WO2005054645A1 - Gasturbine, insbesondere flugtriebwerk, und verfahren zur erzeugung elektrischer energie bei einer gasturbine - Google Patents
Gasturbine, insbesondere flugtriebwerk, und verfahren zur erzeugung elektrischer energie bei einer gasturbine Download PDFInfo
- Publication number
- WO2005054645A1 WO2005054645A1 PCT/DE2004/002444 DE2004002444W WO2005054645A1 WO 2005054645 A1 WO2005054645 A1 WO 2005054645A1 DE 2004002444 W DE2004002444 W DE 2004002444W WO 2005054645 A1 WO2005054645 A1 WO 2005054645A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- gas turbine
- core engine
- electrical energy
- generator
- shaft
- Prior art date
Links
- 238000000034 method Methods 0.000 title claims abstract description 14
- 230000005540 biological transmission Effects 0.000 claims description 9
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 239000007858 starting material Substances 0.000 claims description 3
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 8
- 238000011161 development Methods 0.000 description 3
- 230000018109 developmental process Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000004378 air conditioning Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000006735 deficit Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
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
- Gas turbine in particular aircraft engine, and method for generating electrical energy in a gas turbine
- the invention relates to a gas turbine, in particular an aircraft engine, according to the preamble of patent claim 1. Furthermore, the invention relates to a method for generating electrical energy in a gas turbine, in particular in an aircraft engine, according to the preamble of patent claim 16.
- Aircraft engines be it civil aircraft engines or military aircraft engines, generate not only a feed for locomotion of the aircraft but also energy for supplying add-on devices or auxiliary equipment for the gas turbine or for supplying aircraft-side systems, such as, for example, B. the air conditioning.
- add-on devices or auxiliary equipment for the gas turbine or for supplying aircraft-side systems, such as, for example, B. the air conditioning.
- To generate energy to supply the add-on devices or auxiliary device and the aircraft-side systems it is already known from the prior art to take mechanical energy from a core engine of the gas turbine, which, for. B. is used for driving pumps and generators. So shows z. B. DE 41 31 713 C2 an aircraft engine, shaft power is taken from a core engine and this shaft power is supplied to auxiliary units.
- the prior art has followed the path of designing the gas turbine, in particular its core engine, with a larger surge limit distance.
- This results in a larger overall length, in particular of the high-pressure compressor of the core engine, and in a larger number of stages, a larger number of blades and thus a greater weight and overall higher costs.
- the high-pressure compressor of the core engine is not designed with a larger surge limit distance, the only remaining option according to the state of the art is to lower the working line of the gas turbine, in particular of the core engine, to such an extent that an adequate surge limit distance is maintained even in part-load operation.
- this has the consequence that the optimum efficiency can no longer be achieved in full load operation and therefore an efficiency deficit arises.
- 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 gas turbine mentioned at the outset is further developed by the features of the characterizing part of patent claim 1.
- the gas turbine has means which, on the one hand, generate electrical energy from the shaft power discharged from the core engine and, on the other hand, generate electrical energy from the compressed air discharged from the core engine.
- the means generate the electrical energy exclusively from the mechanical shaft power dissipated in a high load range of the core engine.
- the means In a lower load range of the core engine, on the other hand, the means generate the electrical energy from the extracted mechanical shaft power and from the removed, compressed air.
- the inventive method for generating electrical energy in a gas turbine is characterized by the features of independent claim 16.
- FIG. 2 shows a block diagram to illustrate a first embodiment of the present invention
- FIG. 3 shows a block diagram to illustrate a second embodiment of the present invention.
- Figure 1 shows a map of a high pressure compressor of a core engine of a gas turbine.
- ⁇ is the compression ratio or pressure ratio of the high-pressure compressor
- m is the mass flow through the high-pressure compressor
- T is the temperature
- p is the pressure inside the high-pressure compressor
- n is the speed of the same.
- 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.
- FIG. 2 shows a first preferred embodiment of a gas turbine according to the invention in a highly schematic representation.
- 2 shows a high-pressure compressor 17 of a core engine 18 with a shaft 19 of the high-pressure compressor 17.
- a generator 21 which is derived from the mechanical Power electrical energy generated.
- compressed air is removed from the high-pressure compressor 17 via a controllable valve 22.
- the compressed air is fed to an air turbine 23, the air turbine 23 generating mechanical energy from the pneumatic power contained in the compressed air and driving a corresponding shaft 24.
- the shaft 24 is connected to a second generator 26 via a second gear 25.
- the second generator 26 ultimately converts the pneumatic energy or power contained in the compressed air after conversion thereof by the air turbine 23 into mechanical energy into electrical energy.
- 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
- the generator 21 is accordingly driven via the gear 20 by the shaft 19 of the high-pressure compressor 17, and the generator 26 is operated via the gear 20 by the air turbine 23, to which the extracted, compressed air is fed.
- control means 29 are designed as an energy control unit (ECU).
- ECU energy control unit
- the valve 22, the clutch 27 and the two generators 21 and 26 can be controlled via the control means 29, as indicated by the arrows 30 in FIG. 2.
- the switchover between the two operating states for generating the electrical energy takes place either on the basis of criteria stored in the control sections 29 or on the basis of measured values 31 which are supplied to the control means 29.
- the measured values 31 can be e.g. B. the measured compression ratio ⁇ , measured speeds n or measured temperatures T.
- criteria 29 can then be calculated in the control means, on the basis of which the switchover between the two operating states or the connection or disconnection of the air turbine 23 for generating electrical energy with the extraction of compressed air from the main compressor 17 takes place.
- 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)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04819575A EP1697623A1 (de) | 2003-11-29 | 2004-11-05 | Gasturbine, insbesondere flugtriebwerk, und verfahren zur erzeugung elektrischer energie bei einer gasturbine |
US10/580,743 US7584600B2 (en) | 2003-11-29 | 2004-11-05 | Gas turbine, in particular aircraft engine and method for generating electrical energy in a gas turbine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10355917.5 | 2003-11-29 | ||
DE10355917A DE10355917A1 (de) | 2003-11-29 | 2003-11-29 | Gasturbine, insbesondere Flugtriebwerk, und Verfahren zur Erzeugung elektrischer Energie bei einer Gasturbine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005054645A1 true WO2005054645A1 (de) | 2005-06-16 |
Family
ID=34625408
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/DE2004/002444 WO2005054645A1 (de) | 2003-11-29 | 2004-11-05 | Gasturbine, insbesondere flugtriebwerk, und verfahren zur erzeugung elektrischer energie bei einer gasturbine |
Country Status (4)
Country | Link |
---|---|
US (1) | US7584600B2 (de) |
EP (1) | EP1697623A1 (de) |
DE (1) | DE10355917A1 (de) |
WO (1) | WO2005054645A1 (de) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1614880A1 (de) * | 2004-07-09 | 2006-01-11 | Rolls-Royce Plc | Gasturbinentriebwerk |
US7854582B2 (en) | 2007-05-08 | 2010-12-21 | Pratt & Whitney Canada Corp. | Operation of an aircraft engine after emergency shutdown |
US7926287B2 (en) | 2007-05-08 | 2011-04-19 | Pratt & Whitney Canada Corp. | Method of operating a gas turbine engine |
WO2011073664A3 (en) * | 2009-12-17 | 2012-04-12 | Richard Julius Gozdawa | A gas turbine generator |
US8169100B2 (en) | 2008-01-30 | 2012-05-01 | Pratt & Whitney Canada Corp. | Torque transmission for an aircraft engine |
US8519555B2 (en) | 2010-11-29 | 2013-08-27 | Pratt & Whitney Canada Corp. | Combination low spool generator and ram air turbine generator |
FR3041052A1 (fr) * | 2015-09-14 | 2017-03-17 | Hispano-Suiza | Boitier d'entrainement d'equipements dans une turbomachine |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
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 |
WO2014137418A2 (en) | 2013-03-07 | 2014-09-12 | Rolls-Royce Corporation | Vehicle recuperator |
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 (de) | 2013-12-23 | 2019-02-27 | Rolls-Royce Corporation | Steuersystem für einen doppelt redundanten Motor/Generator und Motor |
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 |
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 |
GB201808436D0 (en) | 2018-05-23 | 2018-07-11 | Rolls Royce Plc | Gas turbine engine compressor control method |
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 |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3145532A (en) * | 1961-07-27 | 1964-08-25 | Plessey Co Ltd | Gas-turbine operated engine starters |
US3514945A (en) * | 1968-10-04 | 1970-06-02 | Avco Corp | Gas turbine accessory power drive unit |
EP0200178A1 (de) * | 1985-05-02 | 1986-11-05 | Klöckner-Humboldt-Deutz Aktiengesellschaft | Hilfsantriebsanordnung mit Getriebe für ein Gasturbinentriebwerk |
US5143329A (en) * | 1990-06-01 | 1992-09-01 | General Electric Company | Gas turbine engine powered aircraft environmental control system and boundary layer bleed |
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 |
EP1186761A2 (de) * | 2000-09-11 | 2002-03-13 | General Electric Company | Energierückgewinnung aus Verdichterzapfluft bei Gasturbinen |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE567824A (de) * | 1957-05-20 | |||
DE2519152C2 (de) * | 1975-04-30 | 1982-11-25 | Vereinigte Flugtechnische Werke Gmbh, 2800 Bremen | Vorrichtung zum Anlassen von Flugzeugtriebwerken und zum Betreiben von Flugzeughilfsgeräten |
US4864812A (en) * | 1987-11-13 | 1989-09-12 | Sundstrand Corporation | Combined auxiliary and emergency power unit |
US5174109A (en) * | 1990-10-25 | 1992-12-29 | Sundstrand Corporation | Clutch to disconnect loads during turbine start-up |
US5243329A (en) * | 1991-09-13 | 1993-09-07 | Happer Jr Robert L | Smoke alarm for use with an electronic timing device |
DE4131713A1 (de) | 1991-09-24 | 1993-04-08 | Mtu Muenchen Gmbh | Zusatzverdichter fuer fantriebwerke mit hohem bypass-verhaeltnis |
US5285626A (en) * | 1992-03-20 | 1994-02-15 | Woodward Governor Company | Drive for main engine auxiliaries for an aircraft gas turbine engine |
-
2003
- 2003-11-29 DE DE10355917A patent/DE10355917A1/de not_active Withdrawn
-
2004
- 2004-11-05 EP EP04819575A patent/EP1697623A1/de not_active Withdrawn
- 2004-11-05 US US10/580,743 patent/US7584600B2/en not_active Expired - Fee Related
- 2004-11-05 WO PCT/DE2004/002444 patent/WO2005054645A1/de active Application Filing
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3145532A (en) * | 1961-07-27 | 1964-08-25 | Plessey Co Ltd | Gas-turbine operated engine starters |
US3514945A (en) * | 1968-10-04 | 1970-06-02 | Avco Corp | Gas turbine accessory power drive unit |
EP0200178A1 (de) * | 1985-05-02 | 1986-11-05 | Klöckner-Humboldt-Deutz Aktiengesellschaft | Hilfsantriebsanordnung mit Getriebe für ein Gasturbinentriebwerk |
US5143329A (en) * | 1990-06-01 | 1992-09-01 | General Electric Company | Gas turbine engine powered aircraft environmental control system and boundary layer bleed |
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 |
EP1186761A2 (de) * | 2000-09-11 | 2002-03-13 | General Electric Company | Energierückgewinnung aus Verdichterzapfluft bei Gasturbinen |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1614880A1 (de) * | 2004-07-09 | 2006-01-11 | Rolls-Royce Plc | Gasturbinentriebwerk |
US7823391B2 (en) | 2004-07-09 | 2010-11-02 | Rolls-Royce Plc | Turbine engine arrangement |
US7997082B2 (en) | 2004-07-09 | 2011-08-16 | Rolls-Royce Plc | Turbine engine arrangement |
US7854582B2 (en) | 2007-05-08 | 2010-12-21 | Pratt & Whitney Canada Corp. | Operation of an aircraft engine after emergency shutdown |
US7926287B2 (en) | 2007-05-08 | 2011-04-19 | Pratt & Whitney Canada Corp. | Method of operating a gas turbine engine |
US8169100B2 (en) | 2008-01-30 | 2012-05-01 | Pratt & Whitney Canada Corp. | Torque transmission for an aircraft engine |
WO2011073664A3 (en) * | 2009-12-17 | 2012-04-12 | 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 |
FR3041052A1 (fr) * | 2015-09-14 | 2017-03-17 | Hispano-Suiza | Boitier d'entrainement d'equipements dans une turbomachine |
WO2017046505A1 (fr) * | 2015-09-14 | 2017-03-23 | Safran Transmission Systems | Boitier d'entrainement d'equipements dans une turbomachine |
CN108027018A (zh) * | 2015-09-14 | 2018-05-11 | 赛峰传输系统 | 涡轮机中的设备驱动变速箱 |
CN108027018B (zh) * | 2015-09-14 | 2021-05-14 | 赛峰传输系统 | 涡轮机中的设备驱动变速箱 |
US11448134B2 (en) | 2015-09-14 | 2022-09-20 | Safran Transmission Systems | Equipment drive gearbox in a turbomachine |
Also Published As
Publication number | Publication date |
---|---|
US20070089420A1 (en) | 2007-04-26 |
US7584600B2 (en) | 2009-09-08 |
DE10355917A1 (de) | 2005-06-30 |
EP1697623A1 (de) | 2006-09-06 |
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