EP3280644A1 - Propeller drive and a vehicle, particularly an aircraft - Google Patents

Propeller drive and a vehicle, particularly an aircraft

Info

Publication number
EP3280644A1
EP3280644A1 EP16739484.0A EP16739484A EP3280644A1 EP 3280644 A1 EP3280644 A1 EP 3280644A1 EP 16739484 A EP16739484 A EP 16739484A EP 3280644 A1 EP3280644 A1 EP 3280644A1
Authority
EP
European Patent Office
Prior art keywords
propeller
drive
machine
electric
aircraft
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Withdrawn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
EP16739484.0A
Other languages
German (de)
French (fr)
Inventor
Christian Bachmann
Dominik Bergmann
Georg Bachmaier
Matthias Gerlich
Guillaume Pais
Iason Vittorias
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Publication of EP3280644A1 publication Critical patent/EP3280644A1/en
Withdrawn legal-status Critical Current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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L50/00—Electric propulsion with power supplied within the vehicle
    • B60L50/10—Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines
    • B60L50/15—Electric propulsion with power supplied within the vehicle using propulsion power supplied by engine-driven generators, e.g. generators driven by combustion engines with additional electric power supply
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L7/00—Electrodynamic brake systems for vehicles in general
    • B60L7/10—Dynamic electric regenerative braking
    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/90—Cooling
    • B64U20/98—Cooling using liquid, e.g. using lubrication oil
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/33—Supply or distribution of electrical power generated by combustion engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2200/00—Type of vehicles
    • B60L2200/10—Air crafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2210/00—Converter types
    • B60L2210/30—AC to DC converters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2210/00—Converter types
    • B60L2210/40—DC to AC converters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2220/00—Electrical machine types; Structures or applications thereof
    • B60L2220/10—Electrical machine types
    • B60L2220/14—Synchronous machines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2240/00—Control parameters of input or output; Target parameters
    • B60L2240/40—Drive Train control parameters
    • B60L2240/44—Drive Train control parameters related to combustion engines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/30—Blade pitch-changing mechanisms
    • 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
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
    • Y02T10/7072—Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
    • 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
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
    • Y02T10/72—Electric energy management in electromobility
    • 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
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • Propeller drive and vehicle in particular aircraft
  • the invention relates to a propeller drive and a vehicle, in particular an aircraft.
  • serial hybrid concepts that is to say a drive motor, in particular an internal combustion engine, and an electrical generator for generating electrical energy are accommodated in the fuselage of the light aircraft so that a favorable mass distribution and aerodynamics can be achieved.
  • the conversion of electrical energy into kinetic energy of the propeller is achieved by compact, aerodynamically favorable electric motors.
  • the propeller drive according to the invention is in particular a vehicle drive, expediently an aircraft drive.
  • the Propel Drive according to the invention comprises a propeller machine and an electric drive, which is connected converter-free to the propeller machine.
  • the electric drive is connected "inverter-free" to the propeller machine, it is merely meant that exactly the electrical connection of the electric drive to the propeller machine takes place without a detour via an inverter itself must necessarily be formed without any inverter.
  • the electric drive is connected to the propeller machine with alternating current, in particular three-phase electrical alternating current coupled.
  • alternating current in particular three-phase electrical alternating current coupled.
  • About the AC coupling of electric drive and propeller machine can be In particular, feed three-phase current directly into the propeller machine.
  • the electric drive comprises an electrical energy source, in particular with a drive motor, preferably an internal combustion engine, and a power generator connected thereto.
  • a drive motor preferably an internal combustion engine
  • a power generator connected thereto.
  • an electrical energy store in particular by means of an inverter, is connected to the electric drive.
  • energy can be fed into the energy storage, for example, to charge the energy storage during operation - in the case of a propeller drive of an aircraft, for example, during the flight.
  • the energy storage device is connected to the electric drive by means of a converter, then the converter only has to be designed for the differential power, which is maximally provided by the energy storage device. Thus, only this difference power is lossy.
  • capacities of the electric energy storage are so small that they are possibly formed for a few minutes lasting full power extraction.
  • the inverter (s) are / are suitably adapted to these requirements.
  • the inverter may have a very small recooler, or the inverter is designed so that the heat capacity of a cooling medium is sufficient to not exceed an upper limit temperature during these few minutes of full load operation. It can therefore be taken into account that full-load operation is not permanently provided.
  • the electric drive and the propeller machine and / or the electric drive and the energy storage unit are each bar, in particular by means of three-phase switches, which are preferably designed as contactors, connected to each other.
  • electrical energy storage and / or electric drive and / or propeller machine can be decoupled from other parts of the propeller drive.
  • faulty components of the propeller drive can be separated, which otherwise disturb the other propeller drive or put out of service.
  • further operating states can be achieved flexibly, in particular the charging of the electrical energy store, if no drive torque is applied to the propeller.
  • the propeller engine at least one propeller with controllable Blattanstellwinkel and / or at least one separate speed control and / or speed control for controlling and / or regulating the speed of the at least one propeller. If a propeller machine with controllable blade pitch and / or separate speed control and / or regulation provided, the speed of the propeller can be kept in a very narrow range. In this way, during flight operation, the propeller speed can be kept in a fixed relationship with the rotational speed of a drive motor of the electric drive, so that a direct coupling of drive motor speed and propeller speed can take place.
  • the propeller machine on the one hand and the electric drive on the other hand have a different number of magnetic pole pairs.
  • the propeller machine has a synchronous machine which is designed in particular such that no tilting point is reached during operation.
  • a limitation of the dynamics of the system is provided, so that too high acceleration torques can occur which would exceed the overturning moment of the electric drive.
  • the synchronous machine is preferably designed without damper winding.
  • the braking torque is proportional to the square of the speed of the propeller of the propeller engine. Additional damping therefore does not necessarily have to be provided.
