DE102008062088B4 - Device for energy recovery in aircraft engines during landing approach. - Google Patents
Device for energy recovery in aircraft engines during landing approach. Download PDFInfo
- Publication number
- DE102008062088B4 DE102008062088B4 DE200810062088 DE102008062088A DE102008062088B4 DE 102008062088 B4 DE102008062088 B4 DE 102008062088B4 DE 200810062088 DE200810062088 DE 200810062088 DE 102008062088 A DE102008062088 A DE 102008062088A DE 102008062088 B4 DE102008062088 B4 DE 102008062088B4
- Authority
- DE
- Germany
- Prior art keywords
- energy recovery
- generator
- recovery according
- energy
- landing approach
- 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 - Fee Related
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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
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- 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
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- 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
Abstract
Vorrichtung zur Energie-Rückgewinnung in Flugzeugtriebwerken beim Landeanflug, dadurch gekennzeichnet, dass der Triebwerks-Fan beim Landeanflug unter Vermeidung von Verlusten durch die Verdichterstufe mit einem Stromgenerator verbunden ist, wobei der Generator eine Speichereinrichtung für elektrische Energie lädt, die Kondensatoren hoher Kapazität enthält und wobei die gespeicherte Energie zum Antrieb einer Gegenschub-Anlage Verwendung findet.Apparatus for power recovery in aircraft engines landing approach, characterized in that the engine fan is connected to the landing approach while avoiding losses through the compressor stage with a power generator, the generator loads an electrical energy storage device containing high capacity capacitors and wherein the stored energy is used to drive a counter-thrust system use.
Description
Flugzeuge verbrauchen, bezogen auf die Flugzeit, einen erheblichen Teil ihres Treibstoffs zur Gewinnung der Flughöhe, die dann mit dem Faktor des Gesamtgewichts als potenzielle Energie vorliegt.Aircraft consume a significant portion of their fuel in terms of flight time to obtain altitude, which is then represented by the factor of the total weight as potential energy.
Beim Landeanflug kann ein guter Teil dieser Energie dadurch zurückgewonnen werden, dass im Sinkflug die Kraftstoffzufuhr zu den Antrieben gedrosselt wird. Jedoch ist nicht immer ein gleitender Sinkflug möglich, so z. B. bei in Talkesseln liegenden Flughäfen, oder häufig auf Grund von Verkehrsbehinderungen. Andererseitsmuss in jedem Falle bis kurz vor dem Aufsetzen der Maschine eine Mindestgeschwindigkeit beibehalten werden, um die Flugstabilität zu erhalten.When landing, a good part of this energy can be recovered by throttling the fuel supply to the drives in descent. However, a sliding descent is not always possible, such. B. in airports located in the basins, or often because of traffic delays. On the other hand, a minimum speed must always be maintained until shortly before the machine is set up in order to maintain flight stability.
Bei großen Verkehrsmaschinen ergeben sich dadurch erhebliche Energiemengen, die kurz vor der Landung durch den Luftwiderstand speziell ausgefahrener Landeklappen, und nach dem Aufsetzen durch Bremsung der Räder, sowie durch Reversierung der Triebwerks-Abstahlrichtung und erneutem Energieaufwand für Gegenschub kompensiert werden müssen.In large transport vehicles, this results in considerable amounts of energy that must be compensated shortly before landing by the drag of specially extended flaps, and after touchdown by braking the wheels, as well as by reversing the engine-stinging direction and renewed energy expenditure for counter-thrust.
Aufgabe vorliegender Erfindung ist daher, diese Energiemengen zu verringern, beziehungsweise weitgehend zurückzugewinnen.Object of the present invention is therefore to reduce these amounts of energy, or largely recover.
Dies wird erfindungsgemäß dadurch erreicht, dass die Triebwerks-Fans der Triebwerke zur gezielten Bremsung und Energie-Rückgewinnung eingesetzt werden.This is inventively achieved in that the engine fans of the engines are used for targeted braking and energy recovery.
Beim Landeanflug kann dabei die Wirkung der Landeklappen verringert, gegebenenfalls könnten diese auch weggelassen werden, soweit sie nicht für Stabilisierung des Auftriebs (gegen ”Durchsacken”) benötigt werden und der Landeanflug kann zur verbesserten Energie-Rekuperation steiler angelegt werden – was auch den Anforderungen erhöhter Luftverkehrsdichte entspricht.When approaching the landing flap effect can be reduced, if necessary, these could also be omitted, unless they are needed for stabilization of the buoyancy (against "sagging") and the landing approach can be applied steeper for improved energy recuperation - which also meets the requirements Air traffic density corresponds.
