GB905136A - Improvements relating to gas turbine power units - Google Patents

Improvements relating to gas turbine power units

Info

Publication number
GB905136A
GB905136A GB1286261A GB1286261A GB905136A GB 905136 A GB905136 A GB 905136A GB 1286261 A GB1286261 A GB 1286261A GB 1286261 A GB1286261 A GB 1286261A GB 905136 A GB905136 A GB 905136A
Authority
GB
United Kingdom
Prior art keywords
compressor
oil
pump
turbine
space
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
GB1286261A
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 GB905136A publication Critical patent/GB905136A/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
    • F02C3/073—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 the compressor and turbine stages being concentric
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

905,136. Gas-turbine plant. DAIMLER-BENZ A.G. April 10, 1961 [April 12, 1960], No. 12862/61. Class 110 (3). A gas-turbine power unit in which each rotor disc carries rings of both compressor and turbine blades separated radially by an annular ring, has an annular, or plurality of annularly disposed combustion chambers surrounding an internal space containing all or almost all the auxiliary units. Each of the rotors L carry compressor blades 11 and turbine blades 12 separated by an annular ring 13. The combustion chamber or chambers 14 in which the direction of flow is reversed, surround a space J containing the auxiliaries, e.g. an oil centrifuge 15, an oil pump 16, a regulator 17, a centrifugal fuel pump 18, an oil and fuel filter 19 and a starting motor 20. The auxiliaries are driven by a common gearing 6. The pump 18 may be mounted on the shaft 26 and a centrifugal governor 17<SP>1</SP> on shaft 29. A part of the air flow from the compressor passes through openings 30 into space J to cool the auxiliary units. A thermal insulating layer or wall 31 may be applied to the radially inner side of the combustion chambers.
GB1286261A 1960-04-12 1961-04-10 Improvements relating to gas turbine power units Expired GB905136A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DED0033090 1960-04-12

Publications (1)

Publication Number Publication Date
GB905136A true GB905136A (en) 1962-09-05

Family

ID=7041589

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1286261A Expired GB905136A (en) 1960-04-12 1961-04-10 Improvements relating to gas turbine power units

Country Status (1)

Country Link
GB (1) GB905136A (en)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3296804A (en) * 1962-08-24 1967-01-10 Rolls Royce Gas turbine vertical lift engine
WO2006060011A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
WO2006059989A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine support structure
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3296804A (en) * 1962-08-24 1967-01-10 Rolls Royce Gas turbine vertical lift engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US10760483B2 (en) 2004-12-01 2020-09-01 Raytheon Technologies Corporation Tip turbine engine composite tailcone
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
WO2006059989A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine support structure
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8276362B2 (en) 2004-12-01 2012-10-02 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
WO2006060011A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
US9109537B2 (en) 2004-12-04 2015-08-18 United Technologies Corporation Tip turbine single plane mount

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