GB744473A - Improvements in or relating to aircraft or self-propelled missiles - Google Patents

Improvements in or relating to aircraft or self-propelled missiles

Info

Publication number
GB744473A
GB744473A GB26335/52A GB2633552A GB744473A GB 744473 A GB744473 A GB 744473A GB 26335/52 A GB26335/52 A GB 26335/52A GB 2633552 A GB2633552 A GB 2633552A GB 744473 A GB744473 A GB 744473A
Authority
GB
United Kingdom
Prior art keywords
engine
projections
radial
housing
slots
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
GB26335/52A
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.)
Bristol Siddeley Engines Ltd
Original Assignee
De Havilland Engine Co Ltd
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 De Havilland Engine Co Ltd filed Critical De Havilland Engine Co Ltd
Priority to GB26335/52A priority Critical patent/GB744473A/en
Publication of GB744473A publication Critical patent/GB744473A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • 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
    • B64D39/00—Refuelling during flight
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)

Abstract

744,473. Gas turbine plant. DE HAVILLAND ENGINE CO., Ltd., HALFORD, F. B.. and GLASS. B. G. Nov. 6. 1953 [Oct. 20, 1952], No. 26335/52. Class 110(3) A gas turbine engine is mounted in an aircraft or self-propelied missile including a tubular housing formed as a complete annular unit or in two parts separable in an approximately diametric plane by means of two annular or arch-like axially spaced. supports connected to or forming part .of the housing and extending around the axis of. the engine completely or over an arc of .substantially 180 degrees, the connection between the engine and one support being arranged to resist axial and circumferential and bodily radial movement of the engine relative to the support but permitting comparatively free radial expansion and contraction of the engine and the connection between the engine and the other support being arranged to resist circumferential and bodily radial movement but permitting comparatively free axial movement and radial expansion and contraction of the engine. The engine A is supported in the housing B by means of two supports B<SP>1</SP>, B<SP>4</SP> attached to the housing and rings A<SP>2</SP>, A' attached to the engine. The ring A<SP>2</SP> is attached to the support B' by a number of radial pins C which engage co-axial sockets B<SP>2</SP>, A<SP>4</SP>. If desired, the pins may be mounted in resilient bushes mounted in the socket B<SP>2</SP>. The ring A<SP>3</SP> has a number of projections A<SP>5</SP> which engage radial open sided slots B'. In a modification, the front mounting comprises a ring rigid with the engine having projections which engage radial slots in the ring B<SP>1</SP>. These radial slots are open at the rear so that the projections on the engine may enter the slots in an axial direction when mounting the engine. The projections are retained in the slots by a ring bolted to the ring B<SP>2</SP>. In a modification of this arrangement each slot has a retaining member which is moved into and out of position by means of a radial screw. In another modification, Fig. 8, the housing B is provided with two semi-circular archshaped members J, K, of U-section. Formed in or built on to the forward face of the member J are a series of radial slots J<SP>1</SP> into which extend projections L formed on the upper half of a two part clamp- 'ing ring L<SP>2</SP>, L<SP>3</SP>. The projections are retained in the slots by a cover plate J<SP>2</SP>. The ring members L<SP>2</SP>, L' have an internal V- groove which engages a rib A<SP>6</SP> attached to the engine. The member K is similar to the member J except that the slots K' have a greater axial length than the projections .M to allow for axial expansion. In a further modification the projections on the engine are bonded to rubber bushes which are also bonded to tubular sockets attached to the housing B. In another modification the projections are replaced by an annular member which is connected to an annular housing member by annular strips of rubber. The annular member forming part of the housing may be detachable.
GB26335/52A 1952-10-20 1952-10-20 Improvements in or relating to aircraft or self-propelled missiles Expired GB744473A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB26335/52A GB744473A (en) 1952-10-20 1952-10-20 Improvements in or relating to aircraft or self-propelled missiles

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB26335/52A GB744473A (en) 1952-10-20 1952-10-20 Improvements in or relating to aircraft or self-propelled missiles

Publications (1)

Publication Number Publication Date
GB744473A true GB744473A (en) 1956-02-08

Family

ID=10242053

Family Applications (1)

Application Number Title Priority Date Filing Date
GB26335/52A Expired GB744473A (en) 1952-10-20 1952-10-20 Improvements in or relating to aircraft or self-propelled missiles

Country Status (1)

Country Link
GB (1) GB744473A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931441A (en) * 1956-09-19 1960-04-05 Westinghouse Electric Corp Jet-driven helicopter rotor
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
US5183223A (en) * 1991-06-27 1993-02-02 Rohr, Inc. Interlocking ring fan jet engine support system
EP0733545A1 (en) * 1995-03-21 1996-09-25 AEROSPATIALE Société Nationale Industrielle Turbofan with a floatury nacelle
GB2434836A (en) * 2006-02-04 2007-08-08 Rolls Royce Plc A mounting system for use in mounting a gas turbine engine

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931441A (en) * 1956-09-19 1960-04-05 Westinghouse Electric Corp Jet-driven helicopter rotor
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
US5183223A (en) * 1991-06-27 1993-02-02 Rohr, Inc. Interlocking ring fan jet engine support system
EP0733545A1 (en) * 1995-03-21 1996-09-25 AEROSPATIALE Société Nationale Industrielle Turbofan with a floatury nacelle
FR2732074A1 (en) * 1995-03-21 1996-09-27 Aerospatiale DOUBLE FLOW TURBOREACTOR WITH A FLOATING PLATFORM
US5642615A (en) * 1995-03-21 1997-07-01 Aerospatiale Societe Nationale Industrielle Turbofan engine with a floating pod
GB2434836A (en) * 2006-02-04 2007-08-08 Rolls Royce Plc A mounting system for use in mounting a gas turbine engine
GB2434836B (en) * 2006-02-04 2008-12-10 Rolls Royce Plc Mounting system for use in mounting a gas turbine engine
US7815145B2 (en) 2006-02-04 2010-10-19 Rolls-Royce Plc Mounting system for use in mounting a gas turbine engine

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