GB875496A - Improvements in or relating to ducted-fan gas turbine jet propulsion engines - Google Patents
Improvements in or relating to ducted-fan gas turbine jet propulsion enginesInfo
- Publication number
- GB875496A GB875496A GB4147359A GB4147359A GB875496A GB 875496 A GB875496 A GB 875496A GB 4147359 A GB4147359 A GB 4147359A GB 4147359 A GB4147359 A GB 4147359A GB 875496 A GB875496 A GB 875496A
- Authority
- GB
- United Kingdom
- Prior art keywords
- duct
- area
- nozzle
- vanes
- 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
- 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
- F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
-
- 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
- F02K1/15—Control or regulation
- F02K1/16—Control or regulation conjointly with another control
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Supercharger (AREA)
Abstract
875,496. Gas turbine jet propulsion plant. GENERAL ELECTRIC CO. Dec. 7, 1959, No. 41473/59. Class 110 (3). A ducted fan gas turbine jet propulsion engine comprising a gas turbine engine disposed within a substantially cylindrical outer casing to form a by-pass duct which is provided with combustion means and an exhaust nozzle, has control vanes to control the air flow to the gas turbine engine to permit selective operation of the engine as a ducted fan engine or as a ram jet and means to vary the configuration of the by-pass exhaust nozzle in accordance with the position of the control vanes. A compressor 10 supplies combustion air to combustion equipment 11 feeding a turbine 12 driving the compressor. The exhaust of the turbine 12 is used to drive a turbine 14 before passing through a duct 20 which terminates in a convergent nozzle 24. The turbine 14 drives fan blades 15 arranged in a duct 16 formed by a casing 17 extending around the inner casing 18. Combustion means 27 is provided in the duct 16. The compressor 10 has control vanes 13 to control the air admission to the compressor which vanes are connected through linkage 23 to an actuator 21 which moves the duct 20 axially. The duct 20 has protuberances 26 which co-operate with protuberances 25 on the casing 17 to form a variable-area nozzle. At take-off and low Mach numbers, the vanes 13 are open and the duct 20 on the position shown. Since the area at X is less than that at Y, the nozzle is convergent. At Mach numbers between 2 and 3 the fuel supply to the combustion equipment 11 is gradually reduced until it is shut off. The vanes 13 are then closed. The entire air flow now passes through duct 16 and the effective area of the propelling nozzle thereby reduced by the amount W. As the area of W is half that of X the area is reduced by one third. To further reduce the area at high Mach numbers the duct 20 is retracted so that the protuberances 25 to 26 become opposite one another which further reduces the effective throat area and also forms a convergentdivergent nozzle.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4147359A GB875496A (en) | 1959-12-07 | 1959-12-07 | Improvements in or relating to ducted-fan gas turbine jet propulsion engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB4147359A GB875496A (en) | 1959-12-07 | 1959-12-07 | Improvements in or relating to ducted-fan gas turbine jet propulsion engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB875496A true GB875496A (en) | 1961-08-23 |
Family
ID=10419848
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB4147359A Expired GB875496A (en) | 1959-12-07 | 1959-12-07 | Improvements in or relating to ducted-fan gas turbine jet propulsion engines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB875496A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2205360A (en) * | 1987-05-27 | 1988-12-07 | Mtu Muenchen Gmbh | Composite fanjet/ramjet propulsion device |
GB2243877A (en) * | 1990-03-31 | 1991-11-13 | Messerschmitt Boelkow Blohm | Adjustable nozzle for hypersonic engine combustion chamber |
US5284014A (en) * | 1991-10-16 | 1994-02-08 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation ("S.N.E.C.M.A.") | Turbojet-ramjet hypersonic aircraft engine |
WO2008045089A1 (en) * | 2006-10-12 | 2008-04-17 | United Technologies Corporation | Core cowl airfoil for a gas turbine engine |
JP2015200191A (en) * | 2014-04-04 | 2015-11-12 | 株式会社Ihi | jet engine |
CN108626025A (en) * | 2018-04-28 | 2018-10-09 | 上海啸风航空科技有限公司 | A kind of double ducts of novel microminiature are vented fanjet respectively |
US10975775B2 (en) | 2015-05-27 | 2021-04-13 | Ihi Corporation | Jet engine |
-
1959
- 1959-12-07 GB GB4147359A patent/GB875496A/en not_active Expired
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2205360A (en) * | 1987-05-27 | 1988-12-07 | Mtu Muenchen Gmbh | Composite fanjet/ramjet propulsion device |
US4909031A (en) * | 1987-05-27 | 1990-03-20 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Combined multi-speed jet engine for the drive of airplanes and space vehicles |
GB2205360B (en) * | 1987-05-27 | 1992-01-22 | Mtu Muenchen Gmbh | Composite changeover-type reaction power unit for aircraft |
GB2243877A (en) * | 1990-03-31 | 1991-11-13 | Messerschmitt Boelkow Blohm | Adjustable nozzle for hypersonic engine combustion chamber |
US5284014A (en) * | 1991-10-16 | 1994-02-08 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation ("S.N.E.C.M.A.") | Turbojet-ramjet hypersonic aircraft engine |
WO2008045089A1 (en) * | 2006-10-12 | 2008-04-17 | United Technologies Corporation | Core cowl airfoil for a gas turbine engine |
US8272204B2 (en) | 2006-10-12 | 2012-09-25 | United Technologies Corporation | Core cowl airfoil for a gas turbine engine |
JP2015200191A (en) * | 2014-04-04 | 2015-11-12 | 株式会社Ihi | jet engine |
US10975775B2 (en) | 2015-05-27 | 2021-04-13 | Ihi Corporation | Jet engine |
CN108626025A (en) * | 2018-04-28 | 2018-10-09 | 上海啸风航空科技有限公司 | A kind of double ducts of novel microminiature are vented fanjet respectively |
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