GB735645A - Improvements relating to aircraft reaction propulsion units and installations - Google Patents
Improvements relating to aircraft reaction propulsion units and installationsInfo
- Publication number
- GB735645A GB735645A GB1615752A GB1615752A GB735645A GB 735645 A GB735645 A GB 735645A GB 1615752 A GB1615752 A GB 1615752A GB 1615752 A GB1615752 A GB 1615752A GB 735645 A GB735645 A GB 735645A
- Authority
- GB
- United Kingdom
- Prior art keywords
- installations
- gas flow
- improvements relating
- propulsion units
- guide vanes
- 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
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/56—Reversing jet main flow
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
735,645. Jet propulsion plant. ROLLSROYCE, Ltd. Sept. 24, 1953 [June 26, 1952], No. 16157/52. Class 110 (3). [Also in Group XXXIII] Part of the wall of the jet pipe 13 is defined by the inner edges of a series of axially-spaced annular or part annular guide vanes 15 of concave section the inner edges being directed upstream relative to the gas flow and the outer edges being directed forwardly with respect to the direction of flight. Compressed air from the engine may be supplied by a pipe 28 to a body 22 with outlets to direct radial air streams towards the guide vanes to induce a gas flow therethrough. The fairing surrounding the vanes is provided with ports 19 which may be opened or closed by a ported sleeve 20 operable by gearing 25, 26.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1615752A GB735645A (en) | 1952-06-26 | 1952-06-26 | Improvements relating to aircraft reaction propulsion units and installations |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1615752A GB735645A (en) | 1952-06-26 | 1952-06-26 | Improvements relating to aircraft reaction propulsion units and installations |
Publications (1)
Publication Number | Publication Date |
---|---|
GB735645A true GB735645A (en) | 1955-08-24 |
Family
ID=10072191
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1615752A Expired GB735645A (en) | 1952-06-26 | 1952-06-26 | Improvements relating to aircraft reaction propulsion units and installations |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB735645A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2865169A (en) * | 1956-02-15 | 1958-12-23 | United Aircraft Corp | Jet exhaust nozzle |
US3031156A (en) * | 1957-11-08 | 1962-04-24 | Bristol Siddeley Engines Ltd | Exhaust systems for jet propulsion engines |
US3224190A (en) * | 1959-02-11 | 1965-12-21 | Daimler Benz Ag | Jet power plant particularly for aircraft |
-
1952
- 1952-06-26 GB GB1615752A patent/GB735645A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2865169A (en) * | 1956-02-15 | 1958-12-23 | United Aircraft Corp | Jet exhaust nozzle |
US3031156A (en) * | 1957-11-08 | 1962-04-24 | Bristol Siddeley Engines Ltd | Exhaust systems for jet propulsion engines |
US3224190A (en) * | 1959-02-11 | 1965-12-21 | Daimler Benz Ag | Jet power plant particularly for aircraft |
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