GB1345337A - Gas turbine engine having a thrust reverser - Google Patents

Gas turbine engine having a thrust reverser

Info

Publication number
GB1345337A
GB1345337A GB1345337DA GB1345337A GB 1345337 A GB1345337 A GB 1345337A GB 1345337D A GB1345337D A GB 1345337DA GB 1345337 A GB1345337 A GB 1345337A
Authority
GB
United Kingdom
Prior art keywords
chain
door
cam track
doors
gas turbine
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
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.)
UK Secretary of State for Defence
Original Assignee
UK Secretary of State for Defence
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 UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Publication of GB1345337A publication Critical patent/GB1345337A/en
Expired legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54Nozzles having means for reversing jet thrust
    • F02K1/64Reversing fan flow
    • F02K1/70Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54Nozzles having means for reversing jet thrust
    • F02K1/76Control or regulation of thrust reversers

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Transmissions By Endless Flexible Members (AREA)
  • Power-Operated Mechanisms For Wings (AREA)
  • Transmission Devices (AREA)

Abstract

1345337 Gas turbine engines having thrust reversers DEFENCE SECRETARY OF STATE FOR 28 Oct 1971 [20 Oct 1970] 49662/70 Heading B7G [Also in Division F2] A gas turbine engine, Fig. 3, has; a gas flow duct between a gas generator casing 10 and a fan cowl wall 18; a plurality of peripherally spaced blocker doors 24 which when inoperative (solid lines) block respective apertures in the wall 18 and which are each pivoted at the centre to a link 54 pivotally mounted to rigid structure upstream of the apertures and are each movably mounted at the downstream end to a mounting means, Figs. 5, 8, including a cam track 40 which the end of the door follows; and blocker door actuating means, Figs. 5, 8, whereby on actuation of the actuating means the shape of the cam track 40 causes the doors to move into or block the gas flow through the duct 14 (chain lines) so that the resultant of the force of the gas flowing through the duct 14 and the reaction force of the door mounting means tends to cause the doors to move to the inoperative position until the engine resultant thrust is zero when the direction of the resultant force reverses. The actuation means, Figs. 5, 8, is mounted in and extended downstream from a strut 26 between a pair of adjacent blocker doors 24 and comprises a ball screw 46, driven by a flexible drive 62, on which moves a yoke 48 having on each side a pin 50 or 52 forming part of a chain 30 adjacent a respective door, the chain 30 being supported by four double sprocket wheels 32 to 35. A lug mounted pin 36 of a door extends through the cam track 40, forms part of the chain 30, and, for part of its travel, is guided by a further cam track 42 of the same shape as the cam track 40. So that the chain follows the curve of the cam tracks 40, 42, further pins 44 of the chain 30 extend into the tracks. Movement of the yoke 48 causes movement of the chain 30 which causes the required movement of the door by virtue of the shape of the cam tracks 40, 42. The chassis may be alternatively driven by gears 72, 74 driving sprocket wheel 32.
GB1345337D 1970-10-20 1971-10-28 Gas turbine engine having a thrust reverser Expired GB1345337A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4966270 1970-10-20

Publications (1)

Publication Number Publication Date
GB1345337A true GB1345337A (en) 1974-01-30

Family

ID=10453118

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1345337D Expired GB1345337A (en) 1970-10-20 1971-10-28 Gas turbine engine having a thrust reverser

Country Status (2)

Country Link
FR (1) FR2111726B1 (en)
GB (1) GB1345337A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013231432A (en) * 2012-04-30 2013-11-14 Mra Systems Inc Thrust reverser assembly and method of operation
EP3034848A1 (en) * 2014-12-15 2016-06-22 United Technologies Corporation Gas turbine engine and thrust reverser assembly therefor
GB2564891A (en) * 2017-07-26 2019-01-30 Short Brothers Plc Nacelle with thrust reverser
EP3702603A1 (en) * 2019-02-28 2020-09-02 Airbus Operations GmbH Thrust reverser assembly for an engine nacelle of an aircraft
US10995701B2 (en) * 2019-09-05 2021-05-04 Rohr, Inc. Translating sleeve thrust reverser assembly

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2697292B1 (en) * 1992-10-27 1994-12-30 Hurel Dubois Avions Thrust reversing assembly for jet aircraft engine providing an axial leakage space in the reversing position and engine equipped with such an assembly.
FR2752017B1 (en) * 1996-08-01 1998-10-16 Hispano Suiza Sa TURBOREACTOR DRIVE INVERTER WITH SCOOPING DOORS

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013231432A (en) * 2012-04-30 2013-11-14 Mra Systems Inc Thrust reverser assembly and method of operation
EP3034848A1 (en) * 2014-12-15 2016-06-22 United Technologies Corporation Gas turbine engine and thrust reverser assembly therefor
US10648427B2 (en) 2014-12-15 2020-05-12 United Technologies Corporation Gas turbine engine and thrust reverser assembly therefore
GB2564891A (en) * 2017-07-26 2019-01-30 Short Brothers Plc Nacelle with thrust reverser
WO2019020995A1 (en) * 2017-07-26 2019-01-31 Short Brothers Plc Nacelle with thrust reverser
US11230994B2 (en) 2017-07-26 2022-01-25 Short Brothers Plc Nacelle with thrust reverser
EP3702603A1 (en) * 2019-02-28 2020-09-02 Airbus Operations GmbH Thrust reverser assembly for an engine nacelle of an aircraft
US11319898B2 (en) 2019-02-28 2022-05-03 Airbus Operations Gmbh Thrust reverser assembly for an engine nacelle of an aircraft
US10995701B2 (en) * 2019-09-05 2021-05-04 Rohr, Inc. Translating sleeve thrust reverser assembly

Also Published As

Publication number Publication date
DE2152031A1 (en) 1972-04-27
FR2111726A1 (en) 1972-06-09
FR2111726B1 (en) 1976-02-13
DE2152031B2 (en) 1976-04-08

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Legal Events

Date Code Title Description
PS Patent sealed
PLE Entries relating assignments, transmissions, licences in the register of patents
PCNP Patent ceased through non-payment of renewal fee