  • the weight caused by the damper winding can be saved in aircraft propeller drives.
  • the propeller drive according to the invention comprises a cooling circuit, wherein the electric drive and / or the propeller machine and / or the drive motor and / or the electric generator are thermally connected together to the cooling circuit.
  • the cooling water temperature for converters is not a limiting factor, in particular a drive motor and the propeller engine can be connected to the same cooling circuit.
  • the propeller drive according to the invention is designed as a hybrid propeller drive.
  • the vehicle according to the invention is in particular an aircraft and with a propeller drive, as described above.
  • the vehicle according to the invention is a hybrid vehicle. The invention will be explained in more detail with reference to an embodiment shown in the drawing. Show it :
  • Figure 1 is a known aircraft with the state of
  • Figure 2 shows an inventive aircraft with a propeller drive according to the invention schematically in a schematic diagram.
  • the aircraft 10 shown in FIG. 1 has an aircraft drive in the form of a propeller drive 20.
  • the structure of this propeller drive 20 is known per se and belongs to the prior art.
  • the propeller drive 20 initially comprises a combustion engine 30, which burns fuel, in the case illustrated aviation gasoline, for the purpose of obtaining kinetic energy.
  • the internal combustion engine 30 provides this kinetic energy in the form of rotational energy by means of a rotating shaft 40.
  • the rotating shaft 40 is connected to an electric generator 50, which converts the kinetic energy by means of electromagnetic induction into electrical energy.
  • the electric generator 50 provides the electrical energy in the form of three-phase current of corresponding power. This three-phase current feeds an electrical converter 70 via a three-phase line connection 60, which converts the three-phase current into a DC intermediate circuit 80.
  • a converter 90 is connected to this DC voltage intermediate circuit 80 and supplies from the DC current of the DC voltage circuit 80 a three-phase current suitable for driving an electric machine 100, which converts the three-phase current into kinetic energy of a rotating propeller 110.
  • two converters 90 each are provided on the drive side of the DC intermediate circuit 80, each of which feeds an electric machine 100 for driving a respective propeller 110.
  • a high-voltage battery 130 is furthermore provided in the example shown in FIG. 1, which is connected to the DC intermediate circuit 80 by means of a direct current connection.
  • the aircraft 10 'according to the invention shown in FIG. 2 has an aircraft drive in the form of a propeller drive 20' according to the invention.
  • the propeller drive 20 'shown in FIG. 2 also has an internal combustion engine 30, which burns fuel in the form of aircraft fuel and provides kinetic energy as rotational energy by means of a rotating shaft 40.
  • the rotating shaft 40 is connected to an electric generator 50, which converts the kinetic energy by means of electromagnetic induction into electrical energy.
  • the electric generator 50 provides the electrical energy in the form of three-phase current of corresponding power.
  • the electric generator 50 according to FIG. 2 is not connected to the electric machine 100 via two converters 70, 90 and an intermediate DC voltage intermediate circuit 80, but the electric generator 50 feeds the electric machine 100 by means of a three-phase line connection 60 directly, that means inverter-free. Consequently, the three-phase current generated in the electric generator 50 is fed directly into the electric machine 100, so that the three-phase current of the electric generator 50 can be directly converted into rotary motion of the propeller 110 by means of the electric machines 100.
  • the propeller drive 20 has two electric machines 100 connected in parallel to the three-phase line connection 60 in the form of synchronous machines, each with a propeller 110 connected thereto.
  • a different number of electric machines 100 may be provided with each connected thereto propellers 110.
  • the electric machines 100 are formed damper winding free, ie, a damper winding or a damper cage are not present.
  • a high-voltage battery 130 is also present in the exemplary embodiment shown in FIG. 2, which is connected by means of an inverter 70 to the three-phase line connection 60 which connects the electrical generator 50 and the electrical machines 100 to one another.
  • the inverter 70 directs the three-phase current into a DC circuit 120 for charging the high-voltage battery 130.
  • the high-voltage battery 130 can be decoupled from the remaining propeller drive 20 'when the high-voltage battery 130 is not required for the operation of the propeller drive 20'.
  • the high-voltage battery 130 is connected to the rest of the propeller drive 20 'only when energy is to be supplied from the high-voltage battery 130 or into the high-voltage battery 130.
  • the drive motor 30 together with the shaft 40 and the electric generator 50 can be decoupled from the remaining propeller drive 20 '.
  • the electric machines 100 together with the connected propellers 110 can be decoupled from the remaining propeller drive 20 '.
  • defective parts of the propeller drive 20 ' may also be decoupled by means of the electrical switches 140.
  • the electrical switches 140 are designed as mechanical switches for high powers, namely as contactors in the form of three-phase switches. In principle, the electrical switches 140 can be realized in other, not specifically illustrated embodiments.
  • a common cooling circuit 150 for cooling the internal combustion engine 30 and the electric generator 50 is also provided.
  • the cooling circuit 150 is a cooling water circuit.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Power Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Transportation (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Oil, Petroleum & Natural Gas (AREA)
  • Remote Sensing (AREA)
  • Control Of Eletrric Generators (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Electric Propulsion And Braking For Vehicles (AREA)

Abstract

The invention relates to a propeller drive (20') which is, in particular, an aircraft drive and comprises a propeller machine (100) as well as an electric drive (30, 50) that is connected without a converter to said propeller machine (100). The aircraft (10') comprises such a propeller drive (20').

Description

Beschreibung description
Propellerantrieb und Fahrzeug, insbesondere Flugzeug Die Erfindung betrifft einen Propellerantrieb sowie ein Fahrzeug, insbesondere ein Flugzeug. Propeller drive and vehicle, in particular aircraft The invention relates to a propeller drive and a vehicle, in particular an aircraft.
