GB850508A - Improvements relating to variable area jet nozzles of turbojet engines - Google Patents
Improvements relating to variable area jet nozzles of turbojet enginesInfo
- Publication number
- GB850508A GB850508A GB910759A GB910759A GB850508A GB 850508 A GB850508 A GB 850508A GB 910759 A GB910759 A GB 910759A GB 910759 A GB910759 A GB 910759A GB 850508 A GB850508 A GB 850508A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shroud
- nozzle
- duct
- flaps
- variable area
- 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
- F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
- F02K1/1238—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on a substantially axially movable structure
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
850,508. Jet propulsion nozzles. GENERAL MOTORS CORPORATION. March 16, 1959, No. 9107/59. Class 110 (3). A gas turbine jet propulsion engine has an exhaust duct terminating in a variable area nozzle comprising overlapping flaps pivoted to the exhaust duct, a shroud duct surrounding the exhaust duct and terminating in a variable area shroud nozzle comprising overlapping flaps pivoted to the shroud duct, the shroud duct being axially movable and connected to the flaps of the jet nozzle so as to move them about their pivots, the jet nozzle flaps being.connected to the shroud nozzle flaps so as to move the latter also. The high-velocity high-temperature exhaust gases from a gas turbine jetpropulsion engine are discharged from the reheat combustion chamber casing 26 through a variable area nozzle formed by overlapping flaps 46 pivoted to the casing 26 at 48. Each flap 46 has an actuating plate 50 containing a cam slot 52. An annular chamber 34 is formed between an annular shroud duct 36 and the casing 26 and is supplied with air passed from the engine intake through a space formed between the engine and its nacelle. The shroud duct 36 has a variable area shroud nozzle 38 formed by overlapping flaps 62 pivoted to the duct 36 at 64. The shroud duct is axially slidable with respect to the casing 26 by means of a number of actuating cylinders. A conical member 54, provided with air passages 56 and a number of U-shaped brackets 58, is secured to the shroud 36. Each bracket 58 carries a pin 60 which co-operates with a cam-slot 52 so that axial movement of the shroud 36 rotates the flaps 46 about their hinge axes 48. Each flap 62 has an actuating-plate 66 formed with a cam-slot 68 which co-operates with a cross-pin 72 carried by an arm 70 attached to each jet nozzle flap 46 so that movement of the shroud will also vary the outlet area of the shroud nozzle. The cam slots 52, 68 are shaped so as to vary the ratio of the outlet areas of the exhaust and shroud nozzles and the ratio of the axial distance between the boundary edges of the nozzle outlets to the square root of the outlet area of the exhaust nozzle. In the arrangement shown these ratios are maintained constant,
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB910759A GB850508A (en) | 1959-03-16 | 1959-03-16 | Improvements relating to variable area jet nozzles of turbojet engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB910759A GB850508A (en) | 1959-03-16 | 1959-03-16 | Improvements relating to variable area jet nozzles of turbojet engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB850508A true GB850508A (en) | 1960-10-05 |
Family
ID=9865493
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB910759A Expired GB850508A (en) | 1959-03-16 | 1959-03-16 | Improvements relating to variable area jet nozzles of turbojet engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB850508A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10662895B2 (en) | 2016-05-24 | 2020-05-26 | Rolls -Royce Plc | Aircraft gas turbine engine nacelle |
| EP4339444A1 (en) * | 2022-09-13 | 2024-03-20 | Rolls-Royce plc | An exhaust nozzle and a method of operating an exhaust nozzle |
-
1959
- 1959-03-16 GB GB910759A patent/GB850508A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10662895B2 (en) | 2016-05-24 | 2020-05-26 | Rolls -Royce Plc | Aircraft gas turbine engine nacelle |
| EP4339444A1 (en) * | 2022-09-13 | 2024-03-20 | Rolls-Royce plc | An exhaust nozzle and a method of operating an exhaust nozzle |
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