GB1433936A - Variable area jet propulsion nozzles - Google Patents

Variable area jet propulsion nozzles

Info

Publication number
GB1433936A
GB1433936A GB4457873A GB4457873A GB1433936A GB 1433936 A GB1433936 A GB 1433936A GB 4457873 A GB4457873 A GB 4457873A GB 4457873 A GB4457873 A GB 4457873A GB 1433936 A GB1433936 A GB 1433936A
Authority
GB
United Kingdom
Prior art keywords
side plates
flap
pivotally mounted
pivotally connected
parallelogram
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
GB4457873A
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of GB1433936A publication Critical patent/GB1433936A/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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
    • 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)
  • Control Of Turbines (AREA)
  • Nozzles (AREA)
  • Transmission Devices (AREA)

Abstract

1433936 Jet propulsion nozzles - variable area SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 24 Sept 1973 [6 Oct 1972] 44578/73 Addition to 1233694 Heading F1J The invention relates to a jet propulsion nozzle of the variable area type which comprises a series of flap members 102 each pivotally mounted at a tangential axis A at the downstream end of fixed nozzle structure 110, and each movable by means of an actuator 103 having an operating rod 104. Follower flaps 122 are disposed between adjacent actuated flaps 102, being maintained thereagainst in operation, by pressure of the gas stream. A pair of side plates 114a, 114b is associated with each actuated flap, the side plates being pivotally mounted on fixed structure as indicated at points K, G, H, J. The actuator 103 is pivotally mounted at its upstream end between the side plates as indicated at G. The pivoted flap 102 comprises a flap portion 102x and a pair of bell-crank levers 102y secured thereto, the flap being pivotally mounted between the side plates at points A. The upper ends of the bell-crank levers 102y have pivotally connected thereto links 106a, 106b which are pivotally connected at intermediate points D to levers 105, the levers 105 being pivotally connected at axes B at the downstream ends of the side plates 114a, 114b. The axes A, B, C, D, are disposed at the corners of a parallelogram, the side AB of which is fixed. The downstream ends of the links 106a, 106b are pivotally connected about an axis E to a crosspiece 107 to the mid-point of which is connected the downstream end of the actuator rod 104 by means of a pin 125. The arrangement is such that the height d2 of the point E above the side AB of the parallelogram is always less than the height h2 of the parallelogram.
GB4457873A 1972-10-06 1973-09-24 Variable area jet propulsion nozzles Expired GB1433936A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7235502A FR2202234B2 (en) 1972-10-06 1972-10-06

Publications (1)

Publication Number Publication Date
GB1433936A true GB1433936A (en) 1976-04-28

Family

ID=9105300

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4457873A Expired GB1433936A (en) 1972-10-06 1973-09-24 Variable area jet propulsion nozzles

Country Status (4)

Country Link
US (1) US3837580A (en)
DE (1) DE2349560C3 (en)
FR (1) FR2202234B2 (en)
GB (1) GB1433936A (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2244917B2 (en) * 1973-09-21 1978-01-13 Snecma
US4311276A (en) * 1978-06-24 1982-01-19 Rolls-Royce Limited Variable area nozzle for a gas turbine engine
FR2714421B1 (en) * 1980-01-14 1996-03-01 Snecma Nozzle comprising an adjustable convergent-diverging nozzle, in particular for a jet engine.
FR2474592A1 (en) * 1980-01-25 1981-07-31 Snecma TURBOREACTOR TUBE DEVICE
FR2723145B1 (en) * 1981-11-24 1996-12-13 Snecma CONVERGENT-DIVERGENT NOZZLE, PARTICULARLY FOR A TURBOREACTOR
FR2714422A1 (en) * 1983-01-13 1995-06-30 Snecma Convergent-divergent nozzle, particularly for jet engines
FR2557211A1 (en) * 1983-12-21 1985-06-28 Camboulives Andre EJECTION ASSEMBLY, IN PARTICULAR FOR TURBOJET ENGINE
FR2617910A1 (en) * 1987-07-08 1989-01-13 Snecma AXISYMETRIC NOZZLE OF DIVERGENT CONVERGENT TURBOREACTOR
FR2661716B1 (en) * 1990-05-03 1992-07-03 Snecma TURBOREACTOR NOZZLE DEVICE.
US5031836A (en) * 1990-07-10 1991-07-16 United Technologies Corporation Flexible fairing for airframe/nozzle interface
FR2873757B1 (en) * 2004-07-28 2006-09-29 Snecma Moteurs Sa CONVERGENT TUYERE OF TURBOREACTOR
FR2875853B1 (en) * 2004-09-29 2006-12-22 Snecma Moteurs Sa TURBOREACTOR WITH A VARIABLE SECTION TUBE WHICH EACH PIVOT SHUTTER AROUND A AXIS, AXES FOR THE SHUTTERS
FR2877052B1 (en) * 2004-10-26 2007-04-20 Snecma Moteurs Sa VARIABLE SECTION TURBOMACHINE TUBE WITH MONOBLOC CONTROL LEVER SUPPORT
US8015820B2 (en) * 2008-06-03 2011-09-13 United Technologies Corporation Gas turbine engine exhaust component and manufacturing method of same
GB201609071D0 (en) 2016-05-24 2016-07-06 Rolls Royce Plc Aircraft gas turbine engine nacelle
CN112555049A (en) * 2020-12-03 2021-03-26 北方工业大学 Outer sleeve type vectoring nozzle structure of micro turbojet engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2990029A (en) * 1956-03-16 1961-06-27 Rolls Royce Variable area jet propulsion nozzles
US3004385A (en) * 1958-06-25 1961-10-17 Gen Motors Corp Variable convergent-divergent jet nozzle
FR1562941A (en) * 1968-01-19 1969-04-11
FR2030532A5 (en) * 1969-07-03 1970-11-13 Snecma

Also Published As

Publication number Publication date
DE2349560C3 (en) 1980-04-03
US3837580A (en) 1974-09-24
FR2202234B2 (en) 1976-03-26
DE2349560B2 (en) 1979-08-02
FR2202234A2 (en) 1974-05-03
DE2349560A1 (en) 1974-04-18

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee