GB876583A - Adjustable jet propulsion nozzle and jet propulsion engine provided with such nozzle - Google Patents
Adjustable jet propulsion nozzle and jet propulsion engine provided with such nozzleInfo
- Publication number
- GB876583A GB876583A GB37720/59A GB3772059A GB876583A GB 876583 A GB876583 A GB 876583A GB 37720/59 A GB37720/59 A GB 37720/59A GB 3772059 A GB3772059 A GB 3772059A GB 876583 A GB876583 A GB 876583A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzle
- flaps
- elements
- group
- jet propulsion
- 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
Abstract
876,583. Deflecting propulsive jets. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Nov. 6, 1959 [Nov. 12, 1958], No. 37720/59. Class 4. [Also in Group XXVI] A substantially circular jet propulsion nozzle comprises two groups of moveable wall elements without any connecting linkage, an upstream group forming a convergent portion and a downstream group which can also form a convergent portion in continuation of the first group or else a divergent portion following the convergent portion the wall elements of the downstream group being able to carry out, in longitudinal planes, a combined translation along the axis of the nozzle and a rotation about an axis located about the middle point of the elements and substantially tangential to the nozzle. A jet propulsion nozzle, Fig. 5, comprises a plurality of upstream flaps 2 pivoted at 3 to the downstream end of the jet pipe 1. These flaps are caused to bear on the upstream ends of the downstream wall elements 4 by the gas pressure of the jet although a spring or return jack may be provided to prevent fluttering. The elements 4 have pins 10, 11 which are guided by slots 6, 7 in a plate 8 attached to a fairing 9. The elements 4 are moved by jacks 15 acting through a synchronising ring 16. Movement of the jacks 15 will cause a combined translational and rotational movement of the elements 4 and alter the shape of the nozzle from that shown to a convergent-divergent configuration. In a modification, Fig. 9, the flaps 2 and members 4 are operated by separate sets of jacks 15, 17, independently operated. With this arrangement, the flaps 2 and members 4 may be separated so as to leave an annular space for atmospheric air to be sucked in by ejector effect. It is possible to control each element or some of them separately in order to give them assymetrical positions causing deflection of the jet. The flaps 2 may be hollow and cooled by air from the atmosphere or by air from the compressor.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR778866A FR1215236A (en) | 1958-11-12 | 1958-11-12 | Adjustable nozzle and jet thruster equipped with such nozzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB876583A true GB876583A (en) | 1961-09-06 |
Family
ID=8708187
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB37720/59A Expired GB876583A (en) | 1958-11-12 | 1959-11-06 | Adjustable jet propulsion nozzle and jet propulsion engine provided with such nozzle |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US3054256A (en) |
| DE (1) | DE1129775B (en) |
| FR (1) | FR1215236A (en) |
| GB (1) | GB876583A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2658867A1 (en) * | 1990-02-26 | 1991-08-30 | Gen Electric | EXHAUST NOZZLE COMPRISING A VARIABLE PROFILE EXHAUST SHUTTER AND RELATED COMBUSTION GAS DISCHARGE METHOD. |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB951130A (en) * | 1961-07-28 | 1964-03-04 | Rolls Royce | Improvements relating to jet engines |
| US3279194A (en) * | 1962-08-14 | 1966-10-18 | Garrett Corp | Aerothermodynamic duct and control means therefor |