Insbesondere für Fahrzeuge in Gestalt von Kleinflugzeugen sind hybridelektrische Antriebe Gegenstand intensiver Ent- wicklung. So ist es etwa bekannt, serielle Hybridkonzepte zu verwenden, das heißt ein Antriebsmotor, insbesondere ein Verbrennungsmotor, sowie ein elektrischer Generator zur Erzeugung von elektrischer Energie sind im Rumpf des Kleinflugzeugs untergebracht, sodass eine günstige Massenverteilung und Aerodynamik erreicht werden kann. Die Wandlung von elektrischer Energie in Bewegungsenergie der Propeller erfolgt durch kompakte, aerodynamisch günstige Elektromotoren. Zwar haben solche seriellen Hybridkonzepte gegenüber Parallelhybridkonzepten einen geringeren Wirkungsgrad, jedoch überwiegen die aerodynamischen und systembedingten Vorteile. In particular, for vehicles in the form of small aircraft, hybrid electric drives are the subject of intensive development. For example, it is known to use serial hybrid concepts, that is to say a drive motor, in particular an internal combustion engine, and an electrical generator for generating electrical energy are accommodated in the fuselage of the light aircraft so that a favorable mass distribution and aerodynamics can be achieved. The conversion of electrical energy into kinetic energy of the propeller is achieved by compact, aerodynamically favorable electric motors. Although such serial hybrid concepts compared to parallel hybrid concepts have a lower efficiency, but outweigh the aerodynamic and systemic benefits.
Vor diesem Hintergrund des Standes der Technik ist es Aufgabe der Erfindung, einen verbesserten Propellerantrieb zu schaffen, welcher eine große Flexibilität aufweist, mit geringem technischen Aufwand herstellbar ist und leicht und kompakt ausbildbar ist. Ferner ist es Aufgabe der Erfindung, ein Fahrzeug, insbesondere ein Flugzeug, mit einem verbesserten Propellerantrieb zu schaffen. Diese Aufgabe wird mit einem Propellerantrieb mit den in Anspruch 1 angegebenen Merkmalen sowie mit einem Fahrzeug mit den in Anspruch 11 angegebenen Merkmalen gelöst. Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den zugehörigen Unteransprüchen, der nachfolgenden Beschreibung und der Zeichnung. Against this background of the prior art, it is an object of the invention to provide an improved propeller drive, which has a high flexibility, can be produced with little technical effort and is lightweight and compact formable. It is another object of the invention to provide a vehicle, in particular an aircraft, with an improved propeller drive. This object is achieved with a propeller drive with the features specified in claim 1 and with a vehicle having the features specified in claim 11. Preferred embodiments of the invention will become apparent from the accompanying dependent claims, the following description and the drawings.
Der erfindungsgemäße Propellerantrieb ist insbesondere ein Fahrzeugantrieb, zweckmäßig ein Flugzeugantrieb. Der Propel- lerantrieb gemäß der Erfindung umfasst eine Propellermaschine sowie einen elektrischen Antrieb, welcher umrichterfrei an die Propellermaschine angebunden ist. Dabei ist unter der Wendung, dass der elektrische Antrieb „umrichterfrei" an die Propellermaschine angebunden ist, lediglich gemeint, dass genau die elektrische Anbindung des elektrischen Antriebs an die Propellermaschine ohne einen Umweg über einen Umrichter erfolgt. Dies bedeutet selbstredend nicht, dass der erfindungsgemäße Propellerantrieb selbst notwendigerweise ohne je- den Umrichter ausgebildet sein muss. The propeller drive according to the invention is in particular a vehicle drive, expediently an aircraft drive. The Propel Drive according to the invention comprises a propeller machine and an electric drive, which is connected converter-free to the propeller machine. By the phrase that the electric drive is connected "inverter-free" to the propeller machine, it is merely meant that exactly the electrical connection of the electric drive to the propeller machine takes place without a detour via an inverter itself must necessarily be formed without any inverter.
Aufgrund dieser Ausbildung des erfindungsgemäße Propellerantriebs lässt sich dieser unter Verzicht auf Umrichter und den mit solchen Umrichtern verbundenen Bauraum sowie das mit Um- richtern einhergehende Gewicht ausbilden. Ferner resultieren Umrichter typischerweise in etwa 2% Verlust, so dass eine umrichterfreie Anbindung des elektrischen Antriebes an die Propellermaschine verlustarm ausbildbar ist. Demgegenüber lässt sich der elektrische Antrieb elektrisch direkt an die Propellermaschine anbinden, so dass ein deutlich einfacherer Aufbau des erfindungsgemäßen Propellerantriebs möglich ist. Gerade bei Flugzeugantrieben ist ein entsprechender Umrichter leicht verzichtbar, da bei Propellerantrieben der Propeller nur in einem sehr eingeschränkten Lastbereich wirkungsgradop- timiert betrieben werden muss. Insbesondere ist bei elektrischen Antrieben, welche eine mechanische Drehbewegung in elektrische Energie übersetzen, ein festes Verhältnis zwischen der Drehzahl dieses elektrischen Antriebs und der Drehzahl des Propellers des Propellerantriebs möglich, denn gera- de bei kleinen Drehzahlen besteht eine nahezu verschwindende Last . On account of this design of the propeller drive according to the invention, this can be achieved by dispensing with converters and the installation space connected to such converters and the weight associated with converters. Furthermore, inverters typically result in about 2% loss, so that a converter-free connection of the electric drive to the propeller machine can be formed with low losses. In contrast, the electric drive can be electrically connected directly to the propeller engine, so that a much simpler structure of the propeller drive according to the invention is possible. Especially with aircraft drives, a corresponding converter is easily dispensed with, since in propeller drives the propeller only has to be operated in an efficiency-optimized manner in a very limited load range. In particular, in electric drives, which translate a mechanical rotary motion into electrical energy, a fixed ratio between the speed of this electric drive and the speed of the propeller of the propeller drive is possible, because straight at low speeds, there is an almost vanishing load.
