GB1504290A - Gas turbine engine mounting systems - Google Patents

Gas turbine engine mounting systems

Info

Publication number
GB1504290A
GB1504290A GB4060674A GB4060674A GB1504290A GB 1504290 A GB1504290 A GB 1504290A GB 4060674 A GB4060674 A GB 4060674A GB 4060674 A GB4060674 A GB 4060674A GB 1504290 A GB1504290 A GB 1504290A
Authority
GB
United Kingdom
Prior art keywords
struts
engine
spaced points
aircraft structure
point
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
GB4060674A
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 GB4060674A priority Critical patent/GB1504290A/en
Publication of GB1504290A publication Critical patent/GB1504290A/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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1504290 Gas turbine engines: mounting on aircraft ROLLS-ROYCE Ltd 1 Aug 1975 [18 Sept 1974] 40606/74 Heading F1G [Also in Division B7] The invention relates to a system for mounting a gas turbine engine 10 on an aircraft indicated by the shaded parts 11, the system comprising a first set of struts 12, 13, 14, 15 and a second set of struts 16, 17. The struts 12, 13 lie in a common plane, the struts being connected to a common point of the aircraft structure 11, the other ends of the struts being connected to points on the engine casing such that the struts are disposed tangentially thereto. The struts 14, 15 also lie in a common plane, the struts being connected to spaced points on the aircraft structure at one end and to spaced points of the engine casing at the other end, the lines of the struts intersecting at point Y on the engine axis. The two planes containing the struts 12, 13 and 14, 15 intersect in a line XX which is perpendicular to the axis of the engine. The struts 16, 17 comprise a second set of struts, the struts being secured to a common point on the aircraft structure at one end and to spaced points on the engine casing at the other end. The struts 16, 17 lie in a common plane which lies normal to the engine axis, the point of intersection being indicated at Z. The points Y and Z are disposed at opposite sides of the centre of gravity C of the engine and equidistant therefrom. In Figs. 3 and 4 the first set of struts comprises struts 18, 19, 20, 21 the strust 18, 19, 20 lying in one plane and the strut 21 lying in a second plane, the two planes intersecting in line XX which lies normal to the engine axis. The struts 18, 19, 20 are connected at one end to three spaced points on the aircraft structure and at the other end to three spaced points on the engine casing, the struts being disposed tangentially to the casing. The struts 16, 17 of the second set of struts are similar to those of the first embodiment. In Figs. 5, 6 (not shown), the first set of struts comprises three struts (22), (23), (24) similar to struts 18, 19, 20 of the second embodiment and a fourth strut (25) of Y- form, the vertical limb of the Y being connected to a point on the aircraft structure, and the two inclined limbs of the Y being connected to spaced points on the engine casing being disposed tangentially thereto. The two planes containing the struts 22, 23, 24 and 25 intersect in a line XX which is disposed above the engine axis and normal thereto.
GB4060674A 1975-08-01 1975-08-01 Gas turbine engine mounting systems Expired GB1504290A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB4060674A GB1504290A (en) 1975-08-01 1975-08-01 Gas turbine engine mounting systems

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4060674A GB1504290A (en) 1975-08-01 1975-08-01 Gas turbine engine mounting systems

Publications (1)

Publication Number Publication Date
GB1504290A true GB1504290A (en) 1978-03-15

Family

ID=10415727

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4060674A Expired GB1504290A (en) 1975-08-01 1975-08-01 Gas turbine engine mounting systems

Country Status (1)

Country Link
GB (1) GB1504290A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2902635A1 (en) * 1978-05-22 1979-11-29 Boeing Co ENGINE SUSPENSION FOR MIXED FLOW NOZZLE ARRANGEMENTS
FR2451461A1 (en) * 1979-03-10 1980-10-10 Rolls Royce ASSEMBLY OF TURBOMACHINE ENGINE GROUP
US5409184A (en) * 1993-02-20 1995-04-25 Rolls-Royce Plc Mounting for coupling a turbofan gas turbine engine to an aircraft structure
WO1996018538A1 (en) * 1994-12-12 1996-06-20 United Technologies Corporation A mounting arrangement for a gas turbine engine
WO1996020111A1 (en) * 1994-12-23 1996-07-04 United Technologies Corporation A mounting arrangement for a gas turbine engine
FR2921900A1 (en) * 2007-10-05 2009-04-10 Aircelle Sa PROPULSIVE ASSEMBLY FOR AIRCRAFT.
FR2925016A1 (en) * 2007-12-12 2009-06-19 Snecma Sa Isostatic jet engine pylon suspension for aircraft, has front attachment with beam transversal with respect to axis, where plane formed by rods of front attachment and transmission rod are convergent in point on axis of motor or near axis
US8444084B2 (en) 2006-04-22 2013-05-21 Rolls-Royce Plc Aeroengine mounting

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4266741A (en) * 1978-05-22 1981-05-12 The Boeing Company Mounting apparatus for fan jet engine having mixed flow nozzle installation
DE2902635A1 (en) * 1978-05-22 1979-11-29 Boeing Co ENGINE SUSPENSION FOR MIXED FLOW NOZZLE ARRANGEMENTS
FR2451461A1 (en) * 1979-03-10 1980-10-10 Rolls Royce ASSEMBLY OF TURBOMACHINE ENGINE GROUP
US5409184A (en) * 1993-02-20 1995-04-25 Rolls-Royce Plc Mounting for coupling a turbofan gas turbine engine to an aircraft structure
WO1996018538A1 (en) * 1994-12-12 1996-06-20 United Technologies Corporation A mounting arrangement for a gas turbine engine
WO1996020111A1 (en) * 1994-12-23 1996-07-04 United Technologies Corporation A mounting arrangement for a gas turbine engine
US8444084B2 (en) 2006-04-22 2013-05-21 Rolls-Royce Plc Aeroengine mounting
FR2921900A1 (en) * 2007-10-05 2009-04-10 Aircelle Sa PROPULSIVE ASSEMBLY FOR AIRCRAFT.
WO2009060138A3 (en) * 2007-10-05 2009-07-02 Aircelle Sa Propulsion assembly for aircraft
RU2469917C2 (en) * 2007-10-05 2012-12-20 Эрсель Aircraft engine unit
WO2009060138A2 (en) * 2007-10-05 2009-05-14 Aircelle Propulsion assembly for aircraft
US8534597B2 (en) 2007-10-05 2013-09-17 Aircelle Propulsion assembly for aircraft
FR2925016A1 (en) * 2007-12-12 2009-06-19 Snecma Sa Isostatic jet engine pylon suspension for aircraft, has front attachment with beam transversal with respect to axis, where plane formed by rods of front attachment and transmission rod are convergent in point on axis of motor or near axis

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Legal Events

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