GB1364370A - Gas turbine ducted fan engines - Google Patents

Gas turbine ducted fan engines

Info

Publication number
GB1364370A
GB1364370A GB5599572A GB5599572A GB1364370A GB 1364370 A GB1364370 A GB 1364370A GB 5599572 A GB5599572 A GB 5599572A GB 5599572 A GB5599572 A GB 5599572A GB 1364370 A GB1364370 A GB 1364370A
Authority
GB
United Kingdom
Prior art keywords
fan
indicated
shutters
air
pitch
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
GB5599572A
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of GB1364370A publication Critical patent/GB1364370A/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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/129—Cascades, i.e. assemblies of similar profiles acting in parallel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1364370 Gas turbine ducted fan engines - reverse thrust operation SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 5 Dec 1972 [7 Dec 1971] 55995/72 Heading F1J The invention relates to a gas turbine ducted fan engine in which the pitch of the fan blades 1a is reversible whereby the fan may be utilized to provide reverse thrust. The object of the invention is to ensure a continuing flow of air to the engine compressor when the fan blades are moved to reverse pitch. The engine comprises a fan 1, LP compressor 6, HP compressor 8, combustion equipment 9, HP turbine 10 and LP turbine 11. The fan is driven by the LP turbine through reduction gearing 15, and the pitch of the fan blades 1a is reversible by means indicated at 17. In normal operation air-flow from the fan is divided, one stream 5a passing to the core engine, the other stream 7a passing to the fan discharge nozzle 7. For reverse thrust operation, air enters the fan nozzle as indicated at 7b and is discharged forwardly from the fan as indicated at 3b. In accordance with the invention means are provided to increase airflow into the fan duct during reverse thrust operation and comprises a series of openings 19 formed in the wall of the fan duct 18, each opening having disposed therein a pair of shutters 20a, 20b which are movable between a closed position to prevent air-flow, and an open position to permit air-flow through the opening. The shutters 20a, 20b are angularly movable about axes (25a), (25b) respectively by means of a shaft 26 and gearing, the shafts 26 of all the openings being connected for simultaneous operation simultaneously with selection of reverse pitch of the fan blades. The shutters are formed with scoop members 32a, 32b which are directed forwardly when the shutters are moved to the open position, Fig. 4 so that airflow as indicated by arrow 34 at the lower part of Fig. 1 is re-directed as indicated by arrows 35 and 5b.
GB5599572A 1971-12-07 1972-12-05 Gas turbine ducted fan engines Expired GB1364370A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7143865A FR2162257B1 (en) 1971-12-07 1971-12-07

Publications (1)

Publication Number Publication Date
GB1364370A true GB1364370A (en) 1974-08-21

Family

ID=9087063

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5599572A Expired GB1364370A (en) 1971-12-07 1972-12-05 Gas turbine ducted fan engines

Country Status (3)

Country Link
US (1) US3824785A (en)
FR (1) FR2162257B1 (en)
GB (1) GB1364370A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3023617A1 (en) * 2014-11-21 2016-05-25 General Electric Company Gas turbine engine with adjustable flow path geometry and method of operating

