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GB587528A - Improvements in or relating to internal combustion turbine power plants - Google Patents

Improvements in or relating to internal combustion turbine power plants

Info

Publication number
GB587528A
GB587528A GB181044A GB181044A GB587528A GB 587528 A GB587528 A GB 587528A GB 181044 A GB181044 A GB 181044A GB 181044 A GB181044 A GB 181044A GB 587528 A GB587528 A GB 587528A
Authority
GB
United Kingdom
Prior art keywords
stator
turbine
compressor
power
blades
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
GB181044A
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development 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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB181044A priority Critical patent/GB587528A/en
Publication of GB587528A publication Critical patent/GB587528A/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
    • 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
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • 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
    • F02K3/065—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 with front and aft fans
    • 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
    • F02K3/072—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 with counter-rotating, e.g. fan rotors

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

587,528. Gas turbine plant; screw fans. POWER JETS (RESEARCH & DEVELOPMENT), Ltd., and HOWELL, A. R. Jan. 31, 1944, Nos. 1810 and 11035. [Classes 110 (i) and 110 (iii)] In a gas turbine plant comprising axial flow turbine and air compressor, useful power is taken off at relatively low speed by means of a rotating turbine or compressor stator, or both. In Fig. 1, the stator 21 of the compressor rotates in the same direction as, but at a lower speed than, the turbine-compressor rotor 32, 15 and carries an'air-screw 22. In another form, the turbine stator rotates and carries jetaugmentor blades. In Fig. 3, the turbine stator 60 and the H.P. part 66 of the compressor stator rotate and carry jet-augmentor blades 61, 71 arranged in series in the duct 82. In a fourth form in which all the useful power is shaft power, the turbine stator and the whole compressor stator rotate and are geared together. Power is taken off these stators by means of hollow shafts mounted about the turbine-compressor rotor shaft. As shown in Fig. 3, the rotor shaft 14 and the stator sleeve shafts 45, 77 are mounted in bearings supported by an intervening bearing sleeve 48. Specification 396,622 is referred to.
GB181044A 1944-01-31 1944-01-31 Improvements in or relating to internal combustion turbine power plants Expired GB587528A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB181044A GB587528A (en) 1944-01-31 1944-01-31 Improvements in or relating to internal combustion turbine power plants

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB181044A GB587528A (en) 1944-01-31 1944-01-31 Improvements in or relating to internal combustion turbine power plants

Publications (1)

Publication Number Publication Date
GB587528A true GB587528A (en) 1947-04-29

Family

ID=9728416

Family Applications (1)

Application Number Title Priority Date Filing Date
GB181044A Expired GB587528A (en) 1944-01-31 1944-01-31 Improvements in or relating to internal combustion turbine power plants

Country Status (1)

Country Link
GB (1) GB587528A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2514408A (en) * 1948-04-19 1950-07-11 Westinghouse Electric Corp Gas turbine apparatus
US2831320A (en) * 1953-10-09 1958-04-22 Ward E Duncan External turbine jet engine
US4192137A (en) * 1977-03-04 1980-03-11 Canadian Patents And Development Limited Turboshaft engine
EP0394102A1 (en) * 1989-04-18 1990-10-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Counter-rotating engine with high bypass fans fore and aft
US5077968A (en) * 1990-04-06 1992-01-07 United Technologies Corporation Vaneless contrarotating turbine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2514408A (en) * 1948-04-19 1950-07-11 Westinghouse Electric Corp Gas turbine apparatus
US2831320A (en) * 1953-10-09 1958-04-22 Ward E Duncan External turbine jet engine
US4192137A (en) * 1977-03-04 1980-03-11 Canadian Patents And Development Limited Turboshaft engine
EP0394102A1 (en) * 1989-04-18 1990-10-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Counter-rotating engine with high bypass fans fore and aft
US5058379A (en) * 1989-04-18 1991-10-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation High by-pass ratio turbojet engine with counterrotating upstream and downstream fans
US5077968A (en) * 1990-04-06 1992-01-07 United Technologies Corporation Vaneless contrarotating turbine

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