GB1535765A - Variable cycle turbofan engines - Google Patents

Variable cycle turbofan engines

Info

Publication number
GB1535765A
GB1535765A GB5208175A GB5208175A GB1535765A GB 1535765 A GB1535765 A GB 1535765A GB 5208175 A GB5208175 A GB 5208175A GB 5208175 A GB5208175 A GB 5208175A GB 1535765 A GB1535765 A GB 1535765A
Authority
GB
United Kingdom
Prior art keywords
fan
pass
duct
variable
gas turbine
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
GB5208175A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1535765A publication Critical patent/GB1535765A/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
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/077—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows

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)
  • Control Of Turbines (AREA)

Abstract

1535765 Gas turbine by-pass type jet engines GENERAL ELECTRIC CO 19 Dec 1975 [2 Jan 1975] 52081/75 Heading F1J In a gas turbine by-pass type jet engine, a first fan 24 delivers air to both the compressor 12 of the core engine and to a by-pass duct 48, and a second fan 26 formed as a radial extension of the blades of fan 24 delivers air to an outer by-pass duct 54, further combustion equipment being provided either at 62 as an after-burner or, Fig. 2 (not shown), at (74) in the inner by-pass duct. Also, the mixer 60 may be omitted, and a splitter (72) provided to separate the flows from duct 48 and from the turbine 16. Adjustable inlet nozzles 45, 47 may be provided for the turbines, and for the fans, e.g. 56. Variable outlet guide vanes 58 may be provided for fan 26. A variable jet nozzle may be provided.
GB5208175A 1975-01-02 1975-12-19 Variable cycle turbofan engines Expired GB1535765A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US53816775A 1975-01-02 1975-01-02

Publications (1)

Publication Number Publication Date
GB1535765A true GB1535765A (en) 1978-12-13

Family

ID=24145795

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5208175A Expired GB1535765A (en) 1975-01-02 1975-12-19 Variable cycle turbofan engines

Country Status (5)

Country Link
JP (1) JPS5924260B2 (en)
DE (1) DE2557735A1 (en)
FR (1) FR2296769A1 (en)
GB (1) GB1535765A (en)
IT (1) IT1052016B (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2262778A (en) * 1991-12-24 1993-06-30 Snecma Variable cycle propulsion engine for supersonic aircraft.
GB2305976A (en) * 1981-12-21 1997-04-23 British Aerospace Jet propulsion powerplants
CN111594316A (en) * 2020-05-11 2020-08-28 中国航发沈阳发动机研究所 Intermediary cartridge receiver assembly
CN114856856A (en) * 2022-05-06 2022-08-05 中国科学院工程热物理研究所 High-lift-limit low-oil-consumption medium bypass ratio variable cycle engine
CN115059554A (en) * 2022-06-06 2022-09-16 上海交通大学 Engine with double exhaust stages and self-adaptive thrust tail nozzle and adjusting mechanism
CN117662323A (en) * 2023-12-07 2024-03-08 中国航空发动机研究院 Modal variable turbofan engine, aircraft and flight mode switching method

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4791783A (en) * 1981-11-27 1988-12-20 General Electric Company Convertible aircraft engine
GB2165892B (en) * 1984-10-22 1988-10-26 Gen Electric Variable cycle engine
CA2091473A1 (en) * 1992-04-20 1993-10-21 Mark J. Wagner Bypass injector valve for variable cycle aircraft engines
US6948317B2 (en) * 2003-10-31 2005-09-27 General Electric Company Methods and apparatus for flade engine nozzle
US7926290B2 (en) * 2006-12-18 2011-04-19 General Electric Company Turbine engine with modulated flow fan and method of operation
CN108087149B (en) * 2016-11-22 2020-05-19 江西洪都航空工业集团有限责任公司 Turbojet engine with high thrust-weight ratio and low oil consumption
FR3097016B1 (en) 2019-06-06 2021-07-23 Safran Aircraft Engines CONFLUENCE STRUCTURE OF A PRIMARY VEIN AND A SECONDARY VEIN IN A DOUBLE-FLOW TURBOMACHINE

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB978658A (en) * 1962-05-31 1964-12-23 Rolls Royce Gas turbine by-pass engines
GB980306A (en) * 1963-05-10 1965-01-13 Rolls Royce Gas turbine engine
GB1069033A (en) * 1965-01-30 1967-05-17 Rolls Royce Improvements in or relating to gas turbine jet propulsion engines
GB1313841A (en) * 1967-01-18 1973-04-18 Secr Defence Gas turbine jet propulsion engine
US3449914A (en) * 1967-12-21 1969-06-17 United Aircraft Corp Variable flow turbofan engine
DE2149619A1 (en) * 1971-10-05 1973-04-19 Motoren Turbinen Union TURBINE JET FOR VERTICAL OR SHORT-STARTING OR LANDING AIRPLANES
DE2153929A1 (en) * 1971-10-29 1973-05-10 Motoren Turbinen Union DEVICE FOR AIR EXTRACTION FOR AIRCRAFT WITH JETS

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2305976A (en) * 1981-12-21 1997-04-23 British Aerospace Jet propulsion powerplants
GB2305976B (en) * 1981-12-21 1998-01-07 British Aerospace Jet propulsion powerplants
GB2262778A (en) * 1991-12-24 1993-06-30 Snecma Variable cycle propulsion engine for supersonic aircraft.
GB2262778B (en) * 1991-12-24 1995-05-10 Snecma Variable cycle propulsion engine for supersonic aircraft
CN111594316A (en) * 2020-05-11 2020-08-28 中国航发沈阳发动机研究所 Intermediary cartridge receiver assembly
CN114856856A (en) * 2022-05-06 2022-08-05 中国科学院工程热物理研究所 High-lift-limit low-oil-consumption medium bypass ratio variable cycle engine
CN114856856B (en) * 2022-05-06 2024-04-30 中国科学院工程热物理研究所 High-rise-limit low-oil-consumption medium-bypass-ratio variable-cycle engine
CN115059554A (en) * 2022-06-06 2022-09-16 上海交通大学 Engine with double exhaust stages and self-adaptive thrust tail nozzle and adjusting mechanism
CN117662323A (en) * 2023-12-07 2024-03-08 中国航空发动机研究院 Modal variable turbofan engine, aircraft and flight mode switching method
CN117662323B (en) * 2023-12-07 2024-06-04 中国航空发动机研究院 Modal variable turbofan engine, aircraft and flight mode switching method

Also Published As

Publication number Publication date
FR2296769B1 (en) 1982-11-19
JPS5192917A (en) 1976-08-14
DE2557735A1 (en) 1976-07-08
FR2296769A1 (en) 1976-07-30
JPS5924260B2 (en) 1984-06-08
IT1052016B (en) 1981-06-20

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Legal Events

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

Effective date: 19921219