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4030290A (en) * 1974-11-06 1977-06-21 The Boeing Company Jet engine thrust reverser
US4026105A (en) * 1975-03-25 1977-05-31 The Boeing Company Jet engine thrust reverser
US3981451A (en) * 1975-11-17 1976-09-21 Rohr Industries, Inc. Fan cascade thrust reverser
US5090196A (en) * 1989-07-21 1992-02-25 The Boeing Company Ducted fan type gas turbine engine power plants
US5516061A (en) * 1994-09-19 1996-05-14 Lockheed Corporation Shroud for a reversible thrust fan
US20110101158A1 (en) * 2005-03-29 2011-05-05 The Boeing Company Thrust Reversers Including Monolithic Components
US7690190B2 (en) * 2005-05-11 2010-04-06 The Boeing Company Aircraft systems including cascade thrust reversers
US7559507B2 (en) * 2005-06-27 2009-07-14 The Boeing Company Thrust reversers including locking assemblies for inhibiting deflection
US7600371B2 (en) * 2005-10-18 2009-10-13 The Boeing Company Thrust reversers including support members for inhibiting deflection
DE102011008917A1 (en) 2011-01-19 2012-07-19 Rolls-Royce Deutschland Ltd & Co Kg Aircraft gas turbine thrust reverser
US10267160B2 (en) * 2015-08-27 2019-04-23 Rolls-Royce North American Technologies Inc. Methods of creating fluidic barriers in turbine engines
US20170198658A1 (en) * 2016-01-11 2017-07-13 The Boeing Company Thrust reverser
FR3069291B1 (en) * 2017-07-24 2019-12-13 Safran Aircraft Engines SUPPLY DUCT FOR A COMPRESSOR OF A TURBOMACHINE
FR3106861B1 (en) 2020-02-03 2023-03-17 Safran Aircraft Engines Nacelle air outlet for an aircraft turbojet comprising a straightening device to promote a thrust reversal phase
FR3107932B1 (en) 2020-03-09 2022-08-12 Safran Aircraft Engines Nacelle air outlet for turbofan aircraft engine comprising a guidance device to promote a thrust reversal phase
EP4123151B1 (en) * 2021-07-20 2024-09-04 Rolls-Royce plc Variable pitch fan thrust reverser
US11840987B2 (en) * 2022-04-05 2023-12-12 General Electric Company Cascade thrust reverser assembly for a gas turbine engine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1294823B (en) * 1965-05-12 1969-05-08 Bristol Siddeley Engines Ltd Flow channel, especially with an annular cross-section, e.g. B. bypass duct of an aircraft engine
US3344604A (en) * 1965-12-14 1967-10-03 Gen Dynamics Corp Apparatus for selectively reversing the thrust of front fan jet engines
GB1190364A (en) * 1966-04-12 1970-05-06 Dowty Rotol Ltd Gas Turbine Engines
US3601992A (en) * 1970-06-10 1971-08-31 Rohr Corp Thrust reversing apparatus
GB1365491A (en) * 1971-01-02 1974-09-04 Dowty Rotol Ltd Gas turbine ducted fan engines and fans therefor
US3690562A (en) * 1971-06-23 1972-09-12 Gen Motors Corp Jet propulsion nozzle

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3023617A1 (en) * 2014-11-21 2016-05-25 General Electric Company Gas turbine engine with adjustable flow path geometry and method of operating
US9777642B2 (en) 2014-11-21 2017-10-03 General Electric Company Gas turbine engine and method of assembling the same

Also Published As

Publication number Publication date
FR2162257A1 (en) 1973-07-20
FR2162257B1 (en) 1975-02-07
DE2259235B2 (en) 1977-02-17
US3824785A (en) 1974-07-23
DE2259235A1 (en) 1973-06-20

Similar Documents

Publication Publication Date Title
GB1364370A (en) Gas turbine ducted fan engines
US3729934A (en) Gas turbine engines
US3783618A (en) Aerodynamic engine system
US4193262A (en) Gas turbine engines
US5155993A (en) Apparatus for compressor air extraction
US4052847A (en) Gas turbine engine gas flow ducts
US3736750A (en) Power plant
US5406787A (en) After-burning turbo-jet engine with a fixed geometry exhaust nozzle
FR1602162A (en)
GB1365491A (en) Gas turbine ducted fan engines and fans therefor
GB1535681A (en) Turbofan engine nacelle
GB1102571A (en) Improvements in jet propulsion power plants
GB1493049A (en) Turbofan engine
GB1069033A (en) Improvements in or relating to gas turbine jet propulsion engines
US4221114A (en) Gas turbine jet propulsion engine
GB1258331A (en)
US3059878A (en) Auxiliary air intakes for jet engines adapted for vertical take-off
GB1270434A (en) Turbofan engines
GB1415679A (en) Gas turbine engine powerplant
US5231825A (en) Method for compressor air extraction
GB1330904A (en) Gas turbine jet propulsion engines
GB1182687A (en) Improvements in or relating to Multiflow Jet Propulsion Engines
GB1321657A (en) Ducted fan gas turbine jet propulsion engine
GB1197028A (en) Thrust Reverser for Jet-Propulsion Engines
GB1452267A (en) Jet propulsion powerplant frames

Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee