EP1697623A1 - Turbine a gaz, notamment groupe motopropulseur, et procede pour produire de l'energie electrique dans une turbine a gaz - Google Patents

Turbine a gaz, notamment groupe motopropulseur, et procede pour produire de l'energie electrique dans une turbine a gaz

Info

Publication number
EP1697623A1
EP1697623A1 EP04819575A EP04819575A EP1697623A1 EP 1697623 A1 EP1697623 A1 EP 1697623A1 EP 04819575 A EP04819575 A EP 04819575A EP 04819575 A EP04819575 A EP 04819575A EP 1697623 A1 EP1697623 A1 EP 1697623A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
core engine
electrical energy
generator
shaft
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.)
Withdrawn
Application number
EP04819575A
Other languages
German (de)
English (en)
Inventor
Hermann Klingels
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1697623A1 publication Critical patent/EP1697623A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • 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
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/275—Mechanical drives
    • F02C7/277—Mechanical drives the starter being a separate turbine
    • 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
    • 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
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
    • B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
    • B64D2013/0603—Environmental Control Systems
    • B64D2013/0644—Environmental Control Systems including electric motors or generators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/70—Application in combination with
    • F05D2220/76—Application in combination with an electrical generator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • Y—GENERAL 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency

Definitions

  • the present invention is based on the problem of creating a novel gas turbine, in particular a novel aircraft engine, and a novel method for generating electrical energy in a gas turbine, in particular in an aircraft engine.
  • the present invention it is within the meaning of the present invention to generate the electrical energy exclusively from the mechanical shaft power dissipated in a high load range of the core engine.
  • the required electrical energy is generated on the one hand from the mechanical shaft power dissipated and on the other hand from the pneumatic energy contained in the compressed air.
  • the reference number 15 denotes a working line of the high-pressure compressor, which is set when the invention is used.
  • a middle section 16 of the working line 15 there is a switchover between the two states, which in principle are to be distinguished from one another, whereby, as already mentioned, in a first state the electrical power is generated exclusively by drawing mechanical shaft power, and in the second state the electrical power is generated is also obtained from the pneumatic energy contained in the discharged, compressed air.
  • the transmission 20 assigned to the first generator 21 and the second transmission 25 assigned to the second generator 26 can be connected to one another via a coupling 27.
  • the clutch 27 can be controlled and either decouples the two transmissions 20 and 25 from one another or couples them together.
  • a so-called freewheel 28 is integrated into the shaft 24, which is driven by the air turbine 23.
  • both the first generator 21 and the second generator 26 are driven exclusively by the shaft 19 of the high-pressure compressor 17 and the two generators 21 and 26 convert the extracted mechanical power into corresponding electrical energy.
  • the clutch 27 is opened and the two gears 20 and 25 and the two generators 21 and 26 are decoupled from one another.
  • the valve 22 is open and compressed air is removed from the high-pressure compressor 17 and fed to the air turbine 23.
  • the freewheel 28 couples the shaft 24 to the second gear 25, so that the air turbine
  • Figure 3 shows a second embodiment of the invention.
  • 3 shows a high-pressure compressor 32 of a core engine 33 with a corresponding shaft 34, mechanical power being taken from the shaft 34 and this being applied to a generator 36 or to a plurality of generators for generating electrical energy.
  • compressed air can also be taken from the high-pressure compressor 32 via a controllable valve 37, the compressed air being fed to an air turbine 38 of the engine, a so-called engine starter.
  • the air turbine 38 can also be used as a starting device.
  • the air turbine 38 or the starter converts the power contained in the extracted, compressed air into mechanical energy and drives a shaft via this mechanical energy.
  • the shaft driven by the air turbine 38 can either be coupled to or decoupled from the transmission 35 via a freewheel 39.
  • the procedure is such that the compressed air is supplied to the air turbine 38 via the valve 37 in the part-load operation of the high-pressure compressor 32.
  • the valve 37 can be controlled via control means 29. If a drive speed of the air turbine 38 is higher than a speed of a shaft on which the air turbine 38 is arranged, the freewheel 39 engages and transfers the mechanical energy generated to the transmission 35 and thus ultimately to the generator 36 for generating electrical energy.
  • Both exemplary embodiments have in common that compressed air is taken from the high-pressure compressor in the lower load range and electrical energy is generated from the power contained in the compressed air.
  • the working line of the high-pressure compressor can be influenced in such a way that the working line moves away from the surge line and thus a sufficient pump-limit distance can be maintained even in the lower load range of the high-pressure compressor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • General Health & Medical Sciences (AREA)
  • Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
  • Control Of Turbines (AREA)

Abstract

L'invention concerne une turbine à gaz, notamment un groupe motopropulseur, et un procédé pour produire de l'énergie électrique dans une turbine à gaz. Cette turbine à gaz comprend au moins un noyau central (18) dans lequel une puissance peut être fournie par un arbre (19). Selon l'invention, cette turbine à gaz comprend des moyens qui produisent de l'énergie électrique d'une part à partir de la puissance fournie par l'arbre du noyau central (18) et d'autre part à partir de l'air comprimé évacué du noyau central (18).
EP04819575A 2003-11-29 2004-11-05 Turbine a gaz, notamment groupe motopropulseur, et procede pour produire de l'energie electrique dans une turbine a gaz Withdrawn EP1697623A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10355917A DE10355917A1 (de) 2003-11-29 2003-11-29 Gasturbine, insbesondere Flugtriebwerk, und Verfahren zur Erzeugung elektrischer Energie bei einer Gasturbine
PCT/DE2004/002444 WO2005054645A1 (fr) 2003-11-29 2004-11-05 Turbine a gaz, notamment groupe motopropulseur, et procede pour produire de l'energie electrique dans une turbine a gaz

Publications (1)

Publication Number Publication Date
EP1697623A1 true EP1697623A1 (fr) 2006-09-06

Family

ID=34625408

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04819575A Withdrawn EP1697623A1 (fr) 2003-11-29 2004-11-05 Turbine a gaz, notamment groupe motopropulseur, et procede pour produire de l'energie electrique dans une turbine a gaz

Country Status (4)

Country Link
US (1) US7584600B2 (fr)
EP (1) EP1697623A1 (fr)
DE (1) DE10355917A1 (fr)
WO (1) WO2005054645A1 (fr)

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US7926287B2 (en) 2007-05-08 2011-04-19 Pratt & Whitney Canada Corp. Method of operating a gas turbine engine
US7854582B2 (en) 2007-05-08 2010-12-21 Pratt & Whitney Canada Corp. Operation of an aircraft engine after emergency shutdown
US8169100B2 (en) 2008-01-30 2012-05-01 Pratt & Whitney Canada Corp. Torque transmission for an aircraft engine
US8146370B2 (en) * 2008-05-21 2012-04-03 Honeywell International Inc. Turbine drive system with lock-up clutch and method
US8291715B2 (en) * 2008-06-11 2012-10-23 Honeywell International Inc. Bi-modal turbine assembly and starter / drive turbine system employing the same
US8039983B2 (en) * 2008-12-02 2011-10-18 The Boeing Company Systems and methods for providing AC power from multiple turbine engine spools
GB2476261A (en) * 2009-12-17 2011-06-22 Richard Julius Gozdawa A gas turbine generator
US8519555B2 (en) 2010-11-29 2013-08-27 Pratt & Whitney Canada Corp. Combination low spool generator and ram air turbine generator
US9261019B2 (en) * 2010-12-30 2016-02-16 Rolls-Royce North American Technologies, Inc. Variable cycle gas turbine engine
US9845734B2 (en) * 2011-04-20 2017-12-19 Honeywell International Inc. Air turbine start system with monopole starter air valve position
US8723385B2 (en) 2011-10-07 2014-05-13 General Electric Company Generator
US8723349B2 (en) 2011-10-07 2014-05-13 General Electric Company Apparatus for generating power from a turbine engine
EP2964931B1 (fr) 2013-03-07 2022-10-05 Rolls-Royce Corporation Récupérateur de véhicule
FR3003514B1 (fr) * 2013-03-25 2016-11-18 Eurocopter France Aeronef a voilure tournante a motorisation hybride.
CN103352961B (zh) * 2013-07-16 2016-08-10 中国南方航空工业(集团)有限公司 机匣传动机构及具有其的机匣
EP2887536B1 (fr) 2013-12-23 2019-02-27 Rolls-Royce Corporation Système de commande pour un moteur/générateur à double redondance et moteur
US10125692B2 (en) 2014-08-22 2018-11-13 Rolls-Royce Corporation Gas turbine engine system having a disengageable electric machine
US10119460B2 (en) * 2014-09-18 2018-11-06 General Electric Company Integrated turboshaft engine
FR3041052B1 (fr) 2015-09-14 2018-07-27 Safran Transmission Systems Boitier d'entrainement d'equipements dans une turbomachine
FR3041379B1 (fr) * 2015-09-18 2017-09-15 Snecma Turbopropulseur d'aeronef
US11203949B2 (en) 2016-08-11 2021-12-21 General Electric Company Mechanically driven air vehicle thermal management device
US10443506B2 (en) * 2017-07-26 2019-10-15 Unison Industries, Llc Air turbine starter
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US11746701B2 (en) * 2018-08-09 2023-09-05 Rolls-Royce North American Technologies, Inc. Bleed expander cooling with turbine
GB2592977B (en) * 2020-03-12 2023-03-08 Safran Electrical & Power Generator accessory drive
FR3135113A1 (fr) * 2022-04-28 2023-11-03 Safran Aircraft Engines Boîtier de relais d’accessoires et turbomachine d’aéronef comportant un tel boîtier

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Also Published As

Publication number Publication date
US7584600B2 (en) 2009-09-08
WO2005054645A1 (fr) 2005-06-16
US20070089420A1 (en) 2007-04-26
DE10355917A1 (de) 2005-06-30

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