Bei weiter vergrößerten Nebenstromverhältnis kann damit die Bremswirkung der Landeklappen – und teilweise der mechanischen Bremsen und der Schubumkehr – durch die Bremswirkung des Elektro-Generators am Triebwerks-Fan kompensiert werden. Dabei ist es möglich, automatische Steuerungssysteme, die z. B. den Gierwinkel des Flugzeugs minimieren, dazu einzusetzen, den Widerstand der Generatoren und damit die Drehzahlabsenkung der Triebwerks-Fans zugunsten einer sicheren Fluglage nachzuregeln.With further increased bypass ratio so that the braking effect of landing flaps - and partly the mechanical brakes and the thrust reverser - can be compensated by the braking effect of the electric generator on the engine fan. It is possible, automatic control systems z. B. minimizing the yaw angle of the aircraft, to use to adjust the resistance of the generators and thus the speed reduction of the engine fans in favor of a safe attitude.
Dem kommt entgegen, dass moderne Jet-Antriebe ein zunehmend großes Luft-Nebenstromverhältnis und damit Triebwerks-Fans großen Durchmessers aufweisen, weiter dass die Entwicklung der Antriebe zu Geared Jetengines geht, bei denen Triebwerks-Fan- und Verdichter/Turbinenstufe durch ein Untersetzungsgetriebe für den Triebwerks-Fan getrennt sind.This is countered by the fact that modern jet engines have an increasingly large air bypass ratio and thus large diameter engine fans, further that the development of the drives is geared to Jetengines, where engine fan and compressor / turbine stage by a reduction gear for the Engine fan are disconnected.
Dieses Untersetzungsgetriebe ist in der Regel als Planetengetriebe ausgeführt und zwischen der Nabe des Triebwerks-Fans und der Verdichterstufe angeordnet.This reduction gear is usually designed as a planetary gear and arranged between the hub of the engine fan and the compressor stage.
Die Erfindungsgemäße Lösung bezieht sich deshalb darauf, die Abnahme für den Stromgenerator am entkoppelten Triebwerks-Fan vorzunehmen – wie dies bei Getriebeturbinen ohnehin der Fall sein wird, notfalls diesen zur Abnahme zu entkoppeln, oder die Verdichterstufe entweder auszukoppeln, oder durch einen Luft-Nebenschluss in ihrer Bremswirkung zu beschränken.The solution according to the invention therefore refers to undertaking the decrease for the power generator on the decoupled engine fan - as will anyway be the case with transmission turbines, if necessary decoupling this for acceptance, or decoupling the compressor stage either, or by an air shunt in to restrict their braking effect.
Zwar sind schon Vorrichtungen und Verfahren bekannt, die dieses teilweise bewirken können, jedoch keine vollständige Lösung darstellen:
So offenbart
So revealed
Das
Auch hier – wie beim vorgenannten Stand der Technik – ist kein Ansatz für eine Energie-Rückgewinnung oder -Speicherung gegeben.Again, as in the aforementioned prior art, no approach for energy recovery or storage is given.
In einer bevorzugten Ausführung vorliegender Erfindung wird dagegen dem Planetengetriebe ein weiterer Planetensatz vorgesetzt und dessen Abtrieb zur Stromerzeugung verwendet, sowie der Abtrieb des Haupt-Planetensatzes zu Verdichterstufe freigeschaltet. Es ist aber auch möglich, den Generator direkt oder über eine Übersetzung – etwa durch Riemen- oder Kettenantrieb – mit der Achse des Triebwerks-Fans zu verbinden.In a preferred embodiment of the present invention, however, the planetary gear set a further planetary gear set and its output used to generate electricity, and unlocked the output of the main planetary gear set to compressor stage. But it is also possible to connect the generator directly or via a translation - such as belt or chain drive - with the axis of the engine fans.
In einer bevorzugten Ausführung des Generators sind magnetische Elemente auf einer Scheibe integriert, die, mit dem sekundären Planetenabtrieb verbunden, vor dem Planetengetriebe auf der Triebwerks-Fanachse frei rotiert. Ihr gegenüber sind Spulen auf eine fixierte Statorscheibe oder dem Getriebegehäuse montiert – ähnliche Anordnungen finden sich z. B. als integrierte Anlasser-Generatoren für Kraftfahrzeuge mit Start-Stop-Einrichtungen.In a preferred embodiment of the generator, magnetic elements are integrated on a disc which, connected to the secondary planetary output, freely rotates in front of the planetary gear on the fan fan axis. Their opposite coils are mounted on a fixed stator or the gear housing - similar arrangements can be found for. As integrated starter generators for motor vehicles with start-stop facilities.
Es sind aber auch Ausführungen mit anderen Anordnungen von Rotor und Stator möglich. Eine Anordnung im Mantelstrom, möglichst unmittelbar hinter dem Triebwerks-Fan und entfernt von den Brennkammern des Triebwerks, ist dabei jedoch hinsichtlich der gegen hohe Umgebungstemperaturen empfindlichen Permanentmagnete vorzuziehen.But there are also possible designs with other arrangements of rotor and stator. An arrangement in the sheath current, preferably immediately behind the engine fan and away from the combustion chambers of the engine, however, is preferable in terms of sensitive to high ambient temperature permanent magnets.
Der Generatorteil ist vorzugsweise elektrisch umsteuerbar, um auch als Anlasser nutzbar zu sein – was den Aufwand für diesen Teil der Einrichtung weit gehend kompensiert.The generator part is preferably reversible electrically to be used as a starter - which largely compensates for the expense of this part of the device.
Erfindungsgemäß wird die vor dem Touch-Down rekuperierte Bremsenergie zwischengespeichert, so dass sie nach dem Touch-Down zur Erzeugung von Gegendruck mit dem Triebwerks-Fan eingesetzt wird. Es kann so – je nach Auslegeng – eine ausreichende Schubumkehr erfolgen, ohne dazu die Turbinen erneut hochzufahren. Auf die aufwendigen Einrichtungen für die Schubumkehr könnte dann verzichtet werden. Die Energie dazu wird aus Gewichtsgründen, weil sie nur kurzfristig gespeichert werden muss und kurzzeitig eine hohe Energie-Auskopplung erforderlich ist, erfindungsgemäß in Kondensatoren hoher Kapazität (sog. ”Supercpas”) gespeichert.According to the invention, the recuperated before the touch-down braking energy is cached so that it is used after the touch-down to generate back pressure with the engine fan. Depending on the layout, sufficient thrust reversal can be achieved without restarting the turbines. The elaborate mechanisms for the thrust reverser could then be dispensed with. For reasons of weight, because of the fact that it only needs to be stored for a short time and that a high energy output is required for a short time, the energy for this purpose is stored according to the invention in capacitors of high capacity (so-called "supercpas").
Ferner ist es möglich, die zurückgewonnene Energie anderweitig nutzbringend zu speichern – z. B. in Lithium-Ionen-Batterien um den Betrieb von APUs während der Standzeit des Flugzeugs mit ihrem ungünstigem Wirkungsgrad und Energieverbrauch, sowie ihre Umweltbelastung durch Lärm und Abgase zu vermeiden.Furthermore, it is possible to otherwise profitably store the recovered energy - e.g. As in lithium-ion batteries to the operation of APUs during the life of the aircraft with its unfavorable efficiency and energy consumption, and to avoid their environmental impact of noise and emissions.
Eine nahe liegende Ausführung der Erfindung wird nachfolgend anhand der Zeichnung
Dem Planetengetriebe
Claims (13)
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200810062088 DE102008062088B4 (en) | 2008-12-12 | 2008-12-12 | Device for energy recovery in aircraft engines during landing approach. |
PCT/IB2009/007664 WO2010067172A2 (en) | 2008-12-12 | 2009-12-07 | Apparatus and method for energy recovery on jet-powered airplanes on approach for landing |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200810062088 DE102008062088B4 (en) | 2008-12-12 | 2008-12-12 | Device for energy recovery in aircraft engines during landing approach. |
Publications (2)
Publication Number | Publication Date |
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DE102008062088A1 DE102008062088A1 (en) | 2010-06-24 |
DE102008062088B4 true DE102008062088B4 (en) | 2015-03-05 |
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ID=42194009
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE200810062088 Expired - Fee Related DE102008062088B4 (en) | 2008-12-12 | 2008-12-12 | Device for energy recovery in aircraft engines during landing approach. |
Country Status (2)
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DE (1) | DE102008062088B4 (en) |
WO (1) | WO2010067172A2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102018203423A1 (en) * | 2018-03-07 | 2019-09-12 | Rolls-Royce Deutschland Ltd & Co Kg | Shaft assembly and aircraft engine with a shaft assembly |
Families Citing this family (17)