Geeigneterweise ist bei dem erfindungsgemäßen Propellerantrieb der elektrische Antrieb mit der Propellermaschine wech- selstromgekoppelt , insbesondere dreiphasig elektrisch wechselstromgekoppelt, angebunden. Über die Wechselstromkopplung von elektrischem Antrieb und Propellermaschine lässt sich insbesondere Drehstrom direkt in die Propellermaschine einspeisen . Conveniently, in the case of the propeller drive according to the invention, the electric drive is connected to the propeller machine with alternating current, in particular three-phase electrical alternating current coupled. About the AC coupling of electric drive and propeller machine can be In particular, feed three-phase current directly into the propeller machine.
Zweckmäßig umfasst bei dem erfindungsgemäßen Propellerantrieb der elektrische Antrieb eine elektrische Energiequelle, insbesondere mit einem Antriebsmotor, vorzugsweise einem Verbrennungsmotor, sowie einen daran angebundenen Stromgenerator. Somit lässt sich in an sich bekannter Weise etwa in Kraftstoff gespeicherte Energie in elektrische Energie wan- dein. Expediently, in the case of the propeller drive according to the invention, the electric drive comprises an electrical energy source, in particular with a drive motor, preferably an internal combustion engine, and a power generator connected thereto. Thus, in a manner known per se, energy stored in fuel can be converted into electrical energy.
Vorteilhaft ist bei dem erfindungsgemäßen Propellerantrieb ein elektrischer Energiespeicher, insbesondere mittels eines Umrichters, an den elektrischen Antrieb angebunden. Auf diese Weise lässt sich Energie in den Energiespeicher einspeisen, etwa um den Energiespeicher im Betrieb - im Falle eines Propellerantriebes eines Flugzeugs etwa während des Fluges - zu laden. Ist der Energiespeicher mittels Umrichter an den elektrischen Antrieb angebunden, so muss der Umrichter ledig- lieh für die Differenzleistung, welche jeweils maximal von dem Energiespeicher zur Verfügung gestellt wird, ausgelegt werden. Somit ist auch lediglich diese Differenzleistung verlustbehaftet. Insbesondere in dem Fall eines Propellerantriebs eines Kleinflugzeugs sind Kapazitäten des elektrischen Energiespeichers derart gering, dass sie allenfalls für einige wenige Minuten dauernde volle Leistungsentnahme ausgebildet sind. Vorteilhaft ist/sind auch der/die Umrichter an diese Erfordernisse geeignet angepasst. Insbesondere kann der Umrichter einen sehr kleinen Rückkühler aufweisen, oder aber der Umrichter ist so ausgelegt, dass die Wärmekapazität eines Kühlmediums ausreicht, um während dieser wenigen Minuten Volllastbetrieb eine obere Grenztemperatur nicht zu überschreiten. Es kann folglich berücksichtigt sein, dass ein Volllastbetrieb nicht dauerhaft vorgesehen ist. Advantageously, in the case of the propeller drive according to the invention, an electrical energy store, in particular by means of an inverter, is connected to the electric drive. In this way, energy can be fed into the energy storage, for example, to charge the energy storage during operation - in the case of a propeller drive of an aircraft, for example, during the flight. If the energy storage device is connected to the electric drive by means of a converter, then the converter only has to be designed for the differential power, which is maximally provided by the energy storage device. Thus, only this difference power is lossy. In particular, in the case of a propeller drive of a small aircraft capacities of the electric energy storage are so small that they are possibly formed for a few minutes lasting full power extraction. Advantageously, the inverter (s) are / are suitably adapted to these requirements. In particular, the inverter may have a very small recooler, or the inverter is designed so that the heat capacity of a cooling medium is sufficient to not exceed an upper limit temperature during these few minutes of full load operation. It can therefore be taken into account that full-load operation is not permanently provided.
Geeigneterweise ist oder sind bei dem erfindungsgemäßen Propellerantrieb elektrischer Antrieb und Propellermaschine und/oder elektrischer Antrieb und Energiespeicher je schalt- bar, insbesondere mittels Dreiphasenschaltern, welche bevorzugt als Schütze ausgebildet sind, aneinander angebunden. In dieser Weiterbildung der Erfindung lassen sich folglich elektrischer Energiespeicher und/oder elektrischer Antrieb und/oder Propellermaschine von übrigen Teilen des Propellerantriebs entkoppeln. Vorteilhaft lassen sich so fehlerhafte Komponenten des Propellerantriebs abtrennen, welche ansonsten den übrigen Propellerantrieb stören oder außer Betrieb setzen könnten. Ferner lassen sich flexibel weitere Betriebszustände erreichen, insbesondere das Laden des elektrischen Energiespeichers, wenn am Propeller kein Antriebsmoment anliegt. Suitably, in the propeller drive according to the invention, the electric drive and the propeller machine and / or the electric drive and the energy storage unit are each bar, in particular by means of three-phase switches, which are preferably designed as contactors, connected to each other. In this embodiment of the invention, therefore, electrical energy storage and / or electric drive and / or propeller machine can be decoupled from other parts of the propeller drive. Advantageously, so faulty components of the propeller drive can be separated, which otherwise disturb the other propeller drive or put out of service. Furthermore, further operating states can be achieved flexibly, in particular the charging of the electrical energy store, if no drive torque is applied to the propeller.
