Hasbrouck Augustus Resilient engine mounting system, including flexible self-compensating joints
FR1095672A (fr) * 1953-01-15 1955-06-06 Rolls Royce Perfectionnements aux installations et unités de propulsion à reaction d'aérodynes
FR1275966A (fr) * 1959-12-18 1961-11-10 Gen Electric Inverseur de poussée
US3352114A (en) * 1965-07-17 1967-11-14 Rolls Royce Mounting means for separately supporting a gas turbine engine and a jet pipe in an engine pod
FR2102187A1 (enExample) * 1970-08-11 1972-04-07 Secretaire Etat Royaume
US3675418A (en) * 1970-11-19 1972-07-11 United Aircraft Corp Jet engine force frame
US3856239A (en) * 1972-08-25 1974-12-24 Mtu Muenchen Gmbh Apparatus for thrust reversal
GB1504290A (en) * 1975-08-01 1978-03-15 Rolls Royce Gas turbine engine mounting systems
US4044973A (en) * 1975-12-29 1977-08-30 The Boeing Company Nacelle assembly and mounting structures for a turbofan jet propulsion engine
GB2010969A (en) * 1977-12-22 1979-07-04 Rolls Royce Mounting for Gas Turbine Jet Propulsion Engine

Also Published As

Publication number Publication date
DE3008690A1 (de) 1980-09-11
GB2044358A (en) 1980-10-15
FR2451461B1 (enExample) 1983-06-17
JPS55123318A (en) 1980-09-22
IT8020481A0 (it) 1980-03-10
IT1130018B (it) 1986-06-11
GB2044358B (en) 1983-01-19
US4326682A (en) 1982-04-27

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