GB1435946A - Efflux conduits for aircraft jet propulsion engines - Google Patents

Efflux conduits for aircraft jet propulsion engines

Info

Publication number
GB1435946A
GB1435946A GB791573A GB791573A GB1435946A GB 1435946 A GB1435946 A GB 1435946A GB 791573 A GB791573 A GB 791573A GB 791573 A GB791573 A GB 791573A GB 1435946 A GB1435946 A GB 1435946A
Authority
GB
United Kingdom
Prior art keywords
members
divergent
nozzle
openings
variable area
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
GB791573A
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.)
British Aircraft Corp Ltd
Original Assignee
British Aircraft Corp Ltd
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 British Aircraft Corp Ltd filed Critical British Aircraft Corp Ltd
Priority to GB791573A priority Critical patent/GB1435946A/en
Publication of GB1435946A publication Critical patent/GB1435946A/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
    • F02K1/56—Reversing jet main flow
    • F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
    • 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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/11—Varying effective area of jet pipe or nozzle by means of pivoted eyelids
    • 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
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
    • F02K1/42—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet the means being movable into an inoperative position

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Joints Allowing Movement (AREA)

Abstract

1435946 Deflecting propulsion jets BRITISH AIRCRAFT CORP Ltd 13 Feb 1974 [17 Feb 1973] 7915/73 Heading B7G [Also in Division F1] An aircraft jet propulsion engine comprises a discharge duct having a first variable area nozzle and downstream thereof a second variable area nozzle, the two nozzles being arranged so that they may form a single divergent outlet duct. The discharge duct 3 comprises a first variable area nozzle 4 comprising series of flap members 5, 5b pivotally mounted at their upstream ends. A second variable area nozzle is disposed downstream of the first nozzle 4 and comprises a pair of pivotally mounted eyelid-like members 6 and 7. Each eyelid member comprises a pair of members 8 and 9 mounted on a common pivotal axis 10, the member 8 having an inner surface 12 and an outer part-spherical surface 11, and the member 9 having an inner surface comprising a part-spherical surface 13 and a surface 14. The member 9 is formed with openings 17, also with an outer guide member 20. The members 8 and 9 are relatively movable-in a first position Fig. 1, the members next together the surfaces 12 and 14 of the two members co-operating to define a common divergent surface generally aligned with a divergent surface 2 on fixed nozzle structure. In this position the openings 17 in the member 9 are closed by the member 8. The flap members 4a, 4c of the first nozzle 4 when moved to the divergent position are in alignment with the divergent surfaces 2, 12 and 14. The downstream portions of the members 9 are formed with toothed portions 18 and constitute noise suppression members. In Fig. 2 the members 9 have been moved relatively to the members 8, the openings 17 now being unobstructed whereby gas flows therethrough; the tooth portions 18 also co-operate to form a corrugated outletthis is the noise suppression position adopted at aircraft take-off. In Fig. 3 the eyelid members 8 and 9 are moved to a reverse thrust position, the tooth portion 18 being spaced to permit inter-digitation whereby the outlet is closed off and the gases discharge through lateral openings 23.
GB791573A 1973-02-17 1973-02-17 Efflux conduits for aircraft jet propulsion engines Expired GB1435946A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB791573A GB1435946A (en) 1973-02-17 1973-02-17 Efflux conduits for aircraft jet propulsion engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB791573A GB1435946A (en) 1973-02-17 1973-02-17 Efflux conduits for aircraft jet propulsion engines

Publications (1)

Publication Number Publication Date
GB1435946A true GB1435946A (en) 1976-05-19

Family

ID=9842241

Family Applications (1)

Application Number Title Priority Date Filing Date
GB791573A Expired GB1435946A (en) 1973-02-17 1973-02-17 Efflux conduits for aircraft jet propulsion engines

Country Status (1)

