GB875496A - Improvements in or relating to ducted-fan gas turbine jet propulsion engines - Google Patents

Improvements in or relating to ducted-fan gas turbine jet propulsion engines

Info

Publication number
GB875496A
GB875496A GB4147359A GB4147359A GB875496A GB 875496 A GB875496 A GB 875496A GB 4147359 A GB4147359 A GB 4147359A GB 4147359 A GB4147359 A GB 4147359A GB 875496 A GB875496 A GB 875496A
Authority
GB
United Kingdom
Prior art keywords
duct
area
nozzle
vanes
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
GB4147359A
Inventor
Heinz Eugen Schmitt
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to GB4147359A priority Critical patent/GB875496A/en
Publication of GB875496A publication Critical patent/GB875496A/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
    • F02K1/08—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
    • F02K1/15—Control or regulation
    • F02K1/16—Control or regulation conjointly with another control

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)

Abstract

875,496. Gas turbine jet propulsion plant. GENERAL ELECTRIC CO. Dec. 7, 1959, No. 41473/59. Class 110 (3). A ducted fan gas turbine jet propulsion engine comprising a gas turbine engine disposed within a substantially cylindrical outer casing to form a by-pass duct which is provided with combustion means and an exhaust nozzle, has control vanes to control the air flow to the gas turbine engine to permit selective operation of the engine as a ducted fan engine or as a ram jet and means to vary the configuration of the by-pass exhaust nozzle in accordance with the position of the control vanes. A compressor 10 supplies combustion air to combustion equipment 11 feeding a turbine 12 driving the compressor. The exhaust of the turbine 12 is used to drive a turbine 14 before passing through a duct 20 which terminates in a convergent nozzle 24. The turbine 14 drives fan blades 15 arranged in a duct 16 formed by a casing 17 extending around the inner casing 18. Combustion means 27 is provided in the duct 16. The compressor 10 has control vanes 13 to control the air admission to the compressor which vanes are connected through linkage 23 to an actuator 21 which moves the duct 20 axially. The duct 20 has protuberances 26 which co-operate with protuberances 25 on the casing 17 to form a variable-area nozzle. At take-off and low Mach numbers, the vanes 13 are open and the duct 20 on the position shown. Since the area at X is less than that at Y, the nozzle is convergent. At Mach numbers between 2 and 3 the fuel supply to the combustion equipment 11 is gradually reduced until it is shut off. The vanes 13 are then closed. The entire air flow now passes through duct 16 and the effective area of the propelling nozzle thereby reduced by the amount W. As the area of W is half that of X the area is reduced by one third. To further reduce the area at high Mach numbers the duct 20 is retracted so that the protuberances 25 to 26 become opposite one another which further reduces the effective throat area and also forms a convergentdivergent nozzle.
GB4147359A 1959-12-07 1959-12-07 Improvements in or relating to ducted-fan gas turbine jet propulsion engines Expired GB875496A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB4147359A GB875496A (en) 1959-12-07 1959-12-07 Improvements in or relating to ducted-fan gas turbine jet propulsion engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4147359A GB875496A (en) 1959-12-07 1959-12-07 Improvements in or relating to ducted-fan gas turbine jet propulsion engines

Publications (1)

Publication Number Publication Date
GB875496A true GB875496A (en) 1961-08-23

Family

ID=10419848

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4147359A Expired GB875496A (en) 1959-12-07 1959-12-07 Improvements in or relating to ducted-fan gas turbine jet propulsion engines

Country Status (1)

Country Link
GB (1) GB875496A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2205360A (en) * 1987-05-27 1988-12-07 Mtu Muenchen Gmbh Composite fanjet/ramjet propulsion device
GB2243877A (en) * 1990-03-31 1991-11-13 Messerschmitt Boelkow Blohm Adjustable nozzle for hypersonic engine combustion chamber
US5284014A (en) * 1991-10-16 1994-02-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation ("S.N.E.C.M.A.") Turbojet-ramjet hypersonic aircraft engine
WO2008045089A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Core cowl airfoil for a gas turbine engine
JP2015200191A (en) * 2014-04-04 2015-11-12 株式会社Ihi jet engine
CN108626025A (en) * 2018-04-28 2018-10-09 上海啸风航空科技有限公司 A kind of double ducts of novel microminiature are vented fanjet respectively
US10975775B2 (en) 2015-05-27 2021-04-13 Ihi Corporation Jet engine

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2205360A (en) * 1987-05-27 1988-12-07 Mtu Muenchen Gmbh Composite fanjet/ramjet propulsion device
US4909031A (en) * 1987-05-27 1990-03-20 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Combined multi-speed jet engine for the drive of airplanes and space vehicles
GB2205360B (en) * 1987-05-27 1992-01-22 Mtu Muenchen Gmbh Composite changeover-type reaction power unit for aircraft
GB2243877A (en) * 1990-03-31 1991-11-13 Messerschmitt Boelkow Blohm Adjustable nozzle for hypersonic engine combustion chamber
US5284014A (en) * 1991-10-16 1994-02-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviation ("S.N.E.C.M.A.") Turbojet-ramjet hypersonic aircraft engine
WO2008045089A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Core cowl airfoil for a gas turbine engine
US8272204B2 (en) 2006-10-12 2012-09-25 United Technologies Corporation Core cowl airfoil for a gas turbine engine
JP2015200191A (en) * 2014-04-04 2015-11-12 株式会社Ihi jet engine
US10975775B2 (en) 2015-05-27 2021-04-13 Ihi Corporation Jet engine
CN108626025A (en) * 2018-04-28 2018-10-09 上海啸风航空科技有限公司 A kind of double ducts of novel microminiature are vented fanjet respectively

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