GB1009776A - Supersonic jet propulsion nozzle - Google Patents
Supersonic jet propulsion nozzleInfo
- Publication number
- GB1009776A GB1009776A GB34817/64A GB3481764A GB1009776A GB 1009776 A GB1009776 A GB 1009776A GB 34817/64 A GB34817/64 A GB 34817/64A GB 3481764 A GB3481764 A GB 3481764A GB 1009776 A GB1009776 A GB 1009776A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzle
- plug
- throat
- casing
- sleeve
- 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
- F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
-
- 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
- F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
-
- 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
- F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
- F02K1/085—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone by transversely deforming an internal member
-
- 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
- F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud
-
- 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
- F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
- F02K1/42—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet the means being movable into an inoperative position
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Special Spraying Apparatus (AREA)
Abstract
1,009,776. Jet propulsion nozzles. ROLLS-ROYCE Ltd. Aug. 25, 1964, No. 34817/64. Heading F1J. A supersonic jet propulsion nozzle has a substantially cylindrical nozzle casing assembly and a bulbous plug mounted therein, the plug and casing assembly being relatively movable axially to permit the throat of the nozzle to be disposed either in a position at the downstream end of the casing assembly or in a position upstream of said downstream end, whereby the nozzle may be employed either as a convergent or as a convergent-divergent nozzle, and silencing means for substantially increasing the peripheral area over which the jet gases mix with the ambient air. A gas turbine jet propulsion engine supersonic nozzle 19, Fig. 2, comprises a nozzle casing having an axially slidable cylindrical outer-portion 22 and a fixed inner portion 23. A bulbous plug 25 is supported within the nozzle casing by struts 26 attached to upstream plug portion 30. Casing portion 22 is slidable between positions shown in full and dotted lines to define respectively with plug 25 a convergent or a convergentdivergent flow passage, the throat remaining at 24. Plug portion 30 is attached to a downstream portion 31 by a tube 32 upon which slide sleeves 42, 50. Sleeve 42 is moved by a rod 43 driven by rack and pinion 44, 45 and is pivotally connected by links 38 to a series of pivoted "fingers" 33, 34 forming the central surface of plug 25, such that axial movement of the sleeve causes radial movement of fingers 33, 34 and a variation in the nozzle throat area. Sleeve 50 is pivotally linked to a series of angularly spaced flaps 52, each pivoted on a fixed central portion of plug 25 intermediate each pair of fingers 33, 34, such that axial movement of the sleeve causes flaps 52 to move into or out of the jet stream. In the position shown dotted flaps 52 increase the peripheral area over which the jet stream mixes with ambient air to effect silencing of the nozzle. Outward movement of flaps 52 is accompanied by inward movement of fingers 33, 34 to compensate for the reduction in flow area of throat 24. In a modification, Fig. 4, an axially slidable nozzle casing portion 100 surrounds a plug 103 supported by struts 105, 106 from fixed casing portion 101 so that the nozzle can be set to convergent or convergent-divergent form, as in the previous embodiment. A series of angularly spaced aerofoil members 113 are pivoted at 115 within the plug outer casing 112 and can be moved into the jet stream at the throat 102 by movement of ram actuated sleeve 117 so as to reduce the throat flow area. A series of angularly spaced vanes 107 extend radially from plug 103 at throat 102. Each vane 107 comprises, Fig. 6, a fixed upstream portion 131 and a downstream portion consisting of two pivoted separable parts 132, 133. Actuation of a push rod 134 by way of a ram 147, slidable sleeve 145 and related linkwork causes parts 132, 133 to move to the dotted line position in which ambient air is admitted between parts 132, 133 to mix with the jet stream and effect silencing.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB34818/64A GB1009777A (en) | 1964-08-25 | 1964-08-25 | Supersonic jet propulsion nozzle |
