GB1211923A - Thrust reverser for gas turbine jet propulsion engine - Google Patents

Thrust reverser for gas turbine jet propulsion engine

Info

Publication number
GB1211923A
GB1211923A GB41554/68A GB4155468A GB1211923A GB 1211923 A GB1211923 A GB 1211923A GB 41554/68 A GB41554/68 A GB 41554/68A GB 4155468 A GB4155468 A GB 4155468A GB 1211923 A GB1211923 A GB 1211923A
Authority
GB
United Kingdom
Prior art keywords
thrust reverser
flap
duct
flap portion
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
GB41554/68A
Inventor
Rowan Herbert Colley
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 GB41554/68A priority Critical patent/GB1211923A/en
Priority to FR6928714A priority patent/FR2016637A1/fr
Priority to US852833A priority patent/US3608314A/en
Priority to DE1943403A priority patent/DE1943403C3/en
Publication of GB1211923A publication Critical patent/GB1211923A/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)
  • Control Of Turbines (AREA)

Abstract

1,211,923. Thrust reverser. ROLLS-ROYCE Ltd. 30 Aug., 1968, No. 41554/68. Heading B7G. A thrust reverser for a ducted fan gas turbine engine 10 comprises an annular duct 16 formed by the inner surface 20 of a cylindrical fan cowl 14 enclosing the surface 18 of the upstream portion of the engine casing and a plurality of circumferentially: spaced flaps 28 which are movable from an inoperative first position in which they lie in a circumferentially extending opening 22a of a passage 22 in the cowl 14 thereby providing part of the surface 20 to an operative second position shown by broken lines in Fig. 2 in which they at least partially block duct 16. Each flap 28 comprises a front flap portion 30 having an extension arm 34 which carries at its end a roller 36 which slidably engages a slot 38 in a rear flap portion 32 which is pivotally connected at its other end to a rearwardly displaceable fairing 24 and at a point 50 intermediate its length to the front flap portion 30. To effect thrust reversal hydraulic jacks 26 displace fairing 24 rearwards and in so doing by means of each of the linkages 46 and 34 moves each flap 28 to its second position wherein the front flap portion 30 lies forward of the rear portion 32, said flap portions deflecting pressure air delivered by a fan 12 along duet 16 into the passage 22 through which the air is guided by cascades of guide vanes 52. The thrust reverser may be employed to forwardly direct engine jet efflux, the duct being defined by a tail bullet and engine casing.
GB41554/68A 1968-08-30 1968-08-30 Thrust reverser for gas turbine jet propulsion engine Expired GB1211923A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB41554/68A GB1211923A (en) 1968-08-30 1968-08-30 Thrust reverser for gas turbine jet propulsion engine
FR6928714A FR2016637A1 (en) 1968-08-30 1969-08-21
US852833A US3608314A (en) 1968-08-30 1969-08-25 Thrust reverser
DE1943403A DE1943403C3 (en) 1968-08-30 1969-08-26 Thrust reverser for «in gas turbine jet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB41554/68A GB1211923A (en) 1968-08-30 1968-08-30 Thrust reverser for gas turbine jet propulsion engine

Publications (1)

Publication Number Publication Date
GB1211923A true GB1211923A (en) 1970-11-11

Family

ID=10420236

Family Applications (1)

Application Number Title Priority Date Filing Date
GB41554/68A Expired GB1211923A (en) 1968-08-30 1968-08-30 Thrust reverser for gas turbine jet propulsion engine

Country Status (4)

Country Link
US (1) US3608314A (en)
DE (1) DE1943403C3 (en)
FR (1) FR2016637A1 (en)
GB (1) GB1211923A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3012027A1 (en) * 1979-03-30 1980-10-09 Gen Electric DRAWER REVERSE FOR GAS TURBINE ENGINES
US9759158B2 (en) 2006-10-12 2017-09-12 United Technologies Corporatio Dual function cascade integrated variable area fan nozzle and thrust reverser

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1304869A (en) * 1970-10-20 1973-01-31
US3736750A (en) * 1971-03-12 1973-06-05 Rolls Royce Power plant
US3941313A (en) * 1972-03-06 1976-03-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Jet engine nacelle with drag augmenter auxiliary for thrust-reverser system
GB1424193A (en) * 1972-03-21 1976-02-11 Rolls Royce Gas turbine ducted fan engines
US3831376A (en) * 1973-02-05 1974-08-27 Boeing Co Thrust reverser
US4030291A (en) * 1976-01-02 1977-06-21 General Electric Company Thrust reverser for a gas turbofan engine
GB1545089A (en) * 1976-09-11 1979-05-02 Rolls Royce Jet engine thrust reverser and cowl structure
US4373328A (en) * 1980-10-22 1983-02-15 United Technologies Corporation Thrust reverser
US4382551A (en) * 1981-05-18 1983-05-10 United Technologies Corporation Flap-type nozzle with built-in reverser
US4690329A (en) * 1984-11-02 1987-09-01 United Technologies Corporation Exhaust nozzle coupled with reverser exhaust door
US4767055A (en) * 1987-03-27 1988-08-30 United Technologies Corporation Method and linkage for positioning a convergent flap and coaxial arc valve
US4922711A (en) * 1988-06-10 1990-05-08 The Boeing Company Thrust reversing system for high bypass fan engines
FR2907170B1 (en) * 2006-10-11 2008-12-12 Aircelle Sa THRUST INVERTER WITH GRIDS FOR REACTION ENGINE
FR2933144B1 (en) * 2008-06-26 2012-08-17 Airbus France NACELLE FOR AN AIRCRAFT COMPRISING INVERTER PUSHING MEANS AND AIRCRAFT COMPRISING AT LEAST ONE SUCH NACELLE
FR2966883B1 (en) * 2010-11-03 2012-11-02 Aircelle Sa INVERSION DEVICE FOR PUSHING WITHOUT BUCKLE IN THE VEIN
FR3011820B1 (en) * 2013-10-11 2017-03-31 Aircelle Sa NACELLE FOR AIRCRAFT ENGINE WITH VARIABLE SECTION TUBE
US10648427B2 (en) 2014-12-15 2020-05-12 United Technologies Corporation Gas turbine engine and thrust reverser assembly therefore
US10844807B2 (en) * 2018-06-27 2020-11-24 Spirit Aerosystems, Inc. System including hidden drag link assembly for actuating blocker door of thrust reverser
US10794328B2 (en) 2018-07-06 2020-10-06 Rohr, Inc. Thrust reverser with blocker door folding linkage

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3012027A1 (en) * 1979-03-30 1980-10-09 Gen Electric DRAWER REVERSE FOR GAS TURBINE ENGINES
US9759158B2 (en) 2006-10-12 2017-09-12 United Technologies Corporatio Dual function cascade integrated variable area fan nozzle and thrust reverser
US10677192B2 (en) 2006-10-12 2020-06-09 Raytheon Technologies Corporation Dual function cascade integrated variable area fan nozzle and thrust reverser
US11499502B2 (en) 2006-10-12 2022-11-15 Raytheon Technologies Corporation Dual function cascade integrated variable area fan nozzle and thrust reverser

Also Published As

Publication number Publication date
DE1943403A1 (en) 1970-04-23
FR2016637A1 (en) 1970-05-08
DE1943403B2 (en) 1973-12-20
US3608314A (en) 1971-09-28
DE1943403C3 (en) 1974-07-25

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PLE Entries relating assignments, transmissions, licences in the register of patents
PCNP Patent ceased through non-payment of renewal fee