GB1141051A - Ejector type exhaust nozzle - Google Patents
Ejector type exhaust nozzleInfo
- Publication number
- GB1141051A GB1141051A GB737166A GB737166A GB1141051A GB 1141051 A GB1141051 A GB 1141051A GB 737166 A GB737166 A GB 737166A GB 737166 A GB737166 A GB 737166A GB 1141051 A GB1141051 A GB 1141051A
- Authority
- GB
- United Kingdom
- Prior art keywords
- flaps
- shroud
- actuator
- convergent
- movable
- 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
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/56—Reversing jet main flow
- F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
-
- 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
-
- 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
- F02K1/123—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, both having their flaps hinged at their upstream ends on a fixed 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
- F02K1/38—Introducing air inside the jet
- F02K1/383—Introducing air inside the jet with retractable elements
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Supercharger (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
1,141,051. Deflecting propulsive jets. UNITED AIRCRAFT CORP. 18 Feb., 1966, No. 7371/66. Heading B7G. [Also in Division F1] An exhaust nozzle 30 for a turbo-jet engine 10 having a casing 12 surrounded by a nacelle 28 comprises a rectangular-shaped shroud 50 forming a rearward extension of the nacelle. Between the nacelle 28 and the shroud 50 there may be provided on the top and bottom surfaces pairs of blow-in-doors 40, 42 movable by actuator 44 from the closed supersonic position shown to the chain-line open position in which air ejector passages 52 are formed. In a modification (Fig. 9, not shown), the doors 40, 42 are omitted and the passages 52 are always open. The primary exhaust nozzle 32 is circular and consists of intersealed flaps 34 movable between a convergent maximum area supersonic position shown and a minimum area convergent subsonic position indicated by chain-lines. The upper surface of the shroud 50 is formed at its rear end by a flap 58 pivoted at 60 and movable by an actuator (96) (Fig. 6, not shown). The lower surface of shroud 50 is formed at its rear end by two flaps 66, 68 pivoted at 64 to the shroud and at 134 to each other. Flap 68 is controlled by an actuator (120) mounted on the flap 66, whereas flaps 66, 68 are movable conjointly by an actuator (150) mounted on the shroud 50. For supersonic operation the flaps 58, 68 are in the solid-line position shown to form a divergent extension to the convergent nozzle 32; for subsonic operation the flaps have the chain-line convergent position. For STOL operation the flaps 58, 66, 68 are moved to the Fig. 3 position. For reverse thrust the flaps take the position of Fig. 4.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB737166A GB1141051A (en) | 1966-02-18 | 1966-02-18 | Ejector type exhaust nozzle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB737166A GB1141051A (en) | 1966-02-18 | 1966-02-18 | Ejector type exhaust nozzle |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1141051A true GB1141051A (en) | 1969-01-22 |
Family
ID=9831862
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB737166A Expired GB1141051A (en) | 1966-02-18 | 1966-02-18 | Ejector type exhaust nozzle |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1141051A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2637016A1 (en) * | 1988-09-28 | 1990-03-30 | Snecma | TWO-DIMENSIONAL EJECTION NOZZLE OF A TURBO-JET AND ITS CONTROL SYSTEM |
US6381950B1 (en) | 1999-07-07 | 2002-05-07 | Bae Systems Plc | Engine nozzle arrangement for an aircraft |
US11566584B1 (en) | 2022-03-07 | 2023-01-31 | Rohr, Inc. | Thrust reverser for variable area nozzle |
-
1966
- 1966-02-18 GB GB737166A patent/GB1141051A/en not_active Expired
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2637016A1 (en) * | 1988-09-28 | 1990-03-30 | Snecma | TWO-DIMENSIONAL EJECTION NOZZLE OF A TURBO-JET AND ITS CONTROL SYSTEM |
EP0362051A1 (en) * | 1988-09-28 | 1990-04-04 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Bidimensional ejection nozzle for a turbine and its control system |
US4955541A (en) * | 1988-09-28 | 1990-09-11 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Two dimensional nozzle for a turbojet engine |
US6381950B1 (en) | 1999-07-07 | 2002-05-07 | Bae Systems Plc | Engine nozzle arrangement for an aircraft |
US11566584B1 (en) | 2022-03-07 | 2023-01-31 | Rohr, Inc. | Thrust reverser for variable area nozzle |
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