EP3280644A1 - Propulsion à hélice et véhicule, notamment avion - Google Patents

Propulsion à hélice et véhicule, notamment avion

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Withdrawn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)
English (en)
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/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • 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
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • 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)
  • Power Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (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

L'invention concerne une propulsion à hélice (20'), notamment une propulsion d'avion, qui comprend une machine à hélice (100) ainsi qu'un entraînement électrique (30, 50) qui est raccordé à la machine à hélice (100) sans détour par un convertisseur. L'avion (10) est doté d'une telle propulsion à hélice (20).
EP16739484.0A 2015-07-20 2016-07-18 Propulsion à hélice et véhicule, notamment avion Withdrawn EP3280644A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015213580.2A DE102015213580A1 (de) 2015-07-20 2015-07-20 Propellerantrieb und Fahrzeug, insbesondere Flugzeug
PCT/EP2016/067048 WO2017013059A1 (fr) 2015-07-20 2016-07-18 Propulsion à hélice et véhicule, notamment avion

Publications (1)

Publication Number Publication Date
EP3280644A1 true EP3280644A1 (fr) 2018-02-14

Family

ID=56418522

Family Applications (1)

Application Number Title Priority Date Filing Date
EP16739484.0A Withdrawn EP3280644A1 (fr) 2015-07-20 2016-07-18 Propulsion à hélice et véhicule, notamment avion

Country Status (5)

Country Link
US (1) US10435164B2 (fr)
EP (1) EP3280644A1 (fr)
CN (1) CN107848632A (fr)
DE (1) DE102015213580A1 (fr)
WO (1) WO2017013059A1 (fr)

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Also Published As

Publication number Publication date
CN107848632A (zh) 2018-03-27
DE102015213580A1 (de) 2017-01-26
US10435164B2 (en) 2019-10-08
US20180201383A1 (en) 2018-07-19
WO2017013059A1 (fr) 2017-01-26

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