Vorteilhafterweise weist bei dem erfindungsgemäßen Propellerantrieb die Propellermaschine mindestens einen Propeller mit steuerbarem Blattanstellwinkel und/oder mindestens eine separate Drehzahlsteuerung und/oder Drehzahlregelung zur Steuerung und/oder Regelung der Drehzahl des zumindest einen Propellers auf. Wird eine Propellermaschine mit steuerbarem Blattanstellwinkel und/oder eine separate Drehzahlsteuerung und/oder -regelung vorgesehen, so kann die Drehzahl des Propellers in einem sehr engen Bereich gehalten werden. Auf diese Weise lässt sich im Flugbetrieb die Propellerdrehzahl in einem festen Verhältnis mit der Drehzahl eines Antriebsmotors des elektrischen Antriebes halten, so dass eine direkte Kupp- lung von Antriebsmotordrehzahl und Propellerdrehzahl erfolgen kann . Advantageously, in the propeller drive according to the invention, the propeller engine at least one propeller with controllable Blattanstellwinkel and / or at least one separate speed control and / or speed control for controlling and / or regulating the speed of the at least one propeller. If a propeller machine with controllable blade pitch and / or separate speed control and / or regulation provided, the speed of the propeller can be kept in a very narrow range. In this way, during flight operation, the propeller speed can be kept in a fixed relationship with the rotational speed of a drive motor of the electric drive, so that a direct coupling of drive motor speed and propeller speed can take place.
Geeigneter Weise weisen bei dem erfindungsgemäßen Propellerantrieb die Propellermaschine einerseits und der elektrische Antrieb andererseits eine unterschiedliche Anzahl von magnetischen Polpaaren auf. Gegebenenfalls lassen sich in dieser Weiterbildung der Erfindung mittels dieser unterschiedlichen Polpaarzahl Drehzahlunterschiede zwischen einem Antriebsmotor des elektrischen Antriebs und dem Propeller ausgleichen, so dass insoweit ein weiterer betriebsrelevanter Freiheitsgrad eröffnet ist. Zweckmäßig weist bei dem erfindungsgemäßen Propellerantrieb die Propellermaschine eine Synchronmaschine auf, welche insbesondere derart ausgelegt ist, dass im Betrieb kein Kipppunkt erreicht wird. Insbesondere ist eine Begrenzung der Dy- namik des Systems vorgesehen, sodass keine zu hohen Beschleunigungsmomente auftreten können, die das Kippmoment des elektrischen Antriebs überschreiten würden. Dies erscheint jedoch unkritisch, da übliche Propellerantriebe lediglich eine geringe Dynamik von insbesondere 10 Sekunden vom Leerlauf bis zur Volllast benötigen. Insbesondere im Falle von Propellerantrieben für Flugzeuge ist eine solche Auslegung daher unproblematisch. Bevorzugt ist bei dem erfindungsgemäßen Propellerantrieb die Synchronmaschine dämpferwicklungsfrei ausgebildet. So verhält sich gerade bei Propellermaschinen das Bremsmoment proportional zun Quadrat der Drehzahl des Propellers der Propellermaschine. Eine zusätzliche Dämpfung muss daher nicht zwangsläufig vorgesehen sein. Vorteilhafterweise kann bei Synchronmaschinen im Form von Propellermaschinen daher auf eine Dämpferwicklung oder einen Dämpferkäfig verzich- tet werden. Vorteilhafterweise kann bei Flugzeugpropellerantrieben das durch die Dämpferwicklung bedingte Gewicht eingespart werden. Suitably, in the case of the propeller drive according to the invention, the propeller machine on the one hand and the electric drive on the other hand have a different number of magnetic pole pairs. Optionally, can be compensated in this development of the invention by means of this different number of pole pairs speed differences between a drive motor of the electric drive and the propeller, so that in this respect a further operationally significant degree of freedom is opened. Expediently, in the case of the propeller drive according to the invention, the propeller machine has a synchronous machine which is designed in particular such that no tilting point is reached during operation. In particular, a limitation of the dynamics of the system is provided, so that too high acceleration torques can occur which would exceed the overturning moment of the electric drive. However, this seems uncritical, since conventional propeller drives only require a low dynamic range of, in particular, 10 seconds from idling to full load. In particular, in the case of propeller drives for aircraft such a design is therefore unproblematic. In the case of the propeller drive according to the invention, the synchronous machine is preferably designed without damper winding. For example, in propeller engines, the braking torque is proportional to the square of the speed of the propeller of the propeller engine. Additional damping therefore does not necessarily have to be provided. Advantageously, in the case of synchronous machines in the form of propeller machines, it is therefore possible to dispense with a damper winding or a damper cage. Advantageously, the weight caused by the damper winding can be saved in aircraft propeller drives.
Geeigneter Weise umfasst der erfindungsgemäße Propellerantrieb einen Kühlkreislauf, wobei der elektrische Antrieb und/oder die Propellermaschine und/oder der Antriebsmotor und/oder der elektrische Generator gemeinsam an den Kühl- kreislauf thermisch angebunden sind. Da in dieser Weiterbildung die Kühlwassertemperatur für Umrichter keine begrenzende Größe bildet, können insbesondere ein Antriebsmotor und die Propellermaschine an denselben Kühlkreislauf angebunden sein.  Suitably, the propeller drive according to the invention comprises a cooling circuit, wherein the electric drive and / or the propeller machine and / or the drive motor and / or the electric generator are thermally connected together to the cooling circuit. Since in this development, the cooling water temperature for converters is not a limiting factor, in particular a drive motor and the propeller engine can be connected to the same cooling circuit.
