GB1300405A - Improvements in nozzles for gas turbine jet propulsion engines - Google Patents

Improvements in nozzles for gas turbine jet propulsion engines

Info

Publication number
GB1300405A
GB1300405A GB31989/69A GB3198969A GB1300405A GB 1300405 A GB1300405 A GB 1300405A GB 31989/69 A GB31989/69 A GB 31989/69A GB 3198969 A GB3198969 A GB 3198969A GB 1300405 A GB1300405 A GB 1300405A
Authority
GB
United Kingdom
Prior art keywords
ring
flaps
links
ring member
gas turbine
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
GB31989/69A
Inventor
David Roberts Mcmurtry
Ronald William Knight
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.)
UK Secretary of State for Defence
Original Assignee
UK Secretary of State for Defence
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 UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Priority to GB31989/69A priority Critical patent/GB1300405A/en
Publication of GB1300405A publication Critical patent/GB1300405A/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
    • F02K1/1261—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 substantially axially movable 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)
  • Supercharger (AREA)

Abstract

1300405 Jet propulsion nozzles - variable area DEFENCE SECRETARY OF STATE FOR 28 July 1970 [25 June 1969] 31989/69 Heading F1J The invention relates to a propulsion nozzle for a gas turbine jet engine comprising an annular array of flaps pivotally mounted at their upstream ends on a support member for radial movement of their downstream ends. The nozzle shown comprises a series of flaps 2 which are pivotally mounted at their upstream ends 4 on a ring member 5 which is axially movable by screw jacks 6. The adjacent flaps 2 are inter-connected by a series of circumferentially-extending links 30 which carry rollers 32 which engage in oppositelyinclined grooves 34 formed in adjacent flaps. A second ring member 14 is provided being connected to the first ring member 5 by a lost motion device so that the ring 14 moves a lesser distance than the ring 5 upon axial movement of the ring 5. The lost motion device comprises pairs of links 18 pivotally connected to the rings 5 and 14, and to a common roller 20, the rollers 20 engaging against a fixed cam member 24. The links 30 are connected to the ring 14 by means of links 12. Thus as the ring member 5 is moved axially, the ring member 14 is also moved axially but at a lesser rate and so relative movement occurs between the links 30 and the flaps 2 resulting in pivotal movement of the flaps about the points 4.
GB31989/69A 1969-06-25 1969-06-25 Improvements in nozzles for gas turbine jet propulsion engines Expired GB1300405A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB31989/69A GB1300405A (en) 1969-06-25 1969-06-25 Improvements in nozzles for gas turbine jet propulsion engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB31989/69A GB1300405A (en) 1969-06-25 1969-06-25 Improvements in nozzles for gas turbine jet propulsion engines

Publications (1)

Publication Number Publication Date
GB1300405A true GB1300405A (en) 1972-12-20

Family

ID=10331364

Family Applications (1)

Application Number Title Priority Date Filing Date
GB31989/69A Expired GB1300405A (en) 1969-06-25 1969-06-25 Improvements in nozzles for gas turbine jet propulsion engines

Country Status (1)

Country Link
GB (1) GB1300405A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2344720A2 (en) * 1976-03-17 1977-10-14 Rolls Royce Convergent-divergent thrust jet for jet propulsion - has divergent angle adjustable independent of jet cross section
FR2455179A1 (en) * 1979-04-23 1980-11-21 Gen Electric SYSTEM FOR HANDLING AN ELEMENT MOUNTED WITHIN A CRANKCASE
US4383407A (en) * 1981-02-02 1983-05-17 Thiokol Corporation Extendible thrust nozzle for rockets
US4411399A (en) * 1981-09-29 1983-10-25 The Boeing Company Retractable nozzle fairing system for aeroplane center boost engine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2344720A2 (en) * 1976-03-17 1977-10-14 Rolls Royce Convergent-divergent thrust jet for jet propulsion - has divergent angle adjustable independent of jet cross section
FR2455179A1 (en) * 1979-04-23 1980-11-21 Gen Electric SYSTEM FOR HANDLING AN ELEMENT MOUNTED WITHIN A CRANKCASE
US4383407A (en) * 1981-02-02 1983-05-17 Thiokol Corporation Extendible thrust nozzle for rockets
US4411399A (en) * 1981-09-29 1983-10-25 The Boeing Company Retractable nozzle fairing system for aeroplane center boost engine

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Legal Events

Date Code Title Description
PS Patent sealed
PLE Entries relating assignments, transmissions, licences in the register of patents
PCNP Patent ceased through non-payment of renewal fee