Small-size traction drive transmission system for use in microturbine-powered aircraft

• US 20050153812A1
• Filed: 01/12/2004
• Published: 07/14/2005
• Est. Priority Date: 01/12/2004
• Status: Abandoned Application

• Current Assignee: Locust USA, Inc.
• Original Assignee: Locust USA, Inc.
• Inventors: Box, J. William, Kish, Jules G.
• Application Number:
  US10/756,031
• Publication Number:
  US 20050153812A1
• Time in Patent Office: Days
• US Class Current: 475/257
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 35/00 Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 50/12 using turbine engines, e.g. turbojets or turbofans
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 50/14 ducted or shrouded
• CPC Class Codes: B64U 50/20 Transmission of mechanical power to rotors or propellers
• CPC Class Codes: F16H 1/20 involving more than two intermeshing members
• CPC Class Codes: F16H 1/227 comprising two or more gearwheels in mesh with the same internally toothed wheel
• CPC Class Codes: F16H 13/04 with balls or with rollers acting in a similar manner

Abstract

A transmission system that is used in conjunction with a microturbine engine for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other applications. The output shaft of the microturbine engine preferably operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP (and most preferably operates in an extended range between 50,000 RPM and 200,000 RPM with an output power between 200 HP and 5 HP). The transmission system includes a traction drive stage that provides a reduction ratio preferably having a value of at least 7, and most preferably greater than 9. The transmission system is of small-size preferably having a maximum diameter less than twelve inches. Preferably, the input stage of the transmission system is self-equilibrating such that first shaft can be supported without bearings and is operably coupled to the output shaft of the microturbine engine by an outside diameter piloted spline coupling mechanism. For vertical lift applications, a single traction stage along with a bevel gear assembly or other shaft transmission mechanism can be used to provide the necessary RPM reduction.

Claims

1. A transmission system for use with a microturbine engine having an output shaft, the transmission system comprising:

a first shaft operably coupled to the output shaft of the microturbine engine;

a traction drive stage that utilizes a planetary system of rollers to drive a second shaft at a reduced rotation speed with respect to said first shaft.

2. A transmission system according to claim 1, wherein:

the output shaft of the microturbine engine operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP.

3. A transmission system according to claim 2, wherein:

said traction drive stage provides a reduction ratio defining rotational speed of said first shaft over rotational speed of said second shaft, said reduction ratio having a value of at least 4.

4. A transmission system according to claim 3, wherein:

said reduction ratio has a value greater than 5.

5. A transmission system according to claim 1, further comprising:

a geared reduction stage operably coupled to said second shaft.

6. A transmission system according to claim 5, wherein:

said gear reduction stage comprises a planetary system having a sun gear, a plurality of planetary pinion gears coupled to a carrier, and a ring gear.

7. A transmission system according to claim 6, wherein:

said sun gear is integral to said second shaft.

8. A transmission system according to claim 7, wherein:

said ring gear is stationary and said carrier rotates about said sun gear; and

output of said transmission system is provided by a shaft operably coupled to said carrier.

9. A transmission system according to claim 5, wherein:

said traction drive stage comprises a plurality of pinion rollers;

said gear reduction stage comprises a plurality of spur pinion gears affixed to corresponding shafts driven by said plurality of pinion rollers, said plurality of spur pinion gears adapted to drive a ring gear coupled thereto; and

output of said transmission system is provided by a shaft operably coupled to said ring gear.

10. A transmission system according to claim 5, wherein:

said traction drive stage and said gear reduction stage provide a reduction ratio having a value of at least 19.

11. A transmission system according to claim 10, wherein:

said reduction ratio has a value greater than 24.

12. A transmission system according to claim 1, wherein:

largest diameter of said transmission system is less than twelve inches.

13. A transmission system according to claim 1, wherein:

an output shaft of said transmission system is operably coupled to a rotating element that propels an aircraft body.

14. A transmission system according to claim 13, wherein:

said aircraft body comprises a fixed-wing aircraft body, and said rotating element comprises a propeller.

15. A transmission system according to claim 13, wherein:

said aircraft body comprises a vertical lift aircraft body, and said rotating element comprises a rotor.

16. A transmission system according to claim 1, wherein:

the output shaft of said microturbine engine is coupled to said first shaft by an outside diameter piloted spline coupling mechanism.

17. A transmission system according to claim 16, wherein:

an outside diameter section of said first shaft includes a plurality of pilot grooves that engage projections that extend radially downward from a corresponding inside diameter section of the output shaft of the microturbine engine.

18. A propulsion system for an aircraft comprising:

a microturbine engine having an output shaft; and

a transmission system according to claim 1.

19. A propulsion system according to claim 18, further comprising:

shaft transmission means for transmitting rotation of said second shaft of said traction drive stage to a vertical rotating shaft of a vertical-lift aircraft.

20. A propulsion system according to claim 19, wherein:

said shaft transmission means comprises a bevel gear assembly coupled directly between said second shaft of said traction drive stage and said vertical rotating shaft.

21. A propulsion system according to claim 19, wherein:

the output shaft of the microturbine engine operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP.

22. A propulsion system according to claim 19, wherein:

reduction of the rotational speed of the output shaft of the microturbine engine is provided only by said traction drive stage and said shaft transmission means.

23. A propulsion system according to claim 22, wherein:

said traction drive stage provide a reduction ratio having a value of at least 5.

24. A propulsion system according to claim 23, wherein:

said reduction ratio has a value greater than 8.

25. A propulsion system according to claim 22, wherein:

said shaft transmission means provides a reduction ratio having a value of at least 2.

26. A propulsion system according to claim 17, wherein:

largest diameter of said transmission system is less than twelve inches.

27. An aircraft comprising:

an aircraft body;

the propulsion system of claim 18;

and

a rotating element, operably coupled to said propulsion system for propelling said aircraft body.

28. An aircraft according to claim 27, wherein:

said aircraft body comprises a vertical-lift aircraft body, and said rotating element comprises a rotor.

29. An aircraft according to claim 27, wherein:

said aircraft body comprises a fixed-wing aircraft body, and said rotating element comprises a propeller.