GB2044358B - Gas turbine jet engine mounting - Google Patents

Gas turbine jet engine mounting

Info

Publication number
GB2044358B
GB2044358B GB7908516A GB7908516A GB2044358B GB 2044358 B GB2044358 B GB 2044358B GB 7908516 A GB7908516 A GB 7908516A GB 7908516 A GB7908516 A GB 7908516A GB 2044358 B GB2044358 B GB 2044358B
Authority
GB
United Kingdom
Prior art keywords
gas turbine
jet engine
engine mounting
turbine jet
mounting
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
Application number
GB7908516A
Other languages
English (en)
Other versions
GB2044358A (en
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
Priority to GB7908516A priority Critical patent/GB2044358B/en
Priority to US06/124,735 priority patent/US4326682A/en
Priority to DE19803008690 priority patent/DE3008690A1/de
Priority to FR8005121A priority patent/FR2451461A1/fr
Priority to JP3020180A priority patent/JPS55123318A/ja
Priority to IT20481/80A priority patent/IT1130018B/it
Publication of GB2044358A publication Critical patent/GB2044358A/en
Application granted granted Critical
Publication of GB2044358B publication Critical patent/GB2044358B/en
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
    • 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)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
GB7908516A 1979-03-10 1979-03-10 Gas turbine jet engine mounting Expired GB2044358B (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
GB7908516A GB2044358B (en) 1979-03-10 1979-03-10 Gas turbine jet engine mounting
US06/124,735 US4326682A (en) 1979-03-10 1980-02-26 Mounting for gas turbine powerplant
DE19803008690 DE3008690A1 (de) 1979-03-10 1980-03-06 Aufhaengung fuer mantelstrom-gasturbinentriebwerke
FR8005121A FR2451461A1 (fr) 1979-03-10 1980-03-07 Montage de groupe moteur de turbomachine
JP3020180A JPS55123318A (en) 1979-03-10 1980-03-10 Mount apparatus for gas turbine power apparatus
IT20481/80A IT1130018B (it) 1979-03-10 1980-03-10 Supporto per gruppo motopropulsore a turbina a gas

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
GB2044358A GB2044358A (en) 1980-10-15
GB2044358B true GB2044358B (en) 1983-01-19

Family

ID=10503796

Family Applications (1)

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

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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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
EP0796198B1 (en) * 1994-12-23 1998-08-19 United Technologies Corporation A mounting arrangement for a gas turbine engine
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
WO2006059971A2 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US7883314B2 (en) * 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
WO2006059992A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Inducer for a fan blade of a tip turbine engine
DE602004016059D1 (de) * 2004-12-01 2008-10-02 United Technologies Corp Tip-turbinentriebwerk mit wärmetauscher
WO2006060009A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Turbine blade engine comprising turbine clusters and radial attachment lock arrangement therefor
EP1825113B1 (en) * 2004-12-01 2012-10-24 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
WO2006059979A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral case, vane, mount, and mixer
US20090169385A1 (en) * 2004-12-01 2009-07-02 Suciu Gabriel L Fan-turbine rotor assembly with integral inducer section for a tip turbine engine
DE602004020125D1 (de) * 2004-12-01 2009-04-30 United Technologies Corp Schmiermittel-versorgungssystem für das getriebe eines tip-turbinen-triebwerks
WO2006059987A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Particle separator for tip turbine engine
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
US8152469B2 (en) * 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
WO2006060001A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Fan rotor assembly for a tip turbine engine
EP1831519B1 (en) * 2004-12-01 2010-08-04 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
US8087885B2 (en) * 2004-12-01 2012-01-03 United Technologies Corporation Stacked annular components for turbine engines
DE602004018045D1 (de) * 2004-12-01 2009-01-08 United Technologies Corp Gebläseschaufelanordnung für ein tip-turbinentriebwerk und montageverfahren
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7934902B2 (en) * 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
WO2006060006A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine non-metallic tailcone
WO2006059989A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine support structure
US8757959B2 (en) * 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US7874163B2 (en) * 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a 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
DE602004027766D1 (de) * 2004-12-01 2010-07-29 United Technologies Corp Hydraulische dichtung für ein getriebe eines spitzenturbinenmotors
DE602004029950D1 (de) * 2004-12-01 2010-12-16 United Technologies Corp Enggekoppelte getriebeanordnung für einen spitzenturbinenmotor
WO2006059977A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and corresponding orepating method
WO2006112807A2 (en) 2004-12-01 2006-10-26 United Technologies Corporation Turbine engine and method for starting a turbine engine
WO2006060013A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7980054B2 (en) * 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
WO2006059978A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Cantilevered tip turbine engine
WO2006059988A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Modular tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
EP1828567B1 (en) 2004-12-01 2011-10-12 United Technologies Corporation Diffuser aspiration for a 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
EP1825128B1 (en) * 2004-12-01 2011-03-02 United Technologies Corporation Regenerative turbine blade and vane cooling for a tip turbine engine
EP1825111B1 (en) * 2004-12-01 2011-08-31 United Technologies Corporation Counter-rotating compressor case for a tip turbine engine
WO2006060000A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
WO2006059996A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US8561383B2 (en) * 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
EP1828591B1 (en) * 2004-12-01 2010-07-21 United Technologies Corporation Peripheral combustor for tip turbine engine
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
US8262050B2 (en) * 2008-12-24 2012-09-11 General Electric Company Method and apparatus for mounting and dismounting an aircraft engine
US8469309B2 (en) * 2008-12-24 2013-06-25 General Electric Company Monolithic structure for mounting aircraft engine
US8567202B2 (en) * 2009-05-15 2013-10-29 Pratt & Whitney Canada Corp. Support links with lockable adjustment feature
US8979491B2 (en) 2009-05-15 2015-03-17 Pratt & Whitney Canada Corp. Turbofan mounting arrangement
US8313293B2 (en) * 2009-05-15 2012-11-20 Pratt & Whitney Canada Corp. Turbofan mounting system
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
WO2011159671A1 (en) * 2010-06-14 2011-12-22 Lord Corporation A helicopter engine mounting system and methods
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

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US2539960A (en) * 1946-05-22 1951-01-30 Bristol Aeroplane Co Ltd Mounting structure for gas-turbine power plants for aircraft
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GB777803A (en) * 1953-01-15 1957-06-26 Pye Ltd Improvements in or relating to television receivers
FR1275966A (fr) * 1959-12-18 1961-11-10 Gen Electric Inverseur de poussée
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Also Published As

Publication number Publication date
IT1130018B (it) 1986-06-11
DE3008690A1 (de) 1980-09-11
IT8020481A0 (it) 1980-03-10
FR2451461A1 (fr) 1980-10-10
JPS55123318A (en) 1980-09-22
GB2044358A (en) 1980-10-15
US4326682A (en) 1982-04-27
FR2451461B1 (enExample) 1983-06-17

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee