GB1340363A - Gas turbine power plants - Google Patents

Gas turbine power plants

Info

Publication number
GB1340363A
GB1340363A GB116071A GB116071A GB1340363A GB 1340363 A GB1340363 A GB 1340363A GB 116071 A GB116071 A GB 116071A GB 116071 A GB116071 A GB 116071A GB 1340363 A GB1340363 A GB 1340363A
Authority
GB
United Kingdom
Prior art keywords
shaft
homopolar
compressor
rotor
discs
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
GB116071A
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of GB1340363A publication Critical patent/GB1340363A/en
Expired legal-status Critical Current

Links

Classifications

    • HELECTRICITY
    • H02GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02KDYNAMO-ELECTRIC MACHINES
    • H02K31/00Acyclic motors or generators, i.e. DC machines having drum or disc armatures with continuous current collectors
    • H02K31/04Acyclic motors or generators, i.e. DC machines having drum or disc armatures with continuous current collectors with at least one liquid-contact collector
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10Adaptations for driving, or combinations with, electric generators
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02Blade-carrying members, e.g. rotors
    • F01D5/06Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06Gas-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
    • F02C3/067Gas-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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • F02C3/113Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/04Air intakes for gas-turbine plants or jet-propulsion plants
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00Features, 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
    • F02C7/36Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00Application
    • F05D2220/30Application in turbines
    • F05D2220/32Application in turbines in gas turbines
    • F05D2220/327Application in turbines in gas turbines to drive shrouded, high solidity propeller
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft

Abstract

1340363 Homopolar machines SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 11 Jan 1971 [15 Jan 1970] 1160/71 Heading H2A [Also in Division F1] A gas turbine engine comprises a compressor and a turbine, the turbine driving at least one homopolar electrical generator and the compressor being driven by at least one homopolar motor supplied with current from the generator. A number of different homopolar machine constructions are described. First embodiment (Fig. 2).-A number of homopolar motors each driving one stage of a compressor are carried by a stationary shaft structure 5 comprising a centre shaft 11, an intermediate shaft 16 and an outer cylinder 44. The first stage of the compressor comprises blades 120 mounted on a rotor disc 124, 126, 128, the part 128 constituting the armature of a homopolar motor through which current flows axially as indicated by arrow I. The armature is rotatably supported on the shaft 16 by means of films of liquid metal disposed at the surfaces 130, 131, a member 134 being secured on the shaft 16 but electrically insulated therefrom. The films of liquid metal permit the passage of the current I. Superconducting field coils 36, 136 are disposed between the shafts 11 and 16 within a casing 45 having an inlet and outlet 46, 48 for the flow of liquid helium and generate a magnetic flux as indicated by arrows B. The second stage 222 is similar to the first stage except that the magnetic field generated by the field coils 136, 236 flows radially outwardly through the armature 228 whereby the second stage rotates in the opposite direction to the first stage. The remaining compressor stages are similar. Second embodiment (Fig. 3).-A homopolar generating arrangement comprises two rotors 154, 254 driven by respective contra-rotating turbines, as 150, and mounted on the shaft 16 and on a ring member 54 secured on the shaft by means of films, as 161, 162, of liquid metal which allow the flow of current as indicated by arrows I. The superconducting field coils 60, 160, 260, 164, 264 create a magnetic field as indicated by arrows B, and are each disposed within a casing 70 through which liquid helium flows. Third embodiment (Fig. 12).-Rotor members 1124 of a homopolar motor drive a drum 1120 which is rotatably mounted in bearings 1121, 1122 and which supports compressor blades 1119. The stator members 1123 of the motor are mounted on the stationary shaft structure 1128, 1129, 1130, the portion 1130 on which the stator members are mounted being non-conducting. Liquid metal films 1127 are provided between the rotor and stator members and the current flows as indicated by arrows I through the stationary shaft 1129, through the rotor and stator members 1124, 1123, through the stationary shaft 1128 and back through the stationary inner shaft 1111. The field coil which is a superconductor 1125 is mounted on stator structure 1126 and creates a magnetic field as indicated by arrow B. Fourth embodiment (Fig. 13).-Rotor discs 1224 of a homopolar motor carry compressor blades 1219 and are rotatably mounted on a fixed shaft member 1211. Disc members 1223 are fixedly mounted on the shaft and carry superconducting field coils 1225 which generate a magnetic field B; the coils 1225 are disposed within casings 1225a through which liquid helium is circulated. Alternate members 1223 form supports for the rotor discs 1224 by means of rings 1227b of liquid metal which also allow passage of current I. The discs are also supported on the stationary shaft 1211 or central flanges of the dises 1223 by means of rings 1227a of liquid metal. Current flows through the outer stationary shaft member 1212, rotor discs 1224 and stator discs 1223a and 1223b as indicated by arrows I, the current returning through stationary shaft 1211. The stator discs 1223a, 1223b are insulated from the shaft 1211 by a layer of alumina. The current flows in opposite radial directions in adjacent rotor discs and the discs therefore are driven in opposite directions. Fifth embodiment (Fig. 15).-A homopolar generator 14c driven by a compressor supplies power to a homoplar motor 15c driving a fan 1c. The generator comprises a disc 16c connected to an extension 19c of the compressor shaft 20c, the extension being mounted in a bearing 21c. The motor comprises a disc 17c secured to a shaft 23c which is connected at its forward end 22c to the fan rotor 1c; the bearing 25c being supported in fixed structure 27c and the bearing 26c being located within the shaft extension 19c in the plane of the bearing 21c. The field winding 33c is a superconductor.
GB116071A 1970-01-15 1971-01-11 Gas turbine power plants Expired GB1340363A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7001437A FR2076450A5 (en) 1970-01-15 1970-01-15

Publications (1)

Publication Number Publication Date
GB1340363A true GB1340363A (en) 1973-12-12

Family

ID=9049087

Family Applications (1)

Application Number Title Priority Date Filing Date
GB116071A Expired GB1340363A (en) 1970-01-15 1971-01-11 Gas turbine power plants

Country Status (4)

Country Link
US (1) US3705775A (en)
DE (1) DE2101918C3 (en)
FR (1) FR2076450A5 (en)
GB (1) GB1340363A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5694765A (en) * 1993-07-06 1997-12-09 Rolls-Royce Plc Shaft power transfer in gas turbine engines with machines operable as generators or motors
US5722229A (en) * 1994-07-30 1998-03-03 Provost; Michael J. Auxiliary gas turbine engines
US5867979A (en) * 1996-03-28 1999-02-09 Rolls-Royce Plc Gas turbine engine system
GB2372157A (en) * 2001-02-09 2002-08-14 Rolls Royce Plc Integral electrical machine in gas turbine
EP1800005A2 (en) * 2004-09-16 2007-06-27 Harris Corporation Embedded fluid pump using a homopolar motor
CN110318815A (en) * 2019-07-18 2019-10-11 北京动力机械研究所 A kind of closed cycle turbine electricity generation system ceramic rotor
CN111636976A (en) * 2020-06-08 2020-09-08 清华大学 Three-duct high-thrust-weight-ratio efficient power propeller
RU2808879C1 (en) * 2023-03-01 2023-12-05 Сергей Юрьевич Негруб Schematic diagrams of gas turbine engine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4591313A (en) * 1983-12-30 1986-05-27 The Boeing Company Propeller pitch control system and apparatus
FR2759734B1 (en) * 1997-02-20 1999-04-09 Snecma TURBOMACHINE WITH OPTIMIZED COMPRESSION SYSTEM
US6261070B1 (en) * 1998-09-17 2001-07-17 El Paso Natural Gas Company In-line electric motor driven compressor
DE10017649A1 (en) * 1999-08-09 2003-08-07 Frank Wiedenfeld Continuously variable electromagnetic transmission (SEG)
AU2003299459A1 (en) * 2002-04-15 2004-11-04 Marius A. Paul Integrated bypass turbojet engines for aircraft and other vehicles
US6966174B2 (en) * 2002-04-15 2005-11-22 Paul Marius A Integrated bypass turbojet engines for air craft and other vehicles
FR2842565B1 (en) * 2002-07-17 2005-01-28 Snecma Moteurs INTEGRATED GENERATOR STARTER FOR TURBOMACHINE
US6942451B1 (en) 2003-06-03 2005-09-13 Hamilton Sundstrand Corporation Damping system for an expendable gas turbine engine
US7194866B1 (en) 2003-06-20 2007-03-27 Hamilton Sundstrand Corporation Static structure for an expendable gas turbine engine
US8438858B1 (en) 2003-08-20 2013-05-14 Hamilton Sundstrand Corporation Rotational system for an expendable gas turbine engine
US7150431B2 (en) * 2004-01-14 2006-12-19 Mjd Innovations, L.L.C. Electrical generator fluid-flow-coolant filtration
DE102004026367B4 (en) * 2004-05-29 2014-05-28 MTU Aero Engines AG turbomachinery
EP1614855A1 (en) * 2004-07-05 2006-01-11 Siemens Aktiengesellschaft Turbomachine and method to operate such a turbomachine
US7371052B2 (en) * 2004-08-16 2008-05-13 Harris Corporation Embedded fluid mixing device using a homopolar motor
US7607286B2 (en) 2004-12-01 2009-10-27 United Technologies Corporation Regenerative turbine blade and vane cooling for a tip turbine engine
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WO2006062497A1 (en) 2004-12-04 2006-06-15 United Technologies Corporation Tip turbine engine mount
FR2896537B1 (en) * 2006-01-24 2011-07-29 Snecma TURBOMACHINE WITH INTEGRATED GENERATOR-STARTER
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US20090288628A1 (en) * 2008-05-21 2009-11-26 Rolls-Royce North American Technologies, Inc. Electrically isolated rotor ground
DE102008031986B4 (en) * 2008-07-07 2014-09-25 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine with counter-rotating compressor modules
DE102008031932A1 (en) * 2008-07-07 2010-01-14 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine with at least one multi-stage compressor unit comprising a plurality of compressor modules
US20100126178A1 (en) * 2008-10-08 2010-05-27 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Hybrid propulsive engine including at least one independently rotatable turbine stator
US8549833B2 (en) * 2008-10-08 2013-10-08 The Invention Science Fund I Llc Hybrid propulsive engine including at least one independently rotatable compressor stator
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US9046001B2 (en) 2011-08-29 2015-06-02 Honeywell International Inc. Annular bearing support dampers, gas turbine engines including the same, and methods for the manufacture thereof
US9297438B2 (en) 2012-01-25 2016-03-29 Honeywell International Inc. Three parameter damper anisotropic vibration isolation mounting assembly
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WO2014150377A1 (en) * 2013-03-15 2014-09-25 Embry-Riddle Aeronautical University, Inc. Electrically coupled counter-rotation for gas turbine compressors
US10954792B2 (en) * 2013-03-15 2021-03-23 Sonic Blue Aerospace, Inc. Superconducting power shaft core
EP2824330A1 (en) * 2013-07-12 2015-01-14 Johnson Controls Denmark ApS An axial compressor and use of an axial compressor
US9371776B2 (en) * 2013-08-20 2016-06-21 Darren Levine Dual flow air injection intraturbine engine and method of operating same
CN105569737A (en) * 2014-10-30 2016-05-11 熵零股份有限公司 Impeller rotation fluid mechanism with electromagnetic counterparts and heat power system of impeller rotation fluid mechanism
US9702404B2 (en) 2015-10-28 2017-07-11 United Technologies Corporation Integral centering spring and bearing support and method of supporting multiple damped bearings
US10378452B1 (en) * 2018-02-26 2019-08-13 The Boeing Company Hybrid turbine jet engines and methods of operating the same
GB201902095D0 (en) * 2019-02-15 2019-04-03 Rolls Royce Plc Electric turbomachine
US11342831B2 (en) 2019-10-07 2022-05-24 Lockheed Martin Corporation Homopolar turbine
US10941707B1 (en) 2019-10-18 2021-03-09 The Boeing Company Hybrid turbine engines, aircraft including the same, and associated methods
US11203439B2 (en) 2019-10-18 2021-12-21 The Boeing Company Rotary electric engines, aircraft including the same, and associated methods
US11274557B2 (en) 2019-11-27 2022-03-15 General Electric Company Damper assemblies for rotating drum rotors of gas turbine engines
US11280219B2 (en) 2019-11-27 2022-03-22 General Electric Company Rotor support structures for rotating drum rotors of gas turbine engines
GB2610571A (en) 2021-09-08 2023-03-15 Rolls Royce Plc An improved gas turbine engine
GB2610573A (en) * 2021-09-08 2023-03-15 Rolls Royce Plc An improved gas turbine engine

