GB863555A - Improvements relating to gas turbine power units - Google Patents

Improvements relating to gas turbine power units

Info

Publication number
GB863555A
GB863555A GB8501/58A GB850158A GB863555A GB 863555 A GB863555 A GB 863555A GB 8501/58 A GB8501/58 A GB 8501/58A GB 850158 A GB850158 A GB 850158A GB 863555 A GB863555 A GB 863555A
Authority
GB
United Kingdom
Prior art keywords
rotor
rotors
gas turbine
compressor
subsonic
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
GB8501/58A
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.)
Daimler Benz AG
Original Assignee
Daimler Benz AG
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 Daimler Benz AG filed Critical Daimler Benz AG
Publication of GB863555A publication Critical patent/GB863555A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D21/00—Pump involving supersonic speed of pumped fluids
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage pumps
    • F04D19/024—Multi-stage pumps with contrarotating parts

Landscapes

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

Abstract

863,555. Axial-flow compressors; gas turbine plant. DAIMLER-BENZ A.G. March 17, 1958 [March 15, 1957], No. 8501/58. Classes 110 (1) and 110 (3). A gas turbine plant comprises an axial flow compressor and turbine, each of which consists essentially of only two contra - rotating rotors situated one directly behind the other, one of the compressor rotors operating partly in the subsonic and partly in the supersonic range while the second compressor rotor operates only in the supersonic range. In the gas turbine engine shown, axial flow compressor rotors 5, 6 are driven in opposite directions by oppositelyrotating turbine rotors 9, 10. Rotor 6 is of supersonic type, while rotor 5 is of transonic type, the latter type being defined as one in which a part of each blade works in the supersonic range and the remaining part works in the subsonic range, the flow to the blading taking place at velocities of about unity Mach number. Subsonic guide blading 7 is provided. Rotor 5 may be preceded by inlet guide blading. The stage head of rotor 5 decreases radially outwardly, while that of rotor 6 increases radially outwardly, the total head of the two rotors being radially constant.
GB8501/58A 1957-03-15 1958-03-17 Improvements relating to gas turbine power units Expired GB863555A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE863555X 1957-03-15

Publications (1)

Publication Number Publication Date
GB863555A true GB863555A (en) 1961-03-22

Family

ID=6801544

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8501/58A Expired GB863555A (en) 1957-03-15 1958-03-17 Improvements relating to gas turbine power units

Country Status (1)

Country Link
GB (1) GB863555A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998030803A1 (en) * 1997-01-13 1998-07-16 Massachusetts Institute Of Technology Counter-rotating compressors with control of boundary layers by fluid removal

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1998030803A1 (en) * 1997-01-13 1998-07-16 Massachusetts Institute Of Technology Counter-rotating compressors with control of boundary layers by fluid removal

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