GB1503425A - Gas turbine ducted fan jet engines for supersonic flight - Google Patents

Gas turbine ducted fan jet engines for supersonic flight

Info

Publication number
GB1503425A
GB1503425A GB1131676A GB1131676A GB1503425A GB 1503425 A GB1503425 A GB 1503425A GB 1131676 A GB1131676 A GB 1131676A GB 1131676 A GB1131676 A GB 1131676A GB 1503425 A GB1503425 A GB 1503425A
Authority
GB
United Kingdom
Prior art keywords
fan
turbine
wall
fan duct
nozzle
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
GB1131676A
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.)
HALLOWELL E
Original Assignee
HALLOWELL E
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 HALLOWELL E filed Critical HALLOWELL E
Priority to GB1131676A priority Critical patent/GB1503425A/en
Publication of GB1503425A publication Critical patent/GB1503425A/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
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
    • F02K3/105—Heating the by-pass flow
    • F02K3/11—Heating the by-pass flow by means of burners or combustion chambers
    • 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
    • F02K1/09—Varying effective area of jet pipe or nozzle by axially moving an external member, e.g. a shroud

Landscapes

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

Abstract

1503425 Gas turbine ducted fan engines E HALLOWELL 4 Aug 1976 [20 March 1976 9 April 1976] 11316/76 and 14705/76 Heading F1J The invention relates to a gas turbine ducted fan engine in which provision is made for burning fuel in the fan duct and in which the fan duct outlet nozzle is of variable form. The engine shown comprises a core engine comprising a compressor 11, combustion equipment 14 and a turbine 10, and a further turbine 12 which drives a fan 13. The turbine exhaust gases discharge through a nozzle 15, exhaust reheat equipment 18 being provided. The fan 13 discharges air through fan duct 19 and fuel injectors 25 are provided in the fan duct, the fuel flowing through coils 27 to provide a cooling effect. The outer wall of the fan duct comprises a fixed wall 20 and an axially movable wall 21 which in the retracted position shown in full lines defines with the inner wall 16 an annular convergent nozzle, and in the extended position shown in broken lines defines with the inner wall a convergent-divergent nozzle. A valve assembly 31 is provided whereby combustion gases and air in the fan duct may pass into the chamber 30 so as to mix with the core engine gases before passing through the fan driving turbine 12; gas flow in the opposite direction is prevented.
GB1131676A 1976-08-04 1976-08-04 Gas turbine ducted fan jet engines for supersonic flight Expired GB1503425A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1131676A GB1503425A (en) 1976-08-04 1976-08-04 Gas turbine ducted fan jet engines for supersonic flight

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1131676A GB1503425A (en) 1976-08-04 1976-08-04 Gas turbine ducted fan jet engines for supersonic flight

Publications (1)

Publication Number Publication Date
GB1503425A true GB1503425A (en) 1978-03-08

Family

ID=9984036

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1131676A Expired GB1503425A (en) 1976-08-04 1976-08-04 Gas turbine ducted fan jet engines for supersonic flight

Country Status (1)

Country Link
GB (1) GB1503425A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2434838A (en) * 2006-02-03 2007-08-08 Stephen Desmond Lewis Supersonic turbofan engine
WO2008045049A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US9074531B2 (en) 2008-03-05 2015-07-07 United Technologies Corporation Variable area fan nozzle fan flutter management system
US11008976B2 (en) 2018-10-12 2021-05-18 Rolls-Royce Plc Afterburner system for turbofan engine
CN114320612A (en) * 2021-12-08 2022-04-12 北京航空航天大学 Engine outer duct backflow control method and device, engine and aircraft
US11454193B2 (en) 2007-08-23 2022-09-27 Raytheon Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2434838A (en) * 2006-02-03 2007-08-08 Stephen Desmond Lewis Supersonic turbofan engine
WO2008045049A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US11454193B2 (en) 2007-08-23 2022-09-27 Raytheon Technologies Corporation Gas turbine engine with axial movable fan variable area nozzle
US9074531B2 (en) 2008-03-05 2015-07-07 United Technologies Corporation Variable area fan nozzle fan flutter management system
US11008976B2 (en) 2018-10-12 2021-05-18 Rolls-Royce Plc Afterburner system for turbofan engine
CN114320612A (en) * 2021-12-08 2022-04-12 北京航空航天大学 Engine outer duct backflow control method and device, engine and aircraft

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Legal Events

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