GB1375868A - - Google Patents

Info

Publication number
GB1375868A
GB1375868A GB3206971A GB3206971A GB1375868A GB 1375868 A GB1375868 A GB 1375868A GB 3206971 A GB3206971 A GB 3206971A GB 3206971 A GB3206971 A GB 3206971A GB 1375868 A GB1375868 A GB 1375868A
Authority
GB
United Kingdom
Prior art keywords
cowl
pylon
bolted
gas turbine
rigid member
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
GB3206971A
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 filed Critical
Priority to GB3206971A priority Critical patent/GB1375868A/en
Publication of GB1375868A publication Critical patent/GB1375868A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/16—Aircraft characterised by the type or position of power plant of jet type
    • B64D27/18—Aircraft characterised by the type or position of power plant of jet type within or attached to wing

Abstract

1375868 Cowls for gas turbine power plants ROLLS-ROYCE (1971) Ltd 22 Sept 1972 [8 July 1971] 32069/71 Heading B7G A gas turbine power plant 16 has a streamlined cowl which is divided into at least two portions 22, 26, the or each division being in a plane normal to the cowl axis, and a rigid member 12 which is fixed to a vehicle, one of the cowl portions 26 is adapted for movement relative to the rigid member in directions axially of the cowl, into and out of locking engagement with the rigid member 12 and one other cowl portion 22. In the illustrated embodiment the power plant, which is a gas turbine of either the ducted fan or pure jet type, is suspended from the wing 10 of an aircraft by means of a pylon 12. The cowl portion 22 is bolted at a single point 24 to the pylon, and the remaining cowl portion 26 is slotted at the top along its full length, the walls of the slot being provided with rollers (32), Fig. 6 (not shown), which engage in slots 36 in the sides of the pylon. The engine is rigidly connected to the pylon by means of a connecting wedge 14, and the cowl portions are bolted to each other and to the pylon, nowhere is the cowl connected to the engine. When the cowl portion 26 has been bolted in position small access doors in the top thereof are opened, and the rollers (32) brought out of contact with the rails 36.
GB3206971A 1972-09-22 1972-09-22 Expired GB1375868A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3206971A GB1375868A (en) 1972-09-22 1972-09-22

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3206971A GB1375868A (en) 1972-09-22 1972-09-22

Publications (1)

Publication Number Publication Date
GB1375868A true GB1375868A (en) 1974-11-27

Family

ID=10332710

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3206971A Expired GB1375868A (en) 1972-09-22 1972-09-22

Country Status (1)

Country Link
GB (1) GB1375868A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4043522A (en) * 1975-12-22 1977-08-23 The Boeing Company Common pod for housing a plurality of different turbofan jet propulsion engines
GB2225060A (en) * 1988-09-28 1990-05-23 Short Brothers Plc Ducted fan turbine engine
WO1994016945A1 (en) * 1993-01-26 1994-08-04 Short Brothers Plc An aircraft propulsive power unit
US6179249B1 (en) * 1996-12-26 2001-01-30 Aerospatiale Societe Nationale Industrielle Turbojet pod with laminar flow
EP1918203A1 (en) * 2006-10-31 2008-05-07 Airbus Espana, S.L. Tail cone for aircraft with movable fairing and support structure for auxiliary power unit and the ancillary elements thereof
FR2916737A1 (en) * 2007-06-01 2008-12-05 Airbus France Sas AIRCRAFT ENGINE ASSEMBLY WITH SLIDING CARGO.
JP2012510021A (en) * 2008-11-26 2012-04-26 エムアールエイ・システムズ・インコーポレイテッド Nacelle and assembly method thereof
WO2019122753A1 (en) * 2017-12-22 2019-06-27 Safran Nacelles Nacelle for turbojet engine, comprising openings of front cowls for access to fixing points of the nacelle

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4043522A (en) * 1975-12-22 1977-08-23 The Boeing Company Common pod for housing a plurality of different turbofan jet propulsion engines
GB2225060A (en) * 1988-09-28 1990-05-23 Short Brothers Plc Ducted fan turbine engine
US5136839A (en) * 1988-09-28 1992-08-11 Short Brothers Plc Ducted fan turbine engine
GB2225060B (en) * 1988-09-28 1993-03-24 Short Brothers Plc Ducted fan turbine engine
WO1994016945A1 (en) * 1993-01-26 1994-08-04 Short Brothers Plc An aircraft propulsive power unit
GB2274490B (en) * 1993-01-26 1996-09-18 Short Brothers Plc An aircraft propulsive power unit
US5609313A (en) * 1993-01-26 1997-03-11 Short Brothers Plc Aircraft propulsive power unit
US6179249B1 (en) * 1996-12-26 2001-01-30 Aerospatiale Societe Nationale Industrielle Turbojet pod with laminar flow
EP1918203A1 (en) * 2006-10-31 2008-05-07 Airbus Espana, S.L. Tail cone for aircraft with movable fairing and support structure for auxiliary power unit and the ancillary elements thereof
FR2916737A1 (en) * 2007-06-01 2008-12-05 Airbus France Sas AIRCRAFT ENGINE ASSEMBLY WITH SLIDING CARGO.
JP2012510021A (en) * 2008-11-26 2012-04-26 エムアールエイ・システムズ・インコーポレイテッド Nacelle and assembly method thereof
WO2019122753A1 (en) * 2017-12-22 2019-06-27 Safran Nacelles Nacelle for turbojet engine, comprising openings of front cowls for access to fixing points of the nacelle
FR3075886A1 (en) * 2017-12-22 2019-06-28 Safran Nacelles TURBOJET NACELLE COMPRISING HOOD OPENINGS BEFORE ACCESSING NACELLE FASTENING POINTS
US11454194B2 (en) 2017-12-22 2022-09-27 Safran Nacelles Nacelle for turbojet engine, comprising openings of front cowls for access to fixing points of the nacelle

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Legal Events

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