GB1360238A - Ducted fan gas turbine power plants - Google Patents

Ducted fan gas turbine power plants

Info

Publication number
GB1360238A
GB1360238A GB1417171A GB1417171A GB1360238A GB 1360238 A GB1360238 A GB 1360238A GB 1417171 A GB1417171 A GB 1417171A GB 1417171 A GB1417171 A GB 1417171A GB 1360238 A GB1360238 A GB 1360238A
Authority
GB
United Kingdom
Prior art keywords
door
duct
inner door
gas turbine
fan
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
GB1417171A
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
Priority to GB1417171A priority Critical patent/GB1360238A/en
Publication of GB1360238A publication Critical patent/GB1360238A/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
    • F02K1/66—Reversing fan flow using reversing fan blades

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

1360238 Gas turbine ducted fan engines DEFENCE SECRETARY OF STATE FOR 17 July 1972 [6 May 1971] 14171/71 Heading F1J A gas turbine ducted fan engine comprises a duct having an air inlet controlled by a pivotally mounted door, the door being responsive to the direction of air flow through the duct and movable from an inoperative position in which it forms part of the wall of the duct to an operative position in which it opens the air inlet. The engine shown comprises a front fan 16 mounted within a duct 15 the fan blades being of reversible pitch for use in aircraft braking. The duct 15 is formed with openings 10 each controlled by a door assembly comprising an inner door 17 and an outer door 18. The inner door is pivotally mounted about an axis 23 inclined at about 5 degrees to the longitudinal axis of the engine, and the outer door 18 is connected to the inner door by a pair of brackets 26, 27. In the closed position, the inner door 17 engages a seal 28 extending around the opening 10, while in the open position the inner door abuts against a stop 25 on the centre structure; the outer door moves with the inner door. In the open position air flows through the inlets 10 and passes forwardly through the fan duct to exert a rearward thrust on the aircraft. The doors open automatically when reverse thrust is selected due to the reduced pressure then prevailing within the duct. In a second embodiment the inner and outer doors inter-engage by means of gear segments 43, 42, the outer doors being pivotally mounted at 40 at their centres.
GB1417171A 1972-07-17 1972-07-17 Ducted fan gas turbine power plants Expired GB1360238A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1417171A GB1360238A (en) 1972-07-17 1972-07-17 Ducted fan gas turbine power plants

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1417171A GB1360238A (en) 1972-07-17 1972-07-17 Ducted fan gas turbine power plants

Publications (1)

Publication Number Publication Date
GB1360238A true GB1360238A (en) 1974-07-17

Family

ID=10036293

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1417171A Expired GB1360238A (en) 1972-07-17 1972-07-17 Ducted fan gas turbine power plants

Country Status (1)

Country Link
GB (1) GB1360238A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4527391A (en) * 1982-09-30 1985-07-09 United Technologies Corporation Thrust reverser
GB2243876A (en) * 1990-05-11 1991-11-13 Gen Electric Automatic bypass operation of gas turbine engine
FR3106861A1 (en) * 2020-02-03 2021-08-06 Safran Aircraft Engines Aircraft turbojet nacelle air outlet comprising a straightening device to promote a thrust reversal phase
FR3107932A1 (en) * 2020-03-09 2021-09-10 Safran Aircraft Engines Nacelle air outlet for a bypass aircraft turbojet engine comprising a guide device to promote a thrust reversal phase

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4527391A (en) * 1982-09-30 1985-07-09 United Technologies Corporation Thrust reverser
GB2243876A (en) * 1990-05-11 1991-11-13 Gen Electric Automatic bypass operation of gas turbine engine
US5184461A (en) * 1990-05-11 1993-02-09 General Electric Company Method and apparatus for automatic bypass operation
FR3106861A1 (en) * 2020-02-03 2021-08-06 Safran Aircraft Engines Aircraft turbojet nacelle air outlet comprising a straightening device to promote a thrust reversal phase
WO2021156036A1 (en) * 2020-02-03 2021-08-12 Safran Aircraft Engines Air outlet for an aircraft turbojet engine nacelle comprising a straightening device for supporting a reverse thrust phase
US11913404B2 (en) 2020-02-03 2024-02-27 Safran Aircraft Engines Nacelle air outlet for aircraft turbojet engine comprising a straightening device for facilitating a reverse thrust phase
FR3107932A1 (en) * 2020-03-09 2021-09-10 Safran Aircraft Engines Nacelle air outlet for a bypass aircraft turbojet engine comprising a guide device to promote a thrust reversal phase
WO2021180509A1 (en) 2020-03-09 2021-09-16 Safran Aircraft Engines Air outlet for a nacelle for an aircraft turbofan comprising a guiding device for supporting a reverse thrust phase

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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