GB34817/64A GB1009776A (en) | 1964-08-25 | 1964-08-25 | Supersonic jet propulsion nozzle |
US474795A US3352494A (en) | 1964-08-25 | 1965-07-26 | Supersonic jet propulsion nozzle |
DER41245A DE1286334B (en) | 1964-08-25 | 1965-08-05 | Supersonic thrust nozzle for gas turbine jet engines |
FR28342A FR1445892A (en) | 1964-08-25 | 1965-08-13 | Supersonic jet propulsion nozzle |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB34817/64A GB1009776A (en) | 1964-08-25 | 1964-08-25 | Supersonic jet propulsion nozzle |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1009776A true GB1009776A (en) | 1965-11-10 |
Family
ID=10370275
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB34818/64A Expired GB1009777A (en) | 1964-08-25 | 1964-08-25 | Supersonic jet propulsion nozzle |
GB34817/64A Expired GB1009776A (en) | 1964-08-25 | 1964-08-25 | Supersonic jet propulsion nozzle |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB34818/64A Expired GB1009777A (en) | 1964-08-25 | 1964-08-25 | Supersonic jet propulsion nozzle |
Country Status (3)
Country | Link |
---|---|
US (1) | US3352494A (en) |
DE (1) | DE1286334B (en) |
GB (2) | GB1009777A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0582424A1 (en) * | 1992-08-03 | 1994-02-09 | General Electric Company | Noise-suppressed exhaust nozzles for jet engines |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3598318A (en) * | 1970-04-10 | 1971-08-10 | Boeing Co | Movable acoustic splitter for nozzle area control and thrust reversal |
US3814324A (en) * | 1972-06-19 | 1974-06-04 | Gen Electric | Propulsion nozzle and actuator system employed therein |
US3774868A (en) * | 1972-12-11 | 1973-11-27 | G Goetz | Integrated nozzle |
US4043508A (en) * | 1975-12-01 | 1977-08-23 | General Electric Company | Articulated plug nozzle |
US4039146A (en) * | 1975-12-01 | 1977-08-02 | General Electric Company | Variable cycle plug nozzle and flap and method of operating same |
US4088270A (en) * | 1976-03-31 | 1978-05-09 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Two dimensional wedge/translating shroud nozzle |
US4074859A (en) * | 1976-11-10 | 1978-02-21 | The United States Of America As Represented By The Secretary Of The Air Force | Deformable plug for an aircraft engine exhaust nozzle |
US4196856A (en) * | 1977-11-25 | 1980-04-08 | The Boeing Company | Variable geometry convergent divergent exhaust nozzle |
GB2333806B (en) * | 1979-08-17 | 1999-11-10 | Rolls Royce | Variable configuration final nozzle assembly for a combined rocket/ramjet engine |
US4537026A (en) * | 1982-04-07 | 1985-08-27 | Rolls-Royce Inc. | Variable area nozzles for turbomachines |
US5463866A (en) * | 1993-12-30 | 1995-11-07 | The Boeing Company | Supersonic jet engine installation and method with sound suppressing nozzle |
US5884843A (en) * | 1996-11-04 | 1999-03-23 | The Boeing Company | Engine noise suppression ejector nozzle |
US5941065A (en) * | 1996-11-04 | 1999-08-24 | The Boeing Company | Stowable mixer ejection nozzle |
US5908159A (en) * | 1997-02-24 | 1999-06-01 | The Boeing Company | Aircraft chute ejector nozzle |
US7886518B2 (en) * | 2006-11-14 | 2011-02-15 | General Electric Company | Turbofan engine cowl assembly and method of operating the same |
US9828943B2 (en) * | 2014-06-09 | 2017-11-28 | United Technologies Corporation | Variable area nozzle for gas turbine engine |
FR3097016B1 (en) * | 2019-06-06 | 2021-07-23 | Safran Aircraft Engines | CONFLUENCE STRUCTURE OF A PRIMARY VEIN AND A SECONDARY VEIN IN A DOUBLE-FLOW TURBOMACHINE |
US11313320B2 (en) * | 2020-02-27 | 2022-04-26 | Rolls-Royce North American Technologies Inc. | Exhaust nozzle with centerbody support structure for a gas turbine engine |
