Aircraft Propeller Device, Method for Driving an Aircraft Propeller, Use of a Bearing for an Aircraft Propeller Drive and Use of an Electric Machine

• US 20100038473A1
• Filed: 01/14/2008
• Published: 02/18/2010
• Est. Priority Date: 01/15/2007
• Status: Abandoned Application

• Current Assignee: Gif Gesellschaft Fuer Industrieforschung Mbh
• Original Assignee: Gif Gesellschaft Fuer Industrieforschung Mbh
• Inventors: Voigt, Dieter, Schneider, Heinz-Dieter
• Application Number:
  US12/448,900
• Publication Number:
  US 20100038473A1
• Time in Patent Office: Days
• US Class Current: 244/60
• CPC Class Codes: B64D 2027/026 comprising different types of power plants, e.g. combination of an electric motor and a gas-turbines
• CPC Class Codes: B64D 27/026 comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine Hybrid electric aircraft B64D27/33
• CPC Class Codes: B64D 27/24 using steam or spring force jet aircraft B64D27/16
• CPC Class Codes: B64D 35/00 Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
• CPC Class Codes: B64D 35/08 characterised by the transmission being driven by a plurality of power plants
• CPC Class Codes: F16F 15/134 Wound springs F16F15/1333, F16F15/1337, F16F15/137 take precedence
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 74/2132 Structural detail, e.g., fiber, held by magnet, etc.

Abstract

To improve the damping of vibrations in aircraft propeller drives, the invention discloses an aircraft propeller drive comprising a propeller, a motor and a drive train between the propeller and the motor. The drive train of the aircraft propeller drive has a torsional vibration damper.

Claims

1. An aircraft propeller drive comprising a propeller, a motor, and a drive train between the propeller and the motor, wherein the drive train comprises a dual-mass flywheel (7).

2. The aircraft propeller drive according to claim 1, wherein the dual-mass flywheel (7) comprises mass distribution in which a primary mass (420) of the torsional vibration damper is more than 35%, while a secondary mass (421) of the torsional vibration damper is less than 65%, of the mass of the torsional vibration damper.

3. The aircraft propeller drive according to claim 2, wherein the dual-mass flywheel (7) comprises mass distribution in which a primary mass (420) of the torsional vibration damper is up to 65%, while a secondary mass (421) of the torsional vibration damper is up to 35%, of the mass of the torsional vibration damper.

4. The aircraft propeller drive according to claim 1, wherein the dual-mass flywheel (7) comprises a primary mass (420) with a moment of inertia of between 0.035 kg/m² and 0.220 kg/m².

5. The aircraft propeller drive according to claim 1, wherein the dual-mass flywheel (7) comprises means for providing additional damping mass, which means are unsuitable for the transmission of drive forces.

6. The aircraft propeller drive according to claim 5, wherein with the use of the means for the additional damping mass, additional moments of inertia for vibration damping can be provided.

7. The aircraft propeller drive according to claim 5, wherein the means for the additional damping mass comprise components and/or component assemblies with a weight of more than 100 g.

9. The aircraft propeller drive according to claim 1, wherein otherwise, i.e. except for a torsional vibration damper or a hydrodynamic clutch, the drive train is rigid.

10. The aircraft propeller according to claim 1, wherein the drive train comprises a break-off separation device.

11. The aircraft propeller drive according to claim 1, further comprising a lubricant pump for providing lubricant to regions of the aircraft propeller drive that require lubricant, for example to bearings and/or gearwheels, wherein the lubricant pump is arranged directly on a drive shaft of the motor, or on a shaft of the drive train or on a gear-arrangement input shaft.

12. The aircraft propeller drive according to claim 1, further comprising a lubricant pump for providing lubricant to regions of the aircraft propeller drive, which regions require lubricant, for example to bearings and/or gearwheels, wherein the lubricant pump comprises a tapered roller bearing of the aircraft propeller drive.

13. The aircraft propeller drive according to claim 1, further comprising a lubricant pump for providing lubricant to regions of the aircraft propeller drive, which regions require lubricant, for example to bearings and/or gearwheels, wherein the lubricant pump is formed by means of a tapered roller bearing of the aircraft propeller drive.

14. The aircraft propeller drive according to claim 1, further comprising a hybrid drive (517) for driving the aircraft propeller (501).

15. The aircraft propeller drive according to claim 1, further comprising means to increase the drive output of the aircraft propeller drive (501).

16. The aircraft propeller drive according to claim 15, wherein the means to increase the drive output comprise an electric motor (518).

17. The aircraft propeller drive according to claim 1, wherein an electric motor (518) is arranged on a gear shaft of the aircraft propeller drive (501).

18. The aircraft propeller drive according to claim 1, wherein an output shaft of an electric motor (518) forms at least part of a gear shaft of the aircraft propeller drive (501).

19. The aircraft propeller drive according to claim 1, wherein an electric motor (518) is arranged between a clutch, in particular a slip clutch (508), and a further drive motor (502).

20. The aircraft propeller drive according to claim 1, wherein an electric motor (518) is arranged on a gear shaft so that it can be decoupled from a propeller shaft (506).

21. The aircraft propeller drive according to claim 16, wherein the electric motor is a bifunctional electric machine.

22. The aircraft propeller drive according to claim 1, wherein a torsional vibration damper of the aircraft propeller drive (501) comprises a bifunctional electric machine (518).

23. The aircraft propeller drive according to claim 14, further comprising a storage device for electrical energy in the form of a high-capacity battery of an ultracapacitor.

24. The aircraft propeller drive according to claim 1, further comprising two motors whose torque and/or rotary speed can be added when required.

8. An aircraft propeller drive comprising a propeller, a motor, and a drive train between the propeller and the motor, wherein the drive train comprises a hydrodynamic clutch, for example a converter, in particular a Fö

ttinger clutch.

25. A method for driving an aircraft propeller with a motor, wherein vibrations, in particular of the motor, are damped by means of a dual-mass flywheel (7).

26. The method according to claim 25, wherein by means of a bearing, in particular a tapered roller bearing of the aircraft propeller drive, lubricant can be conveyed to regions that require lubricant.

27. The method according to claim 25, wherein in a first operating state the aircraft propeller drive (501) is driven by a first motor, for example an internal combustion engine (502), and in a second operating state, as an alternative or cumulatively, the aircraft propeller drive (501) is driven by a second motor, for example an electric motor (518).

28. The method according to claim 25, wherein the aircraft propeller drive (501) is driven by a first motor, for example an internal combustion engine (502) and, if there is an increased demand for output, the aircraft propeller drive (501) is additionally driven by a second motor, for example an electric motor (518).

29. The method according to claim 27, wherein both the first motor and the second motor can be operated for a long time.

30. The method according to claim 25, wherein at least during output-intensive operating phases or flight phases, for example during takeoff or ascent, a further motor (518) in addition to a first motor (502) drives a shared gear shaft.

31. The method according to claim 25, wherein by means of an electric machine, by means of which electrical energy is provided, additional drive output is introduced into the aircraft propeller drive (501).

32. The method according to claim 27, wherein electrical energy is held in intermediate storage in an ultracapacitor.

33. The use of a bearing, in particular a tapered roller bearing, of an aircraft propeller drive, in particular of a motor of the aircraft propeller drive, as a lubricant pump by means of which lubricant is conveyed to regions of the aircraft that require lubricant.

34. The use of an electric machine of an aircraft propeller drive as a means to increase the drive output of the aircraft propeller drive.