GB1535765A - Variable cycle turbofan engines - Google Patents
Variable cycle turbofan enginesInfo
- 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
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.
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)
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)
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)
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 |
-
1975
- 1975-12-19 GB GB5208175A patent/GB1535765A/en not_active Expired
- 1975-12-20 DE DE19752557735 patent/DE2557735A1/en not_active Withdrawn
- 1975-12-30 IT IT3083675A patent/IT1052016B/en active
- 1975-12-31 FR FR7540251A patent/FR2296769A1/en active Granted
-
1976
- 1976-01-05 JP JP2776A patent/JPS5924260B2/en not_active Expired
Cited By (10)
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 |
---|---|
IT1052016B (en) | 1981-06-20 |
JPS5924260B2 (en) | 1984-06-08 |
DE2557735A1 (en) | 1976-07-08 |
FR2296769B1 (en) | 1982-11-19 |
FR2296769A1 (en) | 1976-07-30 |
JPS5192917A (en) | 1976-08-14 |
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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 |