GB1116779A - Gas turbine jet propulsion engine - Google Patents

Gas turbine jet propulsion engine

Info

Publication number
GB1116779A
GB1116779A GB5252066A GB5252066A GB1116779A GB 1116779 A GB1116779 A GB 1116779A GB 5252066 A GB5252066 A GB 5252066A GB 5252066 A GB5252066 A GB 5252066A GB 1116779 A GB1116779 A GB 1116779A
Authority
GB
United Kingdom
Prior art keywords
duct
turbine
fan
thrust
flow
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
GB5252066A
Inventor
Brian Wrigley
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 GB5252066A priority Critical patent/GB1116779A/en
Publication of GB1116779A publication Critical patent/GB1116779A/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
    • 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
    • F02K1/56—Reversing jet main flow
    • F02K1/566—Reversing jet main flow by blocking the rearward discharge by means of a translatable member
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

1,116,779. Deflecting propulsive gases. ROLLS-ROYCE Ltd. 23 Nov., 1966, No. 52520/66. Heading B7G. [Also in Division F1] A gas turbine jet propulsion engine comprises a main flow duct in which are disposed compressor means, combustion equipment, turbine means and an exhaust duct, a second annular flow duct which surrounds the main duct and is adapted to receive air under pressure from a rotor stage of the engine, the turbine means being drivingly connected to the rotor stage. Thrust spoiling means are. located in the exhaust duct and are movable between an inoperative position in which the flow of jet gases through the exhaust duct is substantially unaffected, and a thrust spoiling position in which the pressure in the exhaust duct is reduced so as to increase the speed of rotation of the rotor stage. A thrust reverser is provided at the downstream end of the second flow duct. The engine shown comprises a fan 14, a main duct 11 in which are disposed a compressor 15, combustion equipment 15a, turbine 16 and jet pipe 17, and a fan duct 12 surrounding the main duct, the fan supplying air to the main duct and to the fan duct. The downstream end portion 28 of the inner casing 18 is axially movable by means of actuators 29 between the positions shown in. full lines and in broken lines. In the latter position an opening 32 is formed in the duct wall and the turbine exhaust gases discharge laterally through the opening, this being a thrust spoiling arrangement, The pressure downstream of the turbine is thereby reduced so that the speed of the turbine and thus of the fan 14 driven thereby is increased. A thrust reversing device 24 is disposed at the downstream end of the outer casing 19 and is moved from the retracted position shown in full lines to the operative position shown in broken lines by means of actuators 25 simultaneously with the movement of the casing portion 28 to the thrust spoiling position. Thus the flow of air through the fan duct 12 is increased when the thrust reverser is operative so increasing the braking effect.
GB5252066A 1966-11-23 1966-11-23 Gas turbine jet propulsion engine Expired GB1116779A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB5252066A GB1116779A (en) 1966-11-23 1966-11-23 Gas turbine jet propulsion engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5252066A GB1116779A (en) 1966-11-23 1966-11-23 Gas turbine jet propulsion engine

Publications (1)

Publication Number Publication Date
GB1116779A true GB1116779A (en) 1968-06-12

Family

ID=10464230

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5252066A Expired GB1116779A (en) 1966-11-23 1966-11-23 Gas turbine jet propulsion engine

Country Status (1)

Country Link
GB (1) GB1116779A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0315524A1 (en) * 1987-11-05 1989-05-10 HISPANO-SUIZA Société anonyme dite: Cascade-type thrust reverser for a jet engine, combined with a variable outlet area nozzle
US7955048B2 (en) 2006-08-25 2011-06-07 Alstom Technology Ltd. Steam turbines
EP3412902A1 (en) * 2017-06-09 2018-12-12 United Technologies Corporation Gas turbine with moveable exhaust plug
US10570852B2 (en) 2017-09-21 2020-02-25 United Technologies Corporation Moveable exhaust plug liner

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0315524A1 (en) * 1987-11-05 1989-05-10 HISPANO-SUIZA Société anonyme dite: Cascade-type thrust reverser for a jet engine, combined with a variable outlet area nozzle
FR2622929A1 (en) * 1987-11-05 1989-05-12 Hispano Suiza Sa DRIVE INVERTER OF GRID TURBOREACTOR, WITH VARIABLE EJECTION SECTION
US4922713A (en) * 1987-11-05 1990-05-08 Societe Anonyme Dite Hispano-Suiza Turbojet engine thrust reverser with variable exhaust cross-section
US7955048B2 (en) 2006-08-25 2011-06-07 Alstom Technology Ltd. Steam turbines
EP3412902A1 (en) * 2017-06-09 2018-12-12 United Technologies Corporation Gas turbine with moveable exhaust plug
US10570852B2 (en) 2017-09-21 2020-02-25 United Technologies Corporation Moveable exhaust plug liner

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