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB595357A (en) * 1944-04-08 1947-12-03 Power Jets Res & Dev Ltd Improvements in or relating to power plants
US2914688A (en) * 1954-01-04 1959-11-24 Baso Inc Homopolar motor
US3585398A (en) * 1969-10-13 1971-06-15 Gen Electric Brushless excitation of a steam turbine generator utilizing a driver acyclic generator

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5694765A (en) * 1993-07-06 1997-12-09 Rolls-Royce Plc Shaft power transfer in gas turbine engines with machines operable as generators or motors
US5722229A (en) * 1994-07-30 1998-03-03 Provost; Michael J. Auxiliary gas turbine engines
US5867979A (en) * 1996-03-28 1999-02-09 Rolls-Royce Plc Gas turbine engine system
GB2372157A (en) * 2001-02-09 2002-08-14 Rolls Royce Plc Integral electrical machine in gas turbine
US6729140B2 (en) 2001-02-09 2004-05-04 Rolls-Royce Plc Electrical machine
GB2372157B (en) * 2001-02-09 2005-07-06 Rolls Royce Plc A gas turbine with an electrical machine
EP1800005A2 (en) * 2004-09-16 2007-06-27 Harris Corporation Embedded fluid pump using a homopolar motor
EP1800005A4 (en) * 2004-09-16 2010-10-20 Harris Corp Embedded fluid pump using a homopolar motor
CN110318815A (en) * 2019-07-18 2019-10-11 北京动力机械研究所 A kind of closed cycle turbine electricity generation system ceramic rotor
CN110318815B (en) * 2019-07-18 2022-07-08 北京动力机械研究所 Ceramic rotor of closed-cycle turbine power generation system
CN111636976A (en) * 2020-06-08 2020-09-08 清华大学 Three-duct high-thrust-weight-ratio efficient power propeller
RU2808879C1 (en) * 2023-03-01 2023-12-05 Сергей Юрьевич Негруб Schematic diagrams of gas turbine engine

Also Published As

Publication number Publication date
US3705775A (en) 1972-12-12
DE2101918B2 (en) 1975-01-09
DE2101918A1 (en) 1971-07-22
DE2101918C3 (en) 1975-08-21
FR2076450A5 (en) 1971-10-15

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