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DE102013209388B4 (en) * | 2013-05-22 | 2021-07-22 | Robert Bosch Gmbh | Hybrid propulsion for power-powered aircraft, power-powered aircraft with hybrid drive and associated operating method |
US9915164B2 (en) | 2014-05-20 | 2018-03-13 | United Technologies Corporation | Geared turbofan with high speed generator |
US9982606B2 (en) | 2014-10-01 | 2018-05-29 | Goodrich Corporation | Electric architecture with power storage cells |
FR3037038A1 (en) * | 2015-06-08 | 2016-12-09 | Andre Chaneac | TURBO REACTOR DRIVING A BLOWER AND A GENERATOR, ITS MOUNTING ON A VERTICAL LANDING AEROFEF AND LANDFILLING |
CN106560605B (en) * | 2015-10-06 | 2019-04-19 | 熵零股份有限公司 | Planetary mechanism propfan engine |
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 |
DE102016207517A1 (en) | 2016-05-02 | 2017-11-02 | Siemens Aktiengesellschaft | Propulsion system for aircraft with electric generator |
GB201706361D0 (en) * | 2017-04-21 | 2017-06-07 | Rolls Royce Plc | An auxiliary rotation device for a gas turbine engine and a method of cooling a rotor of a gas turbine engine using an auxiliary rotation device |
DE202017103131U1 (en) * | 2017-05-23 | 2018-08-24 | ENGIRO GmbH | Aircraft with at least one range extender |
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 |
EP3444495A1 (en) | 2017-08-18 | 2019-02-20 | Rolls-Royce Deutschland Ltd & Co KG | Mechanical clutch device and method for operating a mechanical clutch device |
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 |
FR3077804B1 (en) * | 2018-02-09 | 2022-03-18 | Safran | HYBRID PROPULSION FOR AN AIRCRAFT |
US10378452B1 (en) * | 2018-02-26 | 2019-08-13 | The Boeing Company | Hybrid turbine jet engines and methods of operating the same |
EP3633160B1 (en) | 2018-10-01 | 2022-11-02 | Rolls-Royce plc | Gas turbine engine with integrated energy storage device |
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 |
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US6148605A (en) * | 1998-03-05 | 2000-11-21 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Method and device for reversing the thrust of very high bypass ratio turbojet engines |
US20060137355A1 (en) * | 2004-12-27 | 2006-06-29 | Pratt & Whitney Canada Corp. | Fan driven emergency generator |
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DE102006039608A1 (en) * | 2006-08-24 | 2008-04-10 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement for energy extraction in a two-shaft engine |
US20080200299A1 (en) * | 2007-02-16 | 2008-08-21 | David Everett Russ | Multi-speed gearbox for low spool driven auxiliary component |
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US6895741B2 (en) * | 2003-06-23 | 2005-05-24 | Pratt & Whitney Canada Corp. | Differential geared turbine engine with torque modulation capability |
WO2008082335A1 (en) * | 2006-12-29 | 2008-07-10 | Volvo Aero Corporation | A power transmission device for a gas turbine engine |
US7926287B2 (en) * | 2007-05-08 | 2011-04-19 | Pratt & Whitney Canada Corp. | Method of operating a gas turbine engine |
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2008
- 2008-12-12 DE DE200810062088 patent/DE102008062088B4/en not_active Expired - Fee Related
-
2009
- 2009-12-07 WO PCT/IB2009/007664 patent/WO2010067172A2/en active Application Filing
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US6148605A (en) * | 1998-03-05 | 2000-11-21 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Method and device for reversing the thrust of very high bypass ratio turbojet engines |
US20060137355A1 (en) * | 2004-12-27 | 2006-06-29 | Pratt & Whitney Canada Corp. | Fan driven emergency generator |
US20070101721A1 (en) * | 2005-11-09 | 2007-05-10 | Pratt & Whitney Canada Corp. | Method and system for taxiing an aircraft |
DE102006039608A1 (en) * | 2006-08-24 | 2008-04-10 | Rolls-Royce Deutschland Ltd & Co Kg | Arrangement for energy extraction in a two-shaft engine |
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DE102018203423A1 (en) * | 2018-03-07 | 2019-09-12 | Rolls-Royce Deutschland Ltd & Co Kg | Shaft assembly and aircraft engine with a shaft assembly |
Also Published As
Publication number | Publication date |
---|---|
WO2010067172A3 (en) | 2011-01-13 |
WO2010067172A2 (en) | 2010-06-17 |
DE102008062088A1 (en) | 2010-06-24 |
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