GB918189A - Jet propulsion nozzle - Google Patents

Jet propulsion nozzle

Info

Publication number
GB918189A
GB918189A GB23185/60A GB2318560A GB918189A GB 918189 A GB918189 A GB 918189A GB 23185/60 A GB23185/60 A GB 23185/60A GB 2318560 A GB2318560 A GB 2318560A GB 918189 A GB918189 A GB 918189A
Authority
GB
United Kingdom
Prior art keywords
nozzle
engine
jet
skin
sections
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
Application number
GB23185/60A
Inventor
Stanley Frank Smith
David Craigie
John Gregory Keenan
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB23185/60A priority Critical patent/GB918189A/en
Priority to FR866085A priority patent/FR1292878A/en
Priority to US119674A priority patent/US3146584A/en
Priority to DE1961R0030650 priority patent/DE1175036C2/en
Publication of GB918189A publication Critical patent/GB918189A/en
Expired legal-status Critical Current

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
    • F02K1/52—Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Testing Of Engines (AREA)
  • Toys (AREA)

Abstract

918,189. Jet propulsion nozzles. ROLLS-ROYCE Ltd. June 26, 1961 [July 1, 1960], No. 23185/60. Class 110 (3). [Also in Group XXXIII] A jet propulsion nozzle assembly for supersonic jet velocities comprises a nozzle member and a body extending downstream of the nozzle member having a concave surface forming a smoothly curved extension of the inner surface of part of the outer wall of the nozzle so as to control the expansion of the jet gases. A gas turbine engine 15 is mounted in a cowling 12 beneath a wing or fuselage of an aircraft. The engine is connected by a jet pipe 22 to a thrust reverse 23 and nozzle sections 24, 25, 26 and 27 which form a convergent nozzle with a rectangular section throat in the exit plane 64. The nozzle sections are suspended from the aircraft structure by a strap 32 attached to trunnions 33 in a block 34 sliding in guides 35 to allow for relative thermal expansion. The nozzle is provided with a pivoted flap 37 operated by an air motor through a lever 41, in order to vary the throat area. Mounted in the nozzle section 27 is a strap 45 pivotably connected to a link 46 carried on trunnions 47 in a block 48 sliding in guides 50. The links 46 carry a concave skin 53 which is in slidable sealing contact with the nozzle and the skin 54. The skins 54-55 are carried by the structure 51 and are stiffened by sections 56 which bear against pads 57. The structure 51 is protected by a shield 58 and a thermal insulating blanket 60. The skin 55 may merge in to the aircraft wing or fuselage. The tangent 63 to the lip 62 of the nozzle is arranged at the angle of refraction 0 at the design Mach number with the axis of the engine. The curve of the concave skins 53, 54, 55 is similarly chosen so that downstream of the Mach plane 67 all the flow is parallel to the axis of the engine.
GB23185/60A 1960-07-01 1960-07-01 Jet propulsion nozzle Expired GB918189A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB23185/60A GB918189A (en) 1960-07-01 1960-07-01 Jet propulsion nozzle
FR866085A FR1292878A (en) 1960-07-01 1961-06-26 Jet propulsion nozzle
US119674A US3146584A (en) 1960-07-01 1961-06-26 Jet propulsion nozzle
DE1961R0030650 DE1175036C2 (en) 1960-07-01 1961-06-30 Aircraft jet engine plant

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB23185/60A GB918189A (en) 1960-07-01 1960-07-01 Jet propulsion nozzle

Publications (1)

Publication Number Publication Date
GB918189A true GB918189A (en) 1963-02-13

Family

ID=10191525

Family Applications (1)

Application Number Title Priority Date Filing Date
GB23185/60A Expired GB918189A (en) 1960-07-01 1960-07-01 Jet propulsion nozzle

Country Status (4)

Country Link
US (1) US3146584A (en)
DE (1) DE1175036C2 (en)
FR (1) FR1292878A (en)
GB (1) GB918189A (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3643439A (en) * 1968-11-29 1972-02-22 Adolphe C Petersen Compound reaction propulsion means with multiple thrust
US4018046A (en) * 1975-07-17 1977-04-19 Avco Corporation Infrared radiation suppressor for gas turbine engine
US9009966B2 (en) 2013-03-15 2015-04-21 Northrop Gurmman Systems Corporation Internal/external single expansion ramp nozzle with integrated third stream
CN110450964B (en) * 2018-05-07 2020-11-24 南京普国科技有限公司 Axisymmetric inclined outlet convergent-divergent nozzle and design method thereof

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1066429B (en) * 1959-10-01
US2657575A (en) * 1947-08-21 1953-11-03 Harry J Allen Asymmetric adjustable supersonic nozzle
BE498317A (en) * 1949-10-06
NL161099C (en) * 1951-05-10 1900-01-01 Tecalemit Group Services Limit DEVICE FOR LUBRICATION OF A VEHICLE DEPENDING ON THE ROAD.
DE1052822B (en) * 1953-04-08 1959-03-12 Power Jets Res & Dev Ltd Aircraft in which a propulsion jet is directed over the top of the wing flaps
US2972230A (en) * 1954-01-13 1961-02-21 Gen Motors Corp Automobile gas turbine
BE537645A (en) * 1954-06-10
US2799989A (en) * 1954-09-24 1957-07-23 Peter G Kappus Variable area jet nozzle
US2828607A (en) * 1955-10-24 1958-04-01 Gen Motors Corp Dual engine support
US2982496A (en) * 1956-01-11 1961-05-02 English Electric Co Ltd Aircraft
GB834907A (en) * 1956-10-23 1960-05-11 Rolls Royce Improvements in or relating to jet propulsion nozzles
NL247267A (en) * 1958-04-02
US2968920A (en) * 1959-01-28 1961-01-24 Gen Electric Engine mounting arrangement
NL255475A (en) * 1959-10-05
US3080711A (en) * 1960-01-06 1963-03-12 James F Connors Penshape exhaust nozzle for supersonic engine

Also Published As

Publication number Publication date
FR1292878A (en) 1962-05-04
DE1175036C2 (en) 1965-02-04
DE1175036B (en) 1964-07-30
US3146584A (en) 1964-09-01

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