GB887021A - Improvements in aircraft gas turbine engines - Google Patents

Improvements in aircraft gas turbine engines

Info

Publication number
GB887021A
GB887021A GB1361658A GB1361658A GB887021A GB 887021 A GB887021 A GB 887021A GB 1361658 A GB1361658 A GB 1361658A GB 1361658 A GB1361658 A GB 1361658A GB 887021 A GB887021 A GB 887021A
Authority
GB
United Kingdom
Prior art keywords
petals
divergent
beyond
engine
reheat
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
GB1361658A
Inventor
Leonard Sidney Greenland
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.)
HM Hobson Ltd
Original Assignee
HM Hobson Ltd
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 HM Hobson Ltd filed Critical HM Hobson Ltd
Priority to GB1361658A priority Critical patent/GB887021A/en
Publication of GB887021A publication Critical patent/GB887021A/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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)

Abstract

887,021. Jet propulsion plant. HOBSON Ltd., H. M. April 22, 1959 [April 29, 1958], No. 13616/58. Class 110 (3). In a gas turbine engine having a reheat fuel system and a variable area exhaust nozzle, which is automatically positioned when reheat is in operation to maintain the turbine pressure ratio substantially constant, the exhaust nozzle is constituted by short pneumatically actuated petals which are movable after the maximum amount of reheat fuel has been supplied to the engine, beyond the position of full effective area and into a divergent position which includes a fixed conical divergent section near the rear end of the exhaust pipe which forms a prolongation of the petals when the petals are moved to the divergent position. Pneumatic jacks 6 move petals 2 over the normal range of adjustment between positions A and B and beyond to the divergent position C. The petals may be controlled as described in Specification 833,493 wherein, after the maximum amount of reheat fuel has been supplied to the engine to maintain the turbine pressure ratio constant, the nozzle may be moved beyond the position of full effective area into a divergent position to enable the working fluid to be expanded fully. The cowling 4 with a fixed divergent portion 5 forms a prolongation of the petals 2 when they reach the divergent position C.
GB1361658A 1958-04-29 1958-04-29 Improvements in aircraft gas turbine engines Expired GB887021A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1361658A GB887021A (en) 1958-04-29 1958-04-29 Improvements in aircraft gas turbine engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1361658A GB887021A (en) 1958-04-29 1958-04-29 Improvements in aircraft gas turbine engines

Publications (1)

Publication Number Publication Date
GB887021A true GB887021A (en) 1962-01-10

Family

ID=10026280

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1361658A Expired GB887021A (en) 1958-04-29 1958-04-29 Improvements in aircraft gas turbine engines

Country Status (1)

Country Link
GB (1) GB887021A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3971534A (en) * 1973-12-28 1976-07-27 The Boeing Company Method of and apparatus for controlling flow attachment to the wing and flap surfaces of an upper surface blowing type aircraft
US20140298788A1 (en) * 2013-04-08 2014-10-09 United Technologies Corporation Gas turbine engine including pneumatic actuator system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3971534A (en) * 1973-12-28 1976-07-27 The Boeing Company Method of and apparatus for controlling flow attachment to the wing and flap surfaces of an upper surface blowing type aircraft
US20140298788A1 (en) * 2013-04-08 2014-10-09 United Technologies Corporation Gas turbine engine including pneumatic actuator system

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