GB2009063A - Thrust Reversers - Google Patents

Thrust Reversers

Info

Publication number
GB2009063A
GB2009063A GB7840911A GB7840911A GB2009063A GB 2009063 A GB2009063 A GB 2009063A GB 7840911 A GB7840911 A GB 7840911A GB 7840911 A GB7840911 A GB 7840911A GB 2009063 A GB2009063 A GB 2009063A
Authority
GB
United Kingdom
Prior art keywords
fan
exhaust gas
outlet
translatable
turbine engine
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.)
Granted
Application number
GB7840911A
Other versions
GB2009063B (en
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 GB7840911A priority Critical patent/GB2009063B/en
Publication of GB2009063A publication Critical patent/GB2009063A/en
Application granted granted Critical
Publication of GB2009063B publication Critical patent/GB2009063B/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
    • F02K1/566—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
    • 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
    • F02K1/74—Reversing at least one flow in relation to at least one other flow in a plural- flow engine

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

The downstream portions 32, 34 of a ducted fan, gas turbine engine 10 are translatable to open respective gaps and allow the lateral egress of exhaust gas and fan air. The fan air outlet 26 is upstream of the exhaust gas outlet 38 and the translatable fan cowl portion 32 and gas turbine engine casing 16a cooperate to reduce the fan annulus on translation. Exhaust gas passing laterally through outlet 38 enters any annular space remaining between casing 16a and cowl 32 and prevents the passage of fan air in a downstream direction. <IMAGE>
GB7840911A 1977-11-29 1978-10-17 Ducted fan gas turbine engine Expired GB2009063B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7840911A GB2009063B (en) 1977-11-29 1978-10-17 Ducted fan gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB4953577 1977-11-29
GB7840911A GB2009063B (en) 1977-11-29 1978-10-17 Ducted fan gas turbine engine

Publications (2)

Publication Number Publication Date
GB2009063A true GB2009063A (en) 1979-06-13
GB2009063B GB2009063B (en) 1982-03-03

Family

ID=26266506

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7840911A Expired GB2009063B (en) 1977-11-29 1978-10-17 Ducted fan gas turbine engine

Country Status (1)

Country Link
GB (1) GB2009063B (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2669679A1 (en) * 1990-11-28 1992-05-29 Sud Ouest Conception Aeronauti GAS EJECTION NOZZLE FOR A REACTION ENGINE AND A REACTION ENGINE EQUIPPED WITH SUCH A NOZZLE, PARTICULARLY A SEPARATE FLOW TYPE ENGINE.
US8469148B2 (en) 2010-02-22 2013-06-25 Calvidge C. Perry Ladder tray

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2669679A1 (en) * 1990-11-28 1992-05-29 Sud Ouest Conception Aeronauti GAS EJECTION NOZZLE FOR A REACTION ENGINE AND A REACTION ENGINE EQUIPPED WITH SUCH A NOZZLE, PARTICULARLY A SEPARATE FLOW TYPE ENGINE.
EP0488453A1 (en) * 1990-11-28 1992-06-03 Conception Aeronautique Du Sud Ouest Variable ejection nozzle for a jet engine
US5211008A (en) * 1990-11-28 1993-05-18 Conception Aeronautique Du Sud Ouest Gas ejection nozzle for a jet engine and a jet engine fitted with this nozzle, in particular an engine of the separate flow type
US8469148B2 (en) 2010-02-22 2013-06-25 Calvidge C. Perry Ladder tray

Also Published As

Publication number Publication date
GB2009063B (en) 1982-03-03

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Legal Events

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