| US3316716A (en) * | 1964-07-01 | 1967-05-02 | William J D Escher | Composite powerplant and shroud therefor |
| CA961652A (en) * | 1971-12-20 | 1975-01-28 | Richard E. Teagle | Balanced flap converging/diverging nozzle |
| DE2845149C2 (en) * | 1978-10-17 | 1982-03-04 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Jet engine, especially for propelling an aircraft |
| FR2491126A1 (en) * | 1980-10-01 | 1982-04-02 | Snecma | DEVICE FOR MANEUVERING THE SHUTTERS OF A TURBOMACHINE TUBE |
| US5201800A (en) * | 1990-02-26 | 1993-04-13 | General Electric Company | Method for discharging combustion gases from an exhaust nozzle |
| US5484105A (en) * | 1994-07-13 | 1996-01-16 | General Electric Company | Cooling system for a divergent section of a nozzle |
| US5706650A (en) * | 1995-08-09 | 1998-01-13 | United Technologies Corporation | Vectoring nozzle using injected high pressure air |
| CN1181065C (en) * | 2002-05-08 | 2004-12-22 | 上海医药工业研究院 | Aralkylformylalkyl piperazine derivative and its application as brain nerve protector |
| DE102008022271A1 (en) * | 2008-05-06 | 2009-11-26 | Opara, Günther | Nozzle i.e. jet-nozzle, for e.g. gas turbine of aircraft, has one-piece tubular body including wall that forms convergent and divergent channel parts by radial contraction of cross-section dimension of nozzle |
| DE102017104043A1 (en) * | 2017-02-27 | 2018-08-30 | Rolls-Royce Deutschland Ltd & Co Kg | Convergent-divergent exhaust nozzle for a turbofan engine of a supersonic aircraft and method for reducing the rear resistance behind such a thruster |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2597253A (en) * | 1945-11-13 | 1952-05-20 | Effie B Melchior | Jet-propulsion nozzle |
| CA486078A (en) * | 1950-04-27 | 1952-08-26 | W. Kellal George | Exit area control for jet engines |
| US2625008A (en) * | 1951-02-28 | 1953-01-13 | Curtiss Wright Corp | Variable flow nozzle |
| US2770944A (en) * | 1952-04-26 | 1956-11-20 | United Aircraft Corp | Variable area reaction nozzle movable from convergent to convergent-di-vergent form |
| US2858668A (en) * | 1952-09-27 | 1958-11-04 | Curtiss Wright Corp | Control for variable area convergentdivergent exhaust nozzle |
| BE531848A (en) * | 1953-09-17 | |||
| US2939274A (en) * | 1954-01-04 | 1960-06-07 | North American Aviation Inc | Means for varying a jet engine orifice |
| GB782494A (en) * | 1954-03-26 | 1957-09-11 | Rolls Royce | Improvements in or relating to jet propulsion nozzle arrangements |
| GB788359A (en) * | 1954-11-26 | 1958-01-02 | Power Jets Res & Dev Ltd | Discharge nozzles for propulsive jets |
| GB768014A (en) * | 1955-03-07 | 1957-02-13 | United Aircraft Corp | Improvements in or relating to variable area propulsion nozzles |
| US2931169A (en) * | 1956-05-15 | 1960-04-05 | Westinghouse Electric Corp | Variable convergent-divergent exhaust nozzle |
| US2910829A (en) * | 1956-08-24 | 1959-11-03 | United Aircraft Corp | Exhaust nozzle interflap seal |
| US2932163A (en) * | 1958-05-12 | 1960-04-12 | Orenda Engines Ltd | Means for actuating a variable nozzle |
-
1958
- 1958-11-12 FR FR778866A patent/FR1215236A/en not_active Expired
-
1959
- 1959-11-06 GB GB37720/59A patent/GB876583A/en not_active Expired
- 1959-11-07 DE DES65748A patent/DE1129775B/en active Pending
- 1959-11-10 US US852070A patent/US3054256A/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2658867A1 (en) * | 1990-02-26 | 1991-08-30 | Gen Electric | EXHAUST NOZZLE COMPRISING A VARIABLE PROFILE EXHAUST SHUTTER AND RELATED COMBUSTION GAS DISCHARGE METHOD. |
Also Published As
| Publication number | Publication date |
|---|---|
| FR1215236A (en) | 1960-04-15 |
| US3054256A (en) | 1962-09-18 |
| DE1129775B (en) | 1962-05-17 |
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