Idealerweise ist der erfindungsgemäße Propellerantrieb als hybrider Propellerantrieb ausgebildet. Das erfindungsgemäße Fahrzeug ist insbesondere ein Flugzeug und mit einem Propellerantrieb, wie zuvor beschrieben, ausgebildet. Vorteilhafterweise ist das erfindungsgemäße Fahrzeug ein hybrides Fahrzeug. Nachfolgend wird die Erfindung anhand eines in der Zeichnung dargestellten Ausführungsbeispiels näher erläutert. Es zeigen : Ideally, the propeller drive according to the invention is designed as a hybrid propeller drive. The vehicle according to the invention is in particular an aircraft and with a propeller drive, as described above. Advantageously, the vehicle according to the invention is a hybrid vehicle. The invention will be explained in more detail with reference to an embodiment shown in the drawing. Show it :
Figur 1 ein bekanntes Flugzeug mit einem dem Stand der Figure 1 is a known aircraft with the state of
Technik entsprechenden Propellerantrieb schematisch in einer Prinzipskizze sowie  Technology corresponding propeller drive schematically in a schematic diagram as well
Figur 2 ein erfindungsgemäßes Flugzeug mit einem erfindungsgemäßen Propellerantrieb schematisch in einer Prinzipskizze . Figure 2 shows an inventive aircraft with a propeller drive according to the invention schematically in a schematic diagram.
Das in Figur 1 dargestellte Flugzeug 10 weist einen Flugzeugantrieb in Form eines Propellerantriebs 20 auf. Der Aufbau dieses Propellerantriebs 20 ist an sich bekannt und zählt zum Stand der Technik. The aircraft 10 shown in FIG. 1 has an aircraft drive in the form of a propeller drive 20. The structure of this propeller drive 20 is known per se and belongs to the prior art.
Der Propellerantrieb 20 umfasst zunächst einen Verbrennungs- motor 30, welcher Kraftstoff, im dargestellten Fall Flugzeugbenzin, zum Zwecke der Gewinnung von kinetischer Energie, verbrennt. Der Verbrennungsmotor 30 stellt diese kinetische Energie in Form von Rotationsenergie mittels einer rotierenden Welle 40 bereit. Die rotierende Welle 40 ist an einen elektrischen Generator 50 angebunden, welcher die kinetische Energie mittels elektromagnetischer Induktion in elektrische Energie umsetzt. Der elektrische Generator 50 stellt die elektrische Energie in Form von Drehstrom entsprechender Leistung bereit. Dieser Drehstrom speist über eine dreiphasi- ge Leitungsverbindung 60 einen elektrischen Umrichter 70, welcher den Drehstrom in einen Gleichspannungszwischenkreis 80 hin umrichtet. An diesen Gleichspannungszwischenkreis 80 ist wiederum ein Umrichter 90 angebunden, welcher aus dem Gleichstrom des Gleichspannungskreises 80 einen Drehstrom ge- eigneter Frequenz zum Antrieb einer Elektromaschine 100 bereitstellt, welche den Drehstrom in kinetische Energie eines rotierenden Propellers 110 umsetzt. Im in Figur 1 dargestellten Beispiel sind antriebsseitig des Gleichspannungszwischenkreises 80 jeweils zwei Umrichter 90 vorhanden, welche jeweils eine Elektromaschine 100 zum Antrieb jeweils eines Propellers 110 speisen. The propeller drive 20 initially comprises a combustion engine 30, which burns fuel, in the case illustrated aviation gasoline, for the purpose of obtaining kinetic energy. The internal combustion engine 30 provides this kinetic energy in the form of rotational energy by means of a rotating shaft 40. The rotating shaft 40 is connected to an electric generator 50, which converts the kinetic energy by means of electromagnetic induction into electrical energy. The electric generator 50 provides the electrical energy in the form of three-phase current of corresponding power. This three-phase current feeds an electrical converter 70 via a three-phase line connection 60, which converts the three-phase current into a DC intermediate circuit 80. In turn, a converter 90 is connected to this DC voltage intermediate circuit 80 and supplies from the DC current of the DC voltage circuit 80 a three-phase current suitable for driving an electric machine 100, which converts the three-phase current into kinetic energy of a rotating propeller 110. In the example shown in FIG. 1, two converters 90 each are provided on the drive side of the DC intermediate circuit 80, each of which feeds an electric machine 100 for driving a respective propeller 110.
Zur Zwischenspeicherung elektrischer Energie ist ferner im in Figur 1 gezeigten Beispiel eine Hochspannungsbatterie 130 vorhanden, welche mittels einer Gleichstromverbindung an den Gleichspannungszwischenkreis 80 angebunden ist. For intermediate storage of electrical energy, a high-voltage battery 130 is furthermore provided in the example shown in FIG. 1, which is connected to the DC intermediate circuit 80 by means of a direct current connection.
Das in Figur 2 dargestellte erfindungsgemäße Flugzeug 10' hingegen weist einen Flugzeugantrieb in Form eines erfindungsgemäßen Propellerantriebs 20' auf. Auch der in Figur 2 gezeigte Propellerantrieb 20' weist einen Verbrennungsmotor 30 auf, welcher Kraftstoff in Form von Flugzeugbenzin verbrennt und kinetische Energie als Rotationsenergie mittels einer rotierenden Welle 40 bereitstellt. Wie im in Figur 1 dargestellten Beispiel ist die rotierende Welle 40 an einen elektrischen Generator 50 angebunden, welcher die kinetische Energie mittels elektromagnetischer Induktion in elektrische Energie umsetzt. Auch gemäß Figur 2 stellt der elektrische Generator 50 die elektrische Energie in Form von Drehstrom entsprechender Leistung bereit. In contrast, the aircraft 10 'according to the invention shown in FIG. 2 has an aircraft drive in the form of a propeller drive 20' according to the invention. The propeller drive 20 'shown in FIG. 2 also has an internal combustion engine 30, which burns fuel in the form of aircraft fuel and provides kinetic energy as rotational energy by means of a rotating shaft 40. As in the example shown in Figure 1, the rotating shaft 40 is connected to an electric generator 50, which converts the kinetic energy by means of electromagnetic induction into electrical energy. Also in accordance with FIG. 2, the electric generator 50 provides the electrical energy in the form of three-phase current of corresponding power.
