GB884587A - Improvements in jet propulsion nozzles - Google Patents
Improvements in jet propulsion nozzlesInfo
- Publication number
- GB884587A GB884587A GB1245258A GB1245258A GB884587A GB 884587 A GB884587 A GB 884587A GB 1245258 A GB1245258 A GB 1245258A GB 1245258 A GB1245258 A GB 1245258A GB 884587 A GB884587 A GB 884587A
- Authority
- GB
- United Kingdom
- Prior art keywords
- flaps
- nozzle
- shroud
- outer casing
- convergent
- 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
-
- 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
- F02K1/15—Control or regulation
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
Abstract
884,587. Jet propulsion plant. GENERAL ELECTRIC CO. April 18, 1958, No. 12452/58. Class 110 (3). A convergent-divergent nozzle for the jet pipe of a jet propulsion engine comprises a variable area convergent nozzle for subsonic gas flow combined with an air wall provided by means of an exterior passage surrounding the convergent nozzle and itself terminating in another variable area nozzle, the air wall defining an adjustable divergent passage for supersonic flow. The convergent portion of the nozzle is defined by adjustable nozzle flaps 11 hinged at 16 to the rear end of the tail pipe 17, while the boundary of the divergent portion is formed by secondary air flowing through an annular passage 15 between the tail pipe and an outer casing and emerging between the flaps 11 and the adjustable shroud flaps 12 which are hinged at 18 to a tubular shroud 19 which is itself axially slidable within the outer casing 21. Hydraulic actuators 22, 31 vary the angularity of the nozzle flaps 11 and the shroud flaps 12 respectively while an hydraulic actuator 39 varies the axial position of the shroud 19 in the outer casing 15. A control 46 combines measurements of rotor speed, throttle setting, compressor inlet temperature and pressure and turbine discharge temperature and pressure and controls the actuators accordingly. The flow of secondary air created by the ejector action of the nozzle may be used to cool engine accessories placed in the passage 15. In another embodiment (Fig. 4, not shown) a single shroud displacing actuator is used, the nozzle flaps and the shroud flaps being linked mechanically to each other and the outer casing 21 so as to move angularly as the axial position of the shroud 19 in the outer casing is varied. In a further embodiment lacking the axial adjustment the shroud flaps are hinged directly to the outer easing and are mechanically linked to the nozzle flaps, a single controller varying the angularity of the flaps.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1245258A GB884587A (en) | 1958-04-18 | 1958-04-18 | Improvements in jet propulsion nozzles |
DEG27204A DE1194642B (en) | 1958-04-18 | 1959-06-04 | Thrust nozzle for jet engines |
FR798766A FR1228764A (en) | 1958-04-18 | 1959-06-29 | Aerodynamic reaction nozzle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1245258A GB884587A (en) | 1958-04-18 | 1958-04-18 | Improvements in jet propulsion nozzles |
Publications (1)
Publication Number | Publication Date |
---|---|
GB884587A true GB884587A (en) | 1961-12-13 |
Family
ID=10004864
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1245258A Expired GB884587A (en) | 1958-04-18 | 1958-04-18 | Improvements in jet propulsion nozzles |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB884587A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN114017199A (en) * | 2021-11-15 | 2022-02-08 | 中国航发沈阳发动机研究所 | Mechanical area limit limiting method for double-ring control axisymmetric converging-diverging spray pipe |
CN115653779A (en) * | 2022-10-13 | 2023-01-31 | 中国航发四川燃气涡轮研究院 | Multi-shaft pneumatic thrust vectoring nozzle and multi-shaft thrust adjusting method |
-
1958
- 1958-04-18 GB GB1245258A patent/GB884587A/en not_active Expired
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN114017199A (en) * | 2021-11-15 | 2022-02-08 | 中国航发沈阳发动机研究所 | Mechanical area limit limiting method for double-ring control axisymmetric converging-diverging spray pipe |
CN114017199B (en) * | 2021-11-15 | 2022-09-30 | 中国航发沈阳发动机研究所 | Mechanical area limit limiting method for double-ring control axisymmetric converging-diverging spray pipe |
CN115653779A (en) * | 2022-10-13 | 2023-01-31 | 中国航发四川燃气涡轮研究院 | Multi-shaft pneumatic thrust vectoring nozzle and multi-shaft thrust adjusting method |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1718857B1 (en) | Integrated air inlet system for multi-propulsion aircraft engines | |
US2418488A (en) | Power-plant apparatus | |
US3514952A (en) | Variable bypass turbofan engine | |
US3098352A (en) | Adjustable jet propulsion nozzle with secondary air flow control | |
GB1122910A (en) | Improvements in supersonic convergent-divergent jet exhaust nozzle | |
GB1121960A (en) | Improvements relating to jet propulsion engines | |
US2971327A (en) | Discharge control of an overexpanding propulsion nozzle | |
GB1009776A (en) | Supersonic jet propulsion nozzle | |
GB1100099A (en) | Improvements in convergent-divergent jet exhaust nozzle for supersonic aircraft | |
US3722797A (en) | Convergent divergent ejector exhaust nozzle | |
US2563745A (en) | Variable area nozzle for power plants | |
US3390837A (en) | Convergent-divergent plug nozzle having a plurality of freely-floating tandem flaps | |
US3780827A (en) | Gas turbine exhaust nozzle | |
GB834907A (en) | Improvements in or relating to jet propulsion nozzles | |
GB1182687A (en) | Improvements in or relating to Multiflow Jet Propulsion Engines | |
US2986002A (en) | Leaky-type exhaust nozzle for jet propulsion devices | |
US3288373A (en) | Jet nozzle | |
GB1479149A (en) | Variable pitch ducted fan gas turbine power plant | |
JP2021037938A (en) | Propulsion system for aircraft and method of manufacturing propulsion system for aircraft | |
US3154915A (en) | Turbine jet engine | |
GB884587A (en) | Improvements in jet propulsion nozzles | |
GB1340817A (en) | Dual-flow gas turbine jet engines | |
US3068644A (en) | Aerodynamic jet nozzle | |
GB1116999A (en) | Improvements in supersonic convergent-divergent jet exhaust nozzles | |
GB1016198A (en) | Improvements in low drag variable diameter plug jet exhaust nozzle |