GB1110113A - Jet propulsion power plants - Google Patents
Jet propulsion power plantsInfo
- Publication number
- GB1110113A GB1110113A GB1688564A GB1688564A GB1110113A GB 1110113 A GB1110113 A GB 1110113A GB 1688564 A GB1688564 A GB 1688564A GB 1688564 A GB1688564 A GB 1688564A GB 1110113 A GB1110113 A GB 1110113A
- Authority
- GB
- United Kingdom
- Prior art keywords
- duct
- fan
- engine
- exhaust
- 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
- 239000007789 gas Substances 0.000 abstract 10
- 238000007599 discharging Methods 0.000 abstract 3
- 230000001141 propulsive effect Effects 0.000 abstract 1
Classifications
-
- 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
- B64C29/0066—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 with horizontal jet and jet deflector
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Turbines (AREA)
Abstract
1,110,113. Deflecting propulsive jets. BRISTOL SIDDELEY ENGINES. 22 April, 1965 [23 April, 1964; 14 May, 1964], No. 16885/64. Heading B7G. [Also in Division F1] An aircraft gas turbine jet propulsion power plant comprises a gas turbine engine, a ducted fan supported for rotation about an axis parallel to that of the engine, the fan being driven by a turbine mounted on the fan shaft, there being a main duct for the exhaust from the engine, a second duct in which the fan drive turbine is disposed, and third duct in which the fan is disposed, valve means whereby the exhaust gases from the gas turbine engine may be passed either to the exhaust duct or to the second duct, valve means for closing the inlet to the third duct, and means for varying the direction of discharge from the outlet of the third duct in relation to the direction of discharge from the main duct. In Fig. 1 the gas turbine engine 110 comprises an exhaust duct 112 terminating in a propulsion nozzle 113. A turbine driven fan assembly is disposed along each side of the engine, each assembly comprising a turbine 115 which drives a fan 114 through shaft 116. The exhaust duct 112 of the engine 110 is formed with lateral openings 119 which are controlled by valve members 120 so that the exhaust gases from the engine may pass straight to the propulsion nozzle 113 as shown at the upper part of the Figure or so that the exhaust duct 112 is shut off, the exhaust gases then discharging through the lateral openings 119 to the ducts 125 so driving the turbines 115 as shown at the lower part of the Figure. The exhaust gases discharging from the turbines 115 pass through ducts 131 which terminate in nozzles 132 which are angularly adjustable so that the gases may be discharged rearwardly for forward propulsion, downwardly for vertical lift or forwardly for braking. The fan 114 is disposed in a duct 126 the intake of which may be closed by means of a valve member 127 and the fan discharges through a duct 128 which terminates in an angularly adjustable nozzle 129. In a second embodiment the fan duct extends to an annular duct disposed around the exhaust duct of the turbine 115, the fan air and turbine exhaust gases discharging together through an angularly adjustable nozzle.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1688564A GB1110113A (en) | 1964-04-23 | 1964-04-23 | Jet propulsion power plants |
| DE1965B0081544 DE1294222B (en) | 1964-04-23 | 1965-04-21 | Vertical take off and landing aircraft |
| BE662922D BE662922A (en) | 1964-04-23 | 1965-04-22 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1688564A GB1110113A (en) | 1964-04-23 | 1964-04-23 | Jet propulsion power plants |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1110113A true GB1110113A (en) | 1968-04-18 |
Family
ID=10085435
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1688564A Expired GB1110113A (en) | 1964-04-23 | 1964-04-23 | Jet propulsion power plants |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1110113A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2263505A (en) * | 1980-10-31 | 1993-07-28 | Rolls Royce | Shielded vectored thrust gas turbine engines |
| RU168499U1 (en) * | 2016-06-23 | 2017-02-07 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Remote fan module of an aircraft power plant |
-
1964
- 1964-04-23 GB GB1688564A patent/GB1110113A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2263505A (en) * | 1980-10-31 | 1993-07-28 | Rolls Royce | Shielded vectored thrust gas turbine engines |
| GB2263505B (en) * | 1980-10-31 | 1994-01-26 | Rolls Royce | Shielded vectored thrust engines |
| RU168499U1 (en) * | 2016-06-23 | 2017-02-07 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Remote fan module of an aircraft power plant |
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