Im Unterschied zum in Figur 1 dargestellten Propellerantrieb 20 ist jedoch der elektrische Generator 50 gemäß Figur 2 nicht über zwei Umrichter 70, 90 und einen zwischenliegenden Gleichspannungszwischenkreis 80 an die Elektromaschine 100 angebunden, sondern der elektrische Generator 50 speist mittels einer dreiphasigen Leitungsverbindung 60 die Elektromaschine 100 direkt, das heißt umrichterfrei. Folglich wird der in dem elektrischen Generator 50 erzeugte Drehstrom direkt in die Elektromaschine 100 eingespeist, so dass der Drehstrom des elektrischen Generators 50 direkt mittels der Elektroma- schinen 100 in Drehbewegung des Propellers 110 umgesetzt werden kann . Im in Figur 2 dargestellten Ausführungsbeispiel der Erfindung weist der Propellerantrieb 20' zwei parallel an die dreiphasige Leitungsverbindung 60 angebundene Elektromaschinen 100 in Gestalt von Synchronmaschinen mit jeweils einem daran an- gebundenen Propeller 110 auf. Es versteht sich, dass in weiteren, nicht eigens gezeigten, Ausführungsbeispielen eine abweichende Anzahl von Elektromaschinen 100 mit jeweils daran angebundenen Propellern 110 vorgesehen sein kann. Die Elektromaschinen 100 sind dämpferwicklungsfrei ausgebildet, d.h., eine Dämpferwicklung oder ein Dämpferkäfig sind nicht vorhanden . In contrast to the propeller drive 20 shown in FIG. 1, however, the electric generator 50 according to FIG. 2 is not connected to the electric machine 100 via two converters 70, 90 and an intermediate DC voltage intermediate circuit 80, but the electric generator 50 feeds the electric machine 100 by means of a three-phase line connection 60 directly, that means inverter-free. Consequently, the three-phase current generated in the electric generator 50 is fed directly into the electric machine 100, so that the three-phase current of the electric generator 50 can be directly converted into rotary motion of the propeller 110 by means of the electric machines 100. In the exemplary embodiment of the invention shown in FIG. 2, the propeller drive 20 'has two electric machines 100 connected in parallel to the three-phase line connection 60 in the form of synchronous machines, each with a propeller 110 connected thereto. It is understood that in other, not specifically shown, embodiments, a different number of electric machines 100 may be provided with each connected thereto propellers 110. The electric machines 100 are formed damper winding free, ie, a damper winding or a damper cage are not present.
Zur Zwischenspeicherung elektrischer Energie ist zudem im in Figur 2 gezeigten Ausführungsbeispiel eine Hochspannungsbat- terie 130 vorhanden, welche mittels eines Umrichters 70 an die dreiphasige Leitungsverbindung 60, welche den elektrischen Generator 50 und die elektrischen Maschinen 100 miteinander verbindet, angebunden ist. Dazu richtet der Umrichter 70 den Drehstrom in einen Gleichstromkreis 120 zum Laden der Hochspannungsbatterie 130 um. For intermediate storage of electrical energy, a high-voltage battery 130 is also present in the exemplary embodiment shown in FIG. 2, which is connected by means of an inverter 70 to the three-phase line connection 60 which connects the electrical generator 50 and the electrical machines 100 to one another. For this purpose, the inverter 70 directs the three-phase current into a DC circuit 120 for charging the high-voltage battery 130.
Mittels eines elektrischen Schalters 140 kann zum einen die Hochspannungsbatterie 130 vom übrigen Propellerantrieb 20' entkoppelt werden, wenn die Hochspannungsbatterie 130 für den Betrieb des Propellerantriebs 20' nicht erforderlich ist.By means of an electrical switch 140, on the one hand, the high-voltage battery 130 can be decoupled from the remaining propeller drive 20 'when the high-voltage battery 130 is not required for the operation of the propeller drive 20'.
Beispielsweise wird die Hochspannungsbatterie 130 nur dann an den übrigen Propellerantrieb 20' angebunden, wenn tatsächlich Energie aus der Hochspannungsbatterie 130 oder in die Hochspannungsbatterie 130 gespeist werden soll. For example, the high-voltage battery 130 is connected to the rest of the propeller drive 20 'only when energy is to be supplied from the high-voltage battery 130 or into the high-voltage battery 130.
Ferner kann mittels eines weiteren elektrischen Schalters 140 der Antriebsmotor 30 zusammen mit der Welle 40 und dem elektrischen Generator 50 vom übrigen Propellerantrieb 20' entkoppelt werden. Mittels eines weiteren elektrischen Schalters 140 lassen sich ferner die Elektromaschinen 100 gemeinsam mit den daran angebundenen Propellern 110 vom übrigen Propellerantrieb 20' entkoppeln. Insbesondere lassen sich mittels der elektrischen Schalter 140 auch gegebenenfalls schadhafte Teile des Propellerantriebs 20' entkoppeln. Die elektrischen Schalter 140 sind im dargestellten Ausführungsbeispiel als mechanische Schalter für hohe Leistungen, nämlich als Schütze in der Art von Dreiphasenschaltern, aus- gebildet. Grundsätzlich können in weiteren, nicht eigens dargestellten Ausführungsbeispielen die elektrischen Schalter 140 auch auf sonstige Weise realisiert sein. Furthermore, by means of a further electrical switch 140, the drive motor 30 together with the shaft 40 and the electric generator 50 can be decoupled from the remaining propeller drive 20 '. By means of a further electrical switch 140, furthermore, the electric machines 100 together with the connected propellers 110 can be decoupled from the remaining propeller drive 20 '. In particular, defective parts of the propeller drive 20 'may also be decoupled by means of the electrical switches 140. In the exemplary embodiment illustrated, the electrical switches 140 are designed as mechanical switches for high powers, namely as contactors in the form of three-phase switches. In principle, the electrical switches 140 can be realized in other, not specifically illustrated embodiments.
