GB919113A - Improvements in or relating to aircraft propulsive means - Google Patents

Improvements in or relating to aircraft propulsive means

Info

Publication number
GB919113A
GB919113A GB869660A GB869660A GB919113A GB 919113 A GB919113 A GB 919113A GB 869660 A GB869660 A GB 869660A GB 869660 A GB869660 A GB 869660A GB 919113 A GB919113 A GB 919113A
Authority
GB
United Kingdom
Prior art keywords
air
turbine
engine
jet
surrounding
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
GB869660A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB869660A priority Critical patent/GB919113A/en
Publication of GB919113A publication Critical patent/GB919113A/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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/32—Inducing air flow by fluid jet, e.g. ejector action
    • 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
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/077—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof

Landscapes

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

Abstract

919,113. Jet propulsion engines. GARDEN, A. D. March 11, 1960, No. 8696/60. Class 110(3). A jet turbine engine 2 which directs part of its propulsive gas flow into the air surrounding the engine to accelerate the surrounding air flow rearwardly to increase the propulsive efficiency of the engine, is housed within a tubular housing 1. Some of the air entering the inlet 4 passes through the hollow shaft 18 to cool the engine and be expelled into the jet pipe 9. Part of the air entering the compressor 5 is bled out into the surrounding space 3 by a plurality of outlets 6, the remainder of the compressed air either passing through the combustion chambers 7, the turbine 8 and into the pipe 9 or by-passing the combustion chambers and being expelled just aft of the turbine. The air leaving the outlets 6 is divided into two streams by an annular housing having additional burners 14. Controlplates 15 are provided at the outlet of this housing to allow variation of the amount of extra thrust obtainable from air passing the burners 14. Part of the main jet stream leaving the turbine is bled into the space 3 by means of a plurality of outlets 10 in the jet pipe. The main stream leaving the jet pipe may be subjected to after-burning at 12 before leaving the outlet 11 of the housing 1. Additional propulsive means comprising the peripheral portion 20 of part of the compressor is provided to accelerate the surrounding air. The invention is stated to be also applicable to propulsive means including propeller turbine engines, rockets, and piston engine driven propellers.
GB869660A 1960-03-11 1960-03-11 Improvements in or relating to aircraft propulsive means Expired GB919113A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB869660A GB919113A (en) 1960-03-11 1960-03-11 Improvements in or relating to aircraft propulsive means

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB869660A GB919113A (en) 1960-03-11 1960-03-11 Improvements in or relating to aircraft propulsive means

Publications (1)

Publication Number Publication Date
GB919113A true GB919113A (en) 1963-02-20

Family

ID=9857486

Family Applications (1)

Application Number Title Priority Date Filing Date
GB869660A Expired GB919113A (en) 1960-03-11 1960-03-11 Improvements in or relating to aircraft propulsive means

Country Status (1)

Country Link
GB (1) GB919113A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2605679A1 (en) * 1986-10-24 1988-04-29 Culica Georges Francois Multi-spool multi-bypass turbo jet engine with a drum rotor
GB2201467A (en) * 1987-02-24 1988-09-01 Teledyne Ind A turbocharged compound cycle ducted fan engine
WO2001048365A1 (en) * 1999-12-23 2001-07-05 Mathias Meyer Turbojet engine
CN108412615A (en) * 2018-04-25 2018-08-17 大连恒通和科技有限公司 Vortex-spraying type power generation combustor

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2605679A1 (en) * 1986-10-24 1988-04-29 Culica Georges Francois Multi-spool multi-bypass turbo jet engine with a drum rotor
GB2201467A (en) * 1987-02-24 1988-09-01 Teledyne Ind A turbocharged compound cycle ducted fan engine
WO2001048365A1 (en) * 1999-12-23 2001-07-05 Mathias Meyer Turbojet engine
EP1469184A1 (en) * 1999-12-23 2004-10-20 Mathias Meyer Turbo jet engine
CN108412615A (en) * 2018-04-25 2018-08-17 大连恒通和科技有限公司 Vortex-spraying type power generation combustor

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