US11319832B2 (en) | 2020-02-27 | 2022-05-03 | Rolls-Royce North American Technologies Inc. | Single movement convergent and convergent-divergent nozzle |
US11274631B2 (en) | 2020-02-27 | 2022-03-15 | Rolls-Royce North American Technologies Inc. | Methodology for minimizing aerodynamic buzz in an exhaust nozzle |
USD1015134S1 (en) * | 2022-02-21 | 2024-02-20 | Jason D. Kerlin | Spool head thumb screw |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2570629A (en) * | 1945-10-05 | 1951-10-09 | Anxionnaz | Adjustable pipe for the intake of air and expansion of the driving gases in reactionjet propellers for projectiles and vehicles |
GB677973A (en) * | 1951-02-22 | 1952-08-27 | Blackburn & Gen Aircraft Ltd | Improvements in and relating to variable area nozzles for turbo-jet engine installations |
US2788635A (en) * | 1953-10-22 | 1957-04-16 | North American Aviation Inc | Device for varying a jet engine orifice |
BE537645A (en) * | 1954-06-10 | |||
US2940252A (en) * | 1956-02-07 | 1960-06-14 | Boeing Co | Gas stream thrust reaction propulsion engines with noise-suppression and thrust-reversing nozzle means |
US2845775A (en) * | 1956-06-01 | 1958-08-05 | United Aircraft Corp | Noise suppressors for jet engines |
US3055174A (en) * | 1957-01-14 | 1962-09-25 | Boeing Co | Retractable noise suppressor for jet engines |
US2938335A (en) * | 1958-04-14 | 1960-05-31 | Boeing Co | Noise suppressor and thrust reverser |
GB950288A (en) * | 1959-08-18 | 1964-02-26 | Bristol Siddeley Engines Ltd | Improvements in nozzles for aircraft propulsion |
GB920889A (en) * | 1960-11-14 | 1963-03-13 | Rolls Royce | Improvements relating to the silencing of gas turbine engines |
-
1964
- 1964-08-25 GB GB34818/64A patent/GB1009777A/en not_active Expired
- 1964-08-25 GB GB34817/64A patent/GB1009776A/en not_active Expired
-
1965
- 1965-07-26 US US474795A patent/US3352494A/en not_active Expired - Lifetime
- 1965-08-05 DE DER41245A patent/DE1286334B/en active Pending
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0582424A1 (en) * | 1992-08-03 | 1994-02-09 | General Electric Company | Noise-suppressed exhaust nozzles for jet engines |
Also Published As
Publication number | Publication date |
---|---|
GB1009777A (en) | 1965-11-10 |
US3352494A (en) | 1967-11-14 |
DE1286334B (en) | 1969-01-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
GB1009776A (en) | Supersonic jet propulsion nozzle | |
US3409228A (en) | Ejector nozzle | |
US2955414A (en) | Combined power plant | |
US3060679A (en) | Powerplant | |
GB1078421A (en) | Nozzle having a silencer effect for jet propulsion engines | |
GB1456280A (en) | Variable area exhaust nozzle assemblies | |
GB1100099A (en) | Improvements in convergent-divergent jet exhaust nozzle for supersonic aircraft | |
GB1421153A (en) | Propulsion nozzle for ducted fan gas turbine jet propulsion engines | |
GB750307A (en) | Improvements relating to variable nozzles for gas-turbine jet propulsion engines | |
US2972860A (en) | Combined variable ejector and thrust reverser | |
GB1122910A (en) | Improvements in supersonic convergent-divergent jet exhaust nozzle | |
US4502636A (en) | Variable geometry ejector nozzle for turbomachines | |
GB884872A (en) | Jet propulsion nozzle | |
US2987879A (en) | Jet propulsion nozzle with noise reducing means | |
US3780827A (en) | Gas turbine exhaust nozzle | |
US2986002A (en) | Leaky-type exhaust nozzle for jet propulsion devices | |
US2771740A (en) | Afterburning means for turbo-jet engines | |
GB1090147A (en) | Thrust nozzle for supersonic gas turbine jet engines of the by-pass type | |
GB871016A (en) | Gas turbine jet propulsion engines | |
US3355889A (en) | Movable power plant for direct lift and forward propulsion | |
US3109284A (en) | Discharge nozzles for propulsive jets | |
GB1016198A (en) | Improvements in low drag variable diameter plug jet exhaust nozzle | |
US3386248A (en) | Nozzle assembly for a jet propulsion engine | |
GB1142660A (en) | Improvements in combination jet exhaust nozzle and thrust reverser | |
GB839230A (en) | Improvements relating to variable jet nozzles |