Country Link
GB (1) GB1435946A (en)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2525689A1 (en) * 1982-04-26 1983-10-28 Szuminski Gary TURBOMACHINE NOZZLE WITH PUSH INVERTER
EP0180534A1 (en) * 1984-11-02 1986-05-07 United Technologies Corporation Two dimensional gas turbine engine exhaust nozzle
EP0281494A1 (en) * 1987-02-27 1988-09-07 United Technologies Corporation Exhaust nozzle flap assembly
GB2224473A (en) * 1987-05-06 1990-05-09 Astech S A Jet-engine thrust-reversers
US4966327A (en) * 1988-10-27 1990-10-30 The Dee Howard Company Jet engine provided with a thrust reverser
US5192023A (en) * 1988-10-27 1993-03-09 The Dee Howard Company Jet engine provided with a thrust reverser
FR2697292A1 (en) * 1992-10-27 1994-04-29 Hurel Dubois Avions Power inverter for jet engine - Has inverter gate, leaving escape channel for direct flow, when in inverted position
US5310117A (en) * 1988-10-27 1994-05-10 The Dee Howard Company Jet engine provided with a thrust reverser
FR2755729A1 (en) * 1996-11-12 1998-05-15 Fage Etienne Twin flow gas turbine engine
EP0868596A1 (en) * 1996-10-18 1998-10-07 Northrop Grumman Corporation Sound suppressor exhaust structure
GB2372729A (en) * 2001-03-03 2002-09-04 Rolls Royce Plc Thrust reverser arrangement with means for reducing noise
US8443931B2 (en) 2011-04-06 2013-05-21 Lockheed Martin Corporation Noise reduction of supersonic jet engines
FR3010453A1 (en) * 2013-09-10 2015-03-13 Snecma REAR BODY OF TURBOJET ENGINE COMPRISING A PIPE EQUIPPED WITH A PUSH REVERSING SYSTEM WHICH INTEGRATS A CROWN OF ANTI-BREAKING CHEVRONS
CN110080907A (en) * 2019-04-19 2019-08-02 南京航空航天大学 A kind of outlet has the venturi offset fluidic vectoring nozzle of zigzag solid tab
FR3105989A1 (en) * 2020-01-02 2021-07-09 Safran Nacelles Door thrust reverser comprising at least one deflection opening leading to a cylinder housing
CN114718757A (en) * 2022-03-23 2022-07-08 西北工业大学 Design scheme of tail spray pipe of micro turbojet engine

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2525689A1 (en) * 1982-04-26 1983-10-28 Szuminski Gary TURBOMACHINE NOZZLE WITH PUSH INVERTER
EP0180534A1 (en) * 1984-11-02 1986-05-07 United Technologies Corporation Two dimensional gas turbine engine exhaust nozzle
US4753392A (en) * 1984-11-02 1988-06-28 United Technologies Corporation Two dimensional gas turbine engine exhaust nozzle
EP0281494A1 (en) * 1987-02-27 1988-09-07 United Technologies Corporation Exhaust nozzle flap assembly
GB2224473A (en) * 1987-05-06 1990-05-09 Astech S A Jet-engine thrust-reversers
GB2224473B (en) * 1987-05-06 1992-12-02 Astech S A Jet-engine thrust-reversers
US4966327A (en) * 1988-10-27 1990-10-30 The Dee Howard Company Jet engine provided with a thrust reverser
US5192023A (en) * 1988-10-27 1993-03-09 The Dee Howard Company Jet engine provided with a thrust reverser
US5310117A (en) * 1988-10-27 1994-05-10 The Dee Howard Company Jet engine provided with a thrust reverser
FR2697292A1 (en) * 1992-10-27 1994-04-29 Hurel Dubois Avions Power inverter for jet engine - Has inverter gate, leaving escape channel for direct flow, when in inverted position
EP0868596A4 (en) * 1996-10-18 2000-04-19 Northrop Grumman Corp Sound suppressor exhaust structure
EP0868596A1 (en) * 1996-10-18 1998-10-07 Northrop Grumman Corporation Sound suppressor exhaust structure
FR2755729A1 (en) * 1996-11-12 1998-05-15 Fage Etienne Twin flow gas turbine engine
US5956939A (en) * 1996-11-12 1999-09-28 Fage; Etienne Bypass jet engine with confluent nozzle, rotating members which control the bypass air flow and a thrust reverser which controls the variable exhaust area
GB2372729A (en) * 2001-03-03 2002-09-04 Rolls Royce Plc Thrust reverser arrangement with means for reducing noise
US8443931B2 (en) 2011-04-06 2013-05-21 Lockheed Martin Corporation Noise reduction of supersonic jet engines
FR3010453A1 (en) * 2013-09-10 2015-03-13 Snecma REAR BODY OF TURBOJET ENGINE COMPRISING A PIPE EQUIPPED WITH A PUSH REVERSING SYSTEM WHICH INTEGRATS A CROWN OF ANTI-BREAKING CHEVRONS
WO2015036679A1 (en) * 2013-09-10 2015-03-19 Snecma Afterbody for a turbojet engine comprising a nozzle provided with a thrust reverser system that incorporates a crown of noise-reducing chevrons
US10036349B2 (en) 2013-09-10 2018-07-31 Snecma Afterbody for a turbojet engine comprising a nozzle provided with a thrust reverser system that incorporates a crown of noise-reducing chevrons
CN110080907A (en) * 2019-04-19 2019-08-02 南京航空航天大学 A kind of outlet has the venturi offset fluidic vectoring nozzle of zigzag solid tab
FR3105989A1 (en) * 2020-01-02 2021-07-09 Safran Nacelles Door thrust reverser comprising at least one deflection opening leading to a cylinder housing
CN114718757A (en) * 2022-03-23 2022-07-08 西北工业大学 Design scheme of tail spray pipe of micro turbojet engine

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee