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WO2010067172A2 - Appareil et procede de recuperation d'energie sur des aeronefs a reaction en approche d'atterrissage - Google Patents

Appareil et procede de recuperation d'energie sur des aeronefs a reaction en approche d'atterrissage Download PDF

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Publication number
WO2010067172A2
WO2010067172A2 PCT/IB2009/007664 IB2009007664W WO2010067172A2 WO 2010067172 A2 WO2010067172 A2 WO 2010067172A2 IB 2009007664 W IB2009007664 W IB 2009007664W WO 2010067172 A2 WO2010067172 A2 WO 2010067172A2
Authority
WO
WIPO (PCT)
Prior art keywords
generator
fan
gearbox
airplanes
landing
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.)
Ceased
Application number
PCT/IB2009/007664
Other languages
English (en)
Other versions
WO2010067172A3 (fr
Inventor
Norbert Bayer
Christian Schmitt
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of WO2010067172A2 publication Critical patent/WO2010067172A2/fr
Publication of WO2010067172A3 publication Critical patent/WO2010067172A3/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
    • 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
    • F02C6/14—Gas-turbine plants having means for storing energy, e.g. for meeting peak loads
    • 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
    • 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
    • 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
    • F05D2220/50—Application for auxiliary power units (APU's)
    • 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
    • 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
    • F05D2260/85—Starting

Definitions

  • the fan is uncoupled from the compression and turbine section applying a secondary planetary gear set, and therewith connected to the starter/generator unit to produce power, that might be stored in capacitors or batteries for re-use.
  • the invention relates to energy recovery on airplanes with modern turbojet engines and more precisely to the recovery of energy potentials that otherwise need to be braked off in landing flaps, wheelbrakes. and by counterthrust.
  • Airplanes use a substantial part of their fuel consumption for climbing onto their cruising altitude, which is then transformed into potential energy as to height and and total weight as factors.
  • the angle of descent can be made steeper, so to save time and to allow higher air traffic density.
  • This system does as well enable the application of automatic controls, like those to reduce the yawing angle on flight, whilst controlling the mechanical resistance of the generator and fan set, so to ensure safe gliding unto touchdown.
  • the planetary gearbox is equipped with another planetary gear set, the drive side of witch is coupled to the generator, whereas the main drive is uncoupled from the compression section.
  • the generator by means of chain- or belt drives to the fan axle.
  • the generator contains permanent magnetic elements, that are embedded into a disc, which is coupled to the planetary drive and may rotate independently close to a coiled stator disc or cup on the gearbox' housing.
  • Similar constructions are well known in the art as combinations of starter/generators in street vehicles with autostop/start arrangements. 40
  • other arrangements of rotor and stator are well known in the art and alternatively applicable, but in all cases an arrangement closely behind the fan and largely away from compressor and combustion chamber is mandatory to prevent the permanent magnets from overheating an thus deterioration.
  • the generator preferably is reversible, so to be used as starter motor - as well known in the art. This reduces a good deal of cost to be omitted to this section.
  • Recuperated energy at descent can be applied to counterthrust after touch down, simply by counter-rotating the uncoupled fan, this way avoiding to re-activate the turbines for the sake of wasting fuel, but even more to avoid critical noise emissions.
  • recuperated energy is as well possible for energizing airplanes during their stay on ground, what otherwise APUs are applied for - thus not only saving Energy, but particularly the disgusting noise and exhaust gases of these units.
  • some part of the energy may rather be stored in Lihtium-Ion batteries, due to their lower self-discharge. 6
  • FIG. 1 One preferred embodiment of the heredisclosed invention is illustrated by Fig. 1 :
  • Fig 1 defines the cross-section of a sheath current turbofan engine 1 , containing a planetary gearbox 2 between fan 3, compression unit 4 and combustion chamber 5 before the turbine section 6.
  • the planetary gearbox 2 is equipped with a secondary planetary gearset 7, that is fixed to the rotor 8 of the generator 9, that turns freely on the bearing 10 around the fax axle 11. Frontal to rotor 8 of the generator 9 the stator is integrated into the housing of the gearbox 13.
  • the rotor 8 preferably is equipped with permanent magnetsl4, 15, whereas the stator 12 carries the inductive coils 16 and 17 (but construction could as well be done vice- versa).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Retarders (AREA)

