GB998108A - Improvements in turbine engine and gearbox mounting arrangement - Google Patents

Improvements in turbine engine and gearbox mounting arrangement

Info

Publication number
GB998108A
GB998108A GB37127/62A GB3712762A GB998108A GB 998108 A GB998108 A GB 998108A GB 37127/62 A GB37127/62 A GB 37127/62A GB 3712762 A GB3712762 A GB 3712762A GB 998108 A GB998108 A GB 998108A
Authority
GB
United Kingdom
Prior art keywords
engine
mounts
gear
box
main
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
GB37127/62A
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 GB998108A publication Critical patent/GB998108A/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
    • 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
    • B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type 
    • 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
    • B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Support Of The Bearing (AREA)
  • Motor Power Transmission Devices (AREA)

Abstract

998,108. Gas turbine plant. GENERAL ELECTRIC CO. Oct. 1, 1962 [Sept. 29, 1961], No. 37127/62. Heading FIG. [Also in Division B7] A mounting structure for a gas turbine engine 2 and gearbox assembly 4 comprises at least two supporting struts 6, 7 extending between and connected with the engine and the gear-box as well as a torque tube 3 enclosing the output drive shaft of the engine and rigidly interconnecting the engine and the gear-box, first and second main mounts 15, 16 circumferentially positioned on the gear-box in a plane extending between the offset axes of the engine output drive shaft and the propeller shaft 5 extending from the gear-box, a third main mount 17 positioned on the gear-box at a point intermediate the first and second main mounts and a fourth main mount 18 positioned on the engine to allow for thermal deflection. Auxiliary mounts 19 and 20 are provided on the engine attachment pads for the struts 6 and 7, the auxiliary mounts having a deflection characteristic which provides a relatively soft mount under small deflections of the power plant assembly but a stiffer mount under larger deflections such as would occur for instance, if one of the main mounts failed. The elastic axis of the mounts 15, 16, 17 is shown at 51 adjacent the axis of shaft 5 and the elastic centre of the mounting system as a whole is shown at 50.
GB37127/62A 1961-09-29 1962-10-01 Improvements in turbine engine and gearbox mounting arrangement Expired GB998108A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14165661A 1961-09-29 1961-09-29

Publications (1)

Publication Number Publication Date
GB998108A true GB998108A (en) 1965-07-14

Family

ID=22496614

Family Applications (1)

Application Number Title Priority Date Filing Date
GB37127/62A Expired GB998108A (en) 1961-09-29 1962-10-01 Improvements in turbine engine and gearbox mounting arrangement

Country Status (2)

Country Link
DE (1) DE1292501B (en)
GB (1) GB998108A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1539573A1 (en) * 2002-09-17 2005-06-15 Bell Helicopter Textron Inc. Torsionally de-coupled engine mount system

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3907220A (en) * 1974-03-14 1975-09-23 United Aircraft Corp Rear engine redundant mount

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2860712A (en) * 1952-02-23 1958-11-18 Gen Motors Corp Control for aircraft power plant
DE911810C (en) * 1952-06-29 1954-05-20 Bell Aircraft Corp Elastic mounting of the engine unit in the fuselage of a vehicle, in particular a helicopter

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1539573A1 (en) * 2002-09-17 2005-06-15 Bell Helicopter Textron Inc. Torsionally de-coupled engine mount system
EP1539573A4 (en) * 2002-09-17 2005-12-14 Bell Helicopter Textron Inc Torsionally de-coupled engine mount system
US7594623B2 (en) 2002-09-17 2009-09-29 Bell Helicopter Textron Inc. Torsionally de-coupled engine mount system
US7950605B2 (en) 2002-09-17 2011-05-31 Textron Innovations Inc. Torsionally de-coupled engine mount system

Also Published As

Publication number Publication date
DE1292501B (en) 1969-04-10

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