GB1303875A - - Google Patents

Info

Publication number
GB1303875A
GB1303875A GB1303875DA GB1303875A GB 1303875 A GB1303875 A GB 1303875A GB 1303875D A GB1303875D A GB 1303875DA GB 1303875 A GB1303875 A GB 1303875A
Authority
GB
United Kingdom
Prior art keywords
cowl
axis
flap
fan
movement
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
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
Publication of GB1303875A publication Critical patent/GB1303875A/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
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow

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

1303875 Thrust reversers DEFENCE SECRETARY OF STATE FOR 2 April 1970 15586/70 Heading B7G A thrust reverser for a gas turbine ducted fan engine comprises a plurality of blocker flaps 30 disposed around the inner wall of the fan cowl 34 and each arranged to rotate about a respective fixed axis 38 simultaneously with a movable cowl portion 28, each blocker flap being provided with two levers 44 one end of each of which is arranged to pivot freely about the axis 38 while the other end has a roller 48 arranged to roll along an axially profiled inner surface 50 of cowl portion 28 so as to transmit a force through an abutment surface 52 to an edge of blocker flap 30 during part of its retracting movement. An axle 46 on axis 38 is carried by lever 40 fast with fixed portion 42 of the cowl so that, as cowl portion 28 is moved downstream relative to fan air flow by rams 32, links 36 cause flaps 30 to move to close the duct between the cowl and core engine 12. This movement is assisted by the fan air which then passes out through an annular aperture 26 to provide reverse thrust. During this movement said edge of flap 30 comes into contact with abutment surface 52 and at the same time rollers 48 reach a frustoconical part 54 of said surface 50 so that levers 44 can pivot about axis 38. When it is required to move flaps 30 to open the fan duct, the forward movement of cowl portion 28 causes cam surface 54 to bear on rollers 48 thereby rocking levers 44 about axle 46 so that abutments 52 urge the respective flap over its initial deadcentre position, subsequent closing effort being exerted by rods 36.
GB1303875D 1970-04-02 1970-04-02 Expired GB1303875A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1558670 1970-04-02

Publications (1)

Publication Number Publication Date
GB1303875A true GB1303875A (en) 1973-01-24

Family

ID=10061789

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1303875D Expired GB1303875A (en) 1970-04-02 1970-04-02

Country Status (1)

Country Link
GB (1) GB1303875A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2608681A1 (en) * 1986-12-17 1988-06-24 Rolls Royce Plc PROPULSIVE FLUID ENGINE PROVIDED WITH A FLOW OUTLET CONTROL DEVICE
GB2266081A (en) * 1992-04-13 1993-10-20 Rolls Royce Plc Fluid flow duct with alternative outlets.
FR2804474A1 (en) * 2000-01-27 2001-08-03 Hispano Suiza Sa INDEXING DEVICE WITH GROOVED GRINDING DEVIATION WITH FIXED REAR STRUCTURE
FR3078112A1 (en) * 2018-02-22 2019-08-23 Airbus Operations NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER SHUTTER
EP3626959A1 (en) * 2018-07-06 2020-03-25 Rohr Inc. Thrust reverser with blocker door folding linkage
EP3696397A1 (en) * 2019-02-18 2020-08-19 Airbus Operations Turbojet nacelle comprising a locking door and a system for the deployment of the locking door

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2608681A1 (en) * 1986-12-17 1988-06-24 Rolls Royce Plc PROPULSIVE FLUID ENGINE PROVIDED WITH A FLOW OUTLET CONTROL DEVICE
GB2266081A (en) * 1992-04-13 1993-10-20 Rolls Royce Plc Fluid flow duct with alternative outlets.
GB2266081B (en) * 1992-04-13 1996-04-24 Rolls Royce Plc Fluid flow duct with alternative outlets
FR2804474A1 (en) * 2000-01-27 2001-08-03 Hispano Suiza Sa INDEXING DEVICE WITH GROOVED GRINDING DEVIATION WITH FIXED REAR STRUCTURE
EP1128052A1 (en) * 2000-01-27 2001-08-29 Hispano-Suiza Aérostructures Thrust reverser with bladed cascades and fixed rear structure
US6385964B2 (en) 2000-01-27 2002-05-14 Hispano-Suiza Aerostructures Thrust reverser having a bypass vane-cascade and fitted with a stationary rear structure
FR3078112A1 (en) * 2018-02-22 2019-08-23 Airbus Operations NACELLE OF A TURBOJET ENGINE COMPRISING AN INVERTER SHUTTER
EP3530926A1 (en) * 2018-02-22 2019-08-28 Airbus Operations S.A.S. Turbojet nacelle comprising an inverter flap
CN110182372A (en) * 2018-02-22 2019-08-30 空中客车运营简化股份公司 Double-flow turbine jet engine and its nacelle and aircraft comprising it
US11111880B2 (en) 2018-02-22 2021-09-07 Airbus Operations Sas Nacelle of a turbojet engine comprising a thrust-reversing door
CN110182372B (en) * 2018-02-22 2022-08-26 空中客车运营简化股份公司 Double-flow turbojet engine, nacelle thereof and aircraft comprising same
EP3626959A1 (en) * 2018-07-06 2020-03-25 Rohr Inc. Thrust reverser with blocker door folding linkage
EP3696397A1 (en) * 2019-02-18 2020-08-19 Airbus Operations Turbojet nacelle comprising a locking door and a system for the deployment of the locking door
FR3092819A1 (en) * 2019-02-18 2020-08-21 Airbus Operations TURBOREACTOR NACELLE CONTAINING A LOCKING DOOR AND A LOCKING DOOR DEPLOYMENT SYSTEM

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees