NON-LUBRICATED ARCHITECTURE FOR A TURBOSHAFT ENGINE

• US 20130089409A1
• Filed: 06/14/2011
• Published: 04/11/2013
• Est. Priority Date: 06/15/2010
• Status: Active Grant

• Current Assignee: Safran Helicopter Engines
• Original Assignee: Turbomeca
• Inventors: Bedrine, Olivier, Paty, Gerard
• Granted Patent: US 10,336,442 B2
• Time in Patent Office: Days
• US Class Current: 415/122.1
• CPC Class Codes: B64C 27/12 Rotor drives
• CPC Class Codes: F01D 25/22 using working-fluid or other gaseous fluid as lubricant
• CPC Class Codes: F02C 3/103 the compressor being of the centrifugal type
• CPC Class Codes: F02C 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F05D 2220/329 in helicopters
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: F05D 2240/51 Magnetic
• CPC Class Codes: F05D 2240/52 Axial thrust bearings
• CPC Class Codes: F05D 2240/54 Radial bearings
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A turbine engine for a helicopter, the helicopter including a main gearbox, a rotor, and a speed-reducing device housed entirely within the main gearbox of the helicopter while also being connected to the rotor, the turbine engine including a casing, a gas generator with a gas generator shaft, and a free turbine for being driven in rotation by a gas stream generated by the gas generator, the free turbine including a free turbine shaft. When the turbine engine is fastened to the gearbox of the helicopter, the free turbine shaft extends axially into the main gearbox of the helicopter to be connected directly to the speed-reducing device.

Claims

1-12. -12. (canceled)

13. A turbine engine not including a speed reducer and for connection to a helicopter, the helicopter including a main gearbox, a rotor, and a speed-reducing device housed entirely within the main gearbox of the helicopter while also being connected to the rotor, the turbine engine comprising:

a casing;

a gas generator with a gas generator shaft; and

a free turbine for being driven in rotation by a gas stream generated by the gas generator, the free turbine having a free turbine shaft;

wherein, when the turbine engine is fastened to the main gearbox of the helicopter, the free turbine shaft extends axially into the main gearbox of the helicopter to be connected directly to the speed-reducer device.

14. A turbine engine according to claim 13, further comprising at least one non-lubricated bearing arranged radially between the casing and the free turbine shaft.

15. A turbine engine according to claim 13, further comprising at least one non-lubricated bearing arranged radially between the gas generator shaft and the engine casing.

16. A turbine engine according to claim 13, further comprising an electricity generator directly connected to the gas generator shaft.

17. A turbine engine according to claim 13, further comprising a non-lubricated axial abutment device arranged axially between the gas generator shaft and the engine casing.

18. A turbine engine according to claim 13, further comprising a force taking up device for taking up axial forces from the gas generator shaft, the force taking up device being arranged radially between the free turbine shaft and the gas generator shaft.

19. A turbine engine according to claim 18, further comprising a sealing gasket arranged radially between the free turbine shaft and the gas generator shaft.

20. A helicopter comprising:

a main gearbox;

a rotor;

a speed-reducer device housed entirely within the main gearbox, while being connected to the rotor; and

a turbine engine according to claim 13, the engine casing being fastened to the main gearbox of the helicopter with the free turbine shaft extending axially inside the main gearbox and being directly connected to the speed-reducer device.

21. A helicopter according to claim 20, further comprising a force taking up device for taking up axial forces from the free turbine shaft, which force taking up device is housed in the main gearbox of the helicopter while being fastened to the shaft of the free turbine.

22. A helicopter according to claim 21, wherein the force taking up device comprises a rolling bearing mounted on the speed-reducer device and co-operating with an axial abutment of the main gearbox.

23. A helicopter according to claim 20, further comprising a sealing member arranged between the main gearbox of the helicopter and the engine casing.

24. A helicopter according to claim 20, wherein the turbine engine includes an electricity generator directly connected to the gas generator shaft, and wherein the helicopter further includes electrical equipment electrically powered by the generator.