Im in Figur 2 dargestellten Ausführungsbeispiel ist ferner ein gemeinsamer Kühlkreislauf 150 zur Kühlung von Verbrennungsmotor 30 und elektrischem Generator 50 vorgesehen. Der Kühlkreislauf 150 ist ein Kühlwasserkreislauf. In the exemplary embodiment illustrated in FIG. 2, a common cooling circuit 150 for cooling the internal combustion engine 30 and the electric generator 50 is also provided. The cooling circuit 150 is a cooling water circuit.

Claims

Patentansprüche claims
1. Propellerantrieb (20'), insbesondere Fahrzeugantrieb, vorzugsweise Flugzeugantrieb, umfassend eine Propellermaschi - ne (100) sowie einen elektrischen Antrieb (30; 50), welcher umrichterfrei an die Propellermaschine (100) angebunden ist. 1. Propeller drive (20 '), in particular a vehicle drive, preferably an aircraft drive, comprising a propeller machine (100) and an electric drive (30; 50) which is connected to the propeller machine (100) in a converter-free manner.
2. Propellerantrieb nach Anspruch 1, bei welchem der elektrische Antrieb (30, 50) mit der Propellermaschine (100) wech- selstromgekoppelt , insbesondere dreiphasig elektrisch angebunden (60) , ist . 2. propeller drive according to claim 1, wherein the electric drive (30, 50) with the propeller machine (100) alternating current coupled, in particular three-phase electrically connected (60).
3. Propellerantrieb nach einem der vorhergehenden Ansprüche, bei welchem der elektrische Antrieb (30, 50) eine elekt- rische Energiequelle, insbesondere einen Antriebsmotor, vorzugsweise einen Verbrennungsmotor (30) , sowie einen an diesen angebundenen Stromgenerator (50) aufweist. 3. Propeller drive according to one of the preceding claims, wherein the electric drive (30, 50) an electrical energy source, in particular a drive motor, preferably an internal combustion engine (30), and a connected to this power generator (50).
4. Propellerantrieb nach einem der vorhergehenden Ansprü- che, umfassend einen elektrischen Energiespeicher, welcher insbesondere mittels Umrichter (70) , an den elektrischen Antrieb (30, 50) angebunden ist. 4. propeller drive according to one of the preceding claims che, comprising an electrical energy storage, which in particular by means of inverter (70), to the electric drive (30, 50) is connected.
5. Propellerantrieb nach einem der vorhergehenden Ansprü- che, bei welchem elektrischer Antrieb (30, 50) und Propellermaschine (100) und/oder elektrischer Antrieb (30, 50) und elektrischer Energiespeicher (130) insbesondere mittels Dreiphasenschaltern (140), je schaltbar aneinander angebunden sind . 5. propeller drive according to one of the preceding claims che, in which electric drive (30, 50) and propeller machine (100) and / or electric drive (30, 50) and electrical energy storage (130), in particular by means of three-phase switches (140), each switchable are connected to each other.
6. Propellerantrieb nach einem der vorhergehenden Ansprüche, bei welchem die Propellermaschine (100) mindestens einen Propeller (110) mit steuerbarem Blattanstellwinkel und/oder mindestens eine separate Drehzahlsteuerung oder Drehzahlrege- lung aufweist. 6. propeller drive according to one of the preceding claims, wherein the propeller machine (100) has at least one propeller (110) with controllable Blattanstellwinkel and / or at least one separate speed control or speed control.
7. Propellerantrieb nach einem der vorhergehenden Ansprüche, bei welchem die Propellermaschine (100) einerseits und der elektrischer Antrieb (30, 50) andererseits eine unterschiedliche Anzahl von magnetischen Polpaaren aufweisen. 7. propeller drive according to one of the preceding claims, wherein the propeller machine (100) on the one hand and the electric drive (30, 50) on the other hand have a different number of magnetic pole pairs.
8. Propellerantrieb nach einem der vorhergehenden Ansprü- che, bei welchem die Propellermaschine (100) eine Synchronmaschine aufweist, welche insbesondere derart ausgelegt ist, dass im Betrieb kein Kipppunkt erreicht wird. 8. propeller drive according to one of the preceding claims che, in which the propeller machine (100) has a synchronous machine, which is designed in particular such that no tipping point is reached during operation.
9. Propellerantrieb nach dem vorhergehenden Anspruch, bei welchem die Propellermaschine dämpferwicklungsfrei ausgebildet ist. 9. propeller drive according to the preceding claim, wherein the propeller machine is formed damper winding free.
10. Propellerantrieb nach einem der vorhergehenden Ansprüche, insbesondere nach Anspruch 3, aufweisend einen Kühl- kreislauf, bei welchem der elektrische Antrieb (30, 50) und/oder die Propellermaschine (100) und/oder der Antriebsmotor (30) und/oder elektrischer Generator (50) gemeinsam thermisch an den Kühlkreislauf (150) angebunden sind. 10. Propeller drive according to one of the preceding claims, in particular according to claim 3, comprising a cooling circuit, in which the electric drive (30, 50) and / or the propeller machine (100) and / or the drive motor (30) and / or electrical Generator (50) are connected together thermally to the cooling circuit (150).
11. Fahrzeug, insbesondere Flugzeug (10'), mit einem Propellerantrieb (20') nach einem der vorhergehenden Ansprüche. 11. vehicle, in particular aircraft (10 '), with a propeller drive (20') according to one of the preceding claims.
EP16739484.0A 2015-07-20 2016-07-18 Propeller drive and a vehicle, particularly an aircraft Withdrawn EP3280644A1 (en)

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DE102015213580A1 (en) 2017-01-26

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