GB1178437A - Bypass Turbo-Jet Engine for VTOL Aircraft. - Google Patents
Bypass Turbo-Jet Engine for VTOL Aircraft.Info
- Publication number
- GB1178437A GB1178437A GB634867A GB634867A GB1178437A GB 1178437 A GB1178437 A GB 1178437A GB 634867 A GB634867 A GB 634867A GB 634867 A GB634867 A GB 634867A GB 1178437 A GB1178437 A GB 1178437A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzles
- engine
- doors
- aircraft
- jet pipes
- 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
- F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
1,178,437. Controlling aircraft. M.A.N. TURBO G.m.b.H. 9 Feb., 1967 [3 March, 1966], No. 6348/67. Addition to 1,101,042. Heading B7G. Jet pipes 17, 18 are added to the rear end of the engine claimed in Specification 1,101,042 which comprises one mixing chamber 3, 4 on each side of the engine wherein are mixed air from the LP fan 1 and exhaust gases deflected forwardly (by doors 15, 16 in the present invention), the mixed gases passing through nozzles 12, pivotable about transverse axes 11, Fig. 4, the nozzles 12 being on the underside of the mixing chambers. In the present invention, for forward flight, the doors 15, 16 may be opened so that the mixed gases pass through the jet pipes 17, 18 and variable area nozzles 19, 20, the nozzles 12 then being pivoted to a closed position wherein lip 12 forms a seal with the face 14 on the non-rotatable part 10. The doors 15, 16 may be moved by an hydraulic ram (27), Fig. 1 (not shown), and linkage 25, 26. The mixing chambers 3, 4 and the jet pipes 17, 18 may be fitted with after-burners 28, 29, 30, 31 to give additional thrust. All the nozzles 12 on one side of the engine may be pivoted by an hydraulic ram (35), Fig. 1 (not shown), and linkage (32, 33, 34). Both sets of nozzles 12 may be synchronized by a connecting shaft 36, which incorporates a clutch to allow the sets of nozzles independent movement, e.g. to produce a yawing moment on an aircraft carrying the engine. To assist in controlling the aircraft, turbine gases may be fed to a laterally tiltable nozzle 38.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DEM68613A DE1274893B (en) | 1966-03-03 | 1966-03-03 | Twin-flow turbine jet engine for aircraft taking off and landing vertically |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1178437A true GB1178437A (en) | 1970-01-21 |
Family
ID=7312690
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB634867A Expired GB1178437A (en) | 1966-03-03 | 1967-02-09 | Bypass Turbo-Jet Engine for VTOL Aircraft. |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1178437A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2188887A (en) * | 1986-04-08 | 1987-10-14 | Rolls Royce Plc | Aircraft with stowable vectorable nozzle and ejector thrust augmentation |
| US4840329A (en) * | 1986-04-08 | 1989-06-20 | Rolls-Royce Inc. | Aircraft with stowable vectorable nozzle and ejector thrust augmentation |
-
1967
- 1967-02-09 GB GB634867A patent/GB1178437A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2188887A (en) * | 1986-04-08 | 1987-10-14 | Rolls Royce Plc | Aircraft with stowable vectorable nozzle and ejector thrust augmentation |
| US4840329A (en) * | 1986-04-08 | 1989-06-20 | Rolls-Royce Inc. | Aircraft with stowable vectorable nozzle and ejector thrust augmentation |
| GB2188887B (en) * | 1986-04-08 | 1989-11-29 | Rolls Royce Plc | Aircraft with stowable vectorable nozzle and ejector thrust augmentation |
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