Abstract

L'invention concerne la récupération de potentiels énergétiques d'aéronefs dotés de moteurs modernes à double flux en approche d'atterrissage, la soufflante est découplée de la section compression et turbine par application d'un train planétaire secondaire, et connectée à l'unité démarreur/générateur pour produire de la puissance susceptible d'être stockée dans des condensateurs ou des batteries en vue de sa réutilisation.
PCT/IB2009/007664 2008-12-12 2009-12-07 Appareil et procede de recuperation d'energie sur des aeronefs a reaction en approche d'atterrissage Ceased WO2010067172A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE1020080620882-13 2008-12-12
DE200810062088 DE102008062088B4 (de) 2008-12-12 2008-12-12 Vorrichtung zur Energie-Rückgewinnung in Flugzeugtriebwerken beim Landeanflug.

Publications (2)

Publication Number Publication Date
WO2010067172A2 true WO2010067172A2 (fr) 2010-06-17
WO2010067172A3 WO2010067172A3 (fr) 2011-01-13

Family

ID=42194009

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2009/007664 Ceased WO2010067172A2 (fr) 2008-12-12 2009-12-07 Appareil et procede de recuperation d'energie sur des aeronefs a reaction en approche d'atterrissage

Country Status (2)

Country Link
DE (1) DE102008062088B4 (fr)
WO (1) WO2010067172A2 (fr)

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013209388A1 (de) * 2013-05-22 2014-11-27 Robert Bosch Gmbh Hybridantrieb für kraftgetriebenes Luftfahrzeug, kraftgetriebenes Luftfahrzeug mit Hybridantrieb und zugehöriges Betriebsverfahren
EP2947278A1 (fr) * 2014-05-20 2015-11-25 United Technologies Corporation Turboréacteur à engrenages avec générateur à grande vitesse
GB2531429A (en) * 2014-10-01 2016-04-20 Goodrich Corp Electric architecture with power storage cells
FR3037038A1 (fr) * 2015-06-08 2016-12-09 Andre Chaneac Turbo reacteur entrainant une soufflante et une generatrice, son montage sur un aerofef a decollage et atterrissage vertical
CN106560605A (zh) * 2015-10-06 2017-04-12 熵零股份有限公司 行星机构桨扇发动机
EP3190052A1 (fr) * 2016-01-05 2017-07-12 The Boeing Company Moteur d'aéronef et procédé associé d'entraînement du ventilateur avec arbre basse pression pendant les opérations de circulation au sol
DE102016207517A1 (de) * 2016-05-02 2017-11-02 Siemens Aktiengesellschaft Antriebssystem für Luftfahrzeug mit elektrischem Generator
DE202017103131U1 (de) * 2017-05-23 2018-08-24 ENGIRO GmbH Luftfahrzeug mit mindestens einem Range-Extender
EP3392465A3 (fr) * 2017-04-21 2018-11-14 Rolls-Royce plc Dispositif de rotation auxiliaire pour moteur à turbine à gaz et procédé de refroidissement d'un rotor d'un moteur à turbine à gaz au moyen d'un dispositif de rotation auxiliaire
WO2019155173A1 (fr) 2018-02-09 2019-08-15 Safran Propulsion hybride pour un aéronef
EP3530928A1 (fr) * 2018-02-26 2019-08-28 The Boeing Company Moteurs à réaction à turbine hybrides et procédés de fonctionnement correspondant
US10760498B2 (en) * 2018-01-04 2020-09-01 General Electric Company System and method for removing rotor bow in a gas turbine engine using mechanical energy storage device
US11073109B2 (en) 2018-10-01 2021-07-27 Rolls-Royce Plc Gas turbine engine
CN113437742A (zh) * 2021-07-20 2021-09-24 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种用于混合动力航空器的供电方法、系统
US20210396148A1 (en) * 2020-06-22 2021-12-23 Florida Turbine Technologies, Inc. Multi-spool geared turbofan arrangement with integrated starter/generator
US11884172B2 (en) 2020-07-30 2024-01-30 Hamilton Sundstrand Corporation Battery charging for hybrid electric powerplants
US12092214B1 (en) 2023-05-12 2024-09-17 Pratt & Whitney Canada Corp. Adjustable mounting assembly for tension member driven device

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3444495A1 (fr) 2017-08-18 2019-02-20 Rolls-Royce Deutschland Ltd & Co KG Dispositif d'embrayage mécanique et procédé de fonctionnement d'un dispositif d'embrayage mécanique
US10954813B2 (en) 2017-08-18 2021-03-23 Rolls-Royce Deutschland Ltd & Co Kg Planetary gearbox system and method for operating a planetary gearbox system
DE102018203423A1 (de) * 2018-03-07 2019-09-12 Rolls-Royce Deutschland Ltd & Co Kg Wellenanordnung und Flugzeugtriebwerk mit einer Wellenanordnung

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2775734B1 (fr) * 1998-03-05 2000-04-07 Snecma Procede et dispositif d'inversion de poussee pour moteur a tres grand taux de dilution
US6895741B2 (en) * 2003-06-23 2005-05-24 Pratt & Whitney Canada Corp. Differential geared turbine engine with torque modulation capability
US20060137355A1 (en) * 2004-12-27 2006-06-29 Pratt & Whitney Canada Corp. Fan driven emergency generator
US7802757B2 (en) * 2005-11-09 2010-09-28 Pratt & Whitney Canada Corp. Method and system for taxiing an aircraft
DE102006039608A1 (de) * 2006-08-24 2008-04-10 Rolls-Royce Deutschland Ltd & Co Kg Anordnung zur Energieentnahme bei einem Zwei-Wellen-Triebwerk
WO2008082335A1 (fr) * 2006-12-29 2008-07-10 Volvo Aero Corporation Dispositif de transmission de puissance pour une turbine à gaz
US7942079B2 (en) * 2007-02-16 2011-05-17 Hamilton Sundstrand Corporation Multi-speed gearbox for low spool driven auxiliary component
US7926287B2 (en) * 2007-05-08 2011-04-19 Pratt & Whitney Canada Corp. Method of operating a gas turbine engine

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013209388B4 (de) 2013-05-22 2021-07-22 Robert Bosch Gmbh Hybridantrieb für kraftgetriebenes Luftfahrzeug, kraftgetriebenes Luftfahrzeug mit Hybridantrieb und zugehöriges Betriebsverfahren
DE102013209388A1 (de) * 2013-05-22 2014-11-27 Robert Bosch Gmbh Hybridantrieb für kraftgetriebenes Luftfahrzeug, kraftgetriebenes Luftfahrzeug mit Hybridantrieb und zugehöriges Betriebsverfahren
US9915164B2 (en) 2014-05-20 2018-03-13 United Technologies Corporation Geared turbofan with high speed generator
EP2947278A1 (fr) * 2014-05-20 2015-11-25 United Technologies Corporation Turboréacteur à engrenages avec générateur à grande vitesse
US11236632B2 (en) 2014-05-20 2022-02-01 Raytheon Technologies Corporation Geared turbofan with high speed generator
GB2531429A (en) * 2014-10-01 2016-04-20 Goodrich Corp Electric architecture with power storage cells
GB2531429B (en) * 2014-10-01 2017-02-08 Goodrich Corp Electric architecture with power storage cells
US9982606B2 (en) 2014-10-01 2018-05-29 Goodrich Corporation Electric architecture with power storage cells
FR3037038A1 (fr) * 2015-06-08 2016-12-09 Andre Chaneac Turbo reacteur entrainant une soufflante et une generatrice, son montage sur un aerofef a decollage et atterrissage vertical
CN106560605A (zh) * 2015-10-06 2017-04-12 熵零股份有限公司 行星机构桨扇发动机
JP2017122452A (ja) * 2016-01-05 2017-07-13 ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ タキシング中にファンを低圧シャフトで駆動するための航空エンジン及びそれに関連する方法
US10336461B2 (en) 2016-01-05 2019-07-02 The Boeing Company Aircraft engine and associated method for driving the fan with the low pressure shaft during taxi operations
AU2016256682B2 (en) * 2016-01-05 2021-07-01 The Boeing Company Aircraft engine and associated method for driving the fan with the low pressure shaft during taxi operations
EP3190052A1 (fr) * 2016-01-05 2017-07-12 The Boeing Company Moteur d'aéronef et procédé associé d'entraînement du ventilateur avec arbre basse pression pendant les opérations de circulation au sol
JP7025117B2 (ja) 2016-01-05 2022-02-24 ザ・ボーイング・カンパニー タキシング中にファンを低圧シャフトで駆動するための航空エンジン及びそれに関連する方法
DE102016207517A1 (de) * 2016-05-02 2017-11-02 Siemens Aktiengesellschaft Antriebssystem für Luftfahrzeug mit elektrischem Generator
US11092031B2 (en) 2016-05-02 2021-08-17 Rolls-Royce Deutschland Ltd & Co Kg Drive system for an aircraft
EP3392465A3 (fr) * 2017-04-21 2018-11-14 Rolls-Royce plc Dispositif de rotation auxiliaire pour moteur à turbine à gaz et procédé de refroidissement d'un rotor d'un moteur à turbine à gaz au moyen d'un dispositif de rotation auxiliaire
DE202017103131U1 (de) * 2017-05-23 2018-08-24 ENGIRO GmbH Luftfahrzeug mit mindestens einem Range-Extender
US10760498B2 (en) * 2018-01-04 2020-09-01 General Electric Company System and method for removing rotor bow in a gas turbine engine using mechanical energy storage device
WO2019155173A1 (fr) 2018-02-09 2019-08-15 Safran Propulsion hybride pour un aéronef
FR3077804A1 (fr) * 2018-02-09 2019-08-16 Safran Propulsion hybride pour un aeronef
US11608188B2 (en) 2018-02-09 2023-03-21 Safran Hybrid propulsion for an aircraft
EP3530928A1 (fr) * 2018-02-26 2019-08-28 The Boeing Company Moteurs à réaction à turbine hybrides et procédés de fonctionnement correspondant
CN110195656B (zh) * 2018-02-26 2023-02-21 波音公司 混合涡轮喷气发动机及操作其的方法
CN110195656A (zh) * 2018-02-26 2019-09-03 波音公司 混合涡轮喷气发动机及操作其的方法
US11073109B2 (en) 2018-10-01 2021-07-27 Rolls-Royce Plc Gas turbine engine
US20210396148A1 (en) * 2020-06-22 2021-12-23 Florida Turbine Technologies, Inc. Multi-spool geared turbofan arrangement with integrated starter/generator
WO2021260531A1 (fr) * 2020-06-22 2021-12-30 Florida Turbine Technologies, Inc. Agencement de réacteur à réducteur multibobine avec démarreur/générateur intégré
US11286805B2 (en) 2020-06-22 2022-03-29 Florida Turbine Technologies, Inc. Multi-spool geared turbofan arrangement with integrated starter/generator
US11884172B2 (en) 2020-07-30 2024-01-30 Hamilton Sundstrand Corporation Battery charging for hybrid electric powerplants
CN113437742A (zh) * 2021-07-20 2021-09-24 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种用于混合动力航空器的供电方法、系统
US12092214B1 (en) 2023-05-12 2024-09-17 Pratt & Whitney Canada Corp. Adjustable mounting assembly for tension member driven device

Also Published As

Publication number Publication date
DE102008062088A1 (de) 2010-06-24
WO2010067172A3 (fr) 2011-01-13
DE102008062088B4 (de) 2015-03-05

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