GB827744A - Improvements in or relating to apparatus for deflecting a gaseous stream flowing through an annular structure of an aircraft or aircraft engine - Google Patents
Improvements in or relating to apparatus for deflecting a gaseous stream flowing through an annular structure of an aircraft or aircraft engineInfo
- Publication number
- GB827744A GB827744A GB20983/56A GB2098356A GB827744A GB 827744 A GB827744 A GB 827744A GB 20983/56 A GB20983/56 A GB 20983/56A GB 2098356 A GB2098356 A GB 2098356A GB 827744 A GB827744 A GB 827744A
- Authority
- GB
- United Kingdom
- Prior art keywords
- jet
- turbo
- aircraft
- compressor
- ram
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
- B64C39/062—Aircraft not otherwise provided for having disc- or ring-shaped wings having annular wings
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Turbines (AREA)
Abstract
827,744. Jet propulsion plant. SOC. NATIONALE D' ETUDE ET DE CONSTRUCTION DE MOTEURS D' AVIATION. July 6, 1956 [July 12, 1955], No. 20983/56. Class 110(3). [Also in Group XXXIII] In an aircraft power plant consisting of a turbo-jet engine located concentrically within a rain-jet 1, means is provided for deflecting the gases flowing from the ram-jet and the turbojet or the gases from the ram-jet alone when the turbo-jet is inoperative. A rain-jet 1, having an air intake 2 and a jet nozzle 4, surrounds a concentrically arranged turbo-jet propulsion unit consisting of intake 5, compressor 6 and turbine 8. The rear end of the turbo-jet casing is formed into two annular manifolds 10, 11 divided by radial partitions into four compartments each supplied with compressed air from compressor 6 through a pipe 15 and a control valve 16. Each compartment of manifold 10 is provided with a slot 13 and each partition of manifold 11 has a slot 14. By this means the gases emerging from the ram-jet and the turbo-jet may be controlled directionally by selective operation of the valves 16 to produce a deflection as indicated by the arrows f and f2. At high speeds of the aircraft when the turbo-jet is not working the manifolds may be supplied with compressed air from a source other than the compressor 6.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR827744X | 1955-07-12 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB827744A true GB827744A (en) | 1960-02-10 |
Family
ID=9283438
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB20983/56A Expired GB827744A (en) | 1955-07-12 | 1956-07-06 | Improvements in or relating to apparatus for deflecting a gaseous stream flowing through an annular structure of an aircraft or aircraft engine |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB827744A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2425516A (en) * | 2005-04-29 | 2006-11-01 | Gen Electric | Jet engine thrust vectoring using fluid jets |
US7424805B2 (en) | 2005-04-29 | 2008-09-16 | General Electric Company | Supersonic missile turbojet engine |
US7448199B2 (en) | 2005-04-29 | 2008-11-11 | General Electric Company | Self powdered missile turbojet |
US7475545B2 (en) | 2005-04-29 | 2009-01-13 | General Electric Company | Fladed supersonic missile turbojet |
-
1956
- 1956-07-06 GB GB20983/56A patent/GB827744A/en not_active Expired
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2425516A (en) * | 2005-04-29 | 2006-11-01 | Gen Electric | Jet engine thrust vectoring using fluid jets |
US7424805B2 (en) | 2005-04-29 | 2008-09-16 | General Electric Company | Supersonic missile turbojet engine |
US7448199B2 (en) | 2005-04-29 | 2008-11-11 | General Electric Company | Self powdered missile turbojet |
US7475545B2 (en) | 2005-04-29 | 2009-01-13 | General Electric Company | Fladed supersonic missile turbojet |
US7509797B2 (en) | 2005-04-29 | 2009-03-31 | General Electric Company | Thrust vectoring missile turbojet |
GB2425516B (en) * | 2005-04-29 | 2010-09-15 | Gen Electric | Thrust vectoring missile turbojet |
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