Non-lubricated architecture for a turboshaft engine

• US 10,336,442 B2
• Filed: 06/14/2011
• Issued: 07/02/2019
• Est. Priority Date: 06/15/2010
• Status: Active Grant

• Current Assignee: Safran Helicopter Engines
• Original Assignee: Safran Helicopter Engines
• Inventors: Bedrine, Olivier, Paty, Gerard
• Primary Examiner(s): McCaffrey, Kayla
• Application Number:
  US13/703,530
• Publication Number:
  US 20130089409A1
• Time in Patent Office: 2,940 Days
• 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. An assembly comprising:

a turbine engine and a main gearbox for a helicopter having a rotor, said main gearbox comprising a speed-reducing device including gearing and a lubricated rolling bearing and housed entirely within the main gearbox while also being connected to the rotor, the turbine engine, not having a speed reducer and free of an oil lubrication system, 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 the casing of the turbine engine is fastened to the main gearbox,

wherein a sealing member is arranged between the main gearbox and the casing of the turbine engine,

wherein the free turbine shaft extends axially into the main gearbox to be connected directly to the speed-reducer device via a coupling sleeve provided on a free end of the free turbine shaft, the coupling sleeve being supported by the lubricated rolling bearing, and the lubricated rolling bearing cooperating with an axial abutment of the main gearbox, and

wherein an axis of the free turbine shaft is perpendicular to an axis of the rotor.

2. The assembly according to claim 1, wherein the turbine engine further comprises at least one non-lubricated bearing arranged radially between the casing and the free turbine shaft.

3. The assembly according to claim 1, wherein the turbine engine further comprises at least one non-lubricated bearing arranged radially between the gas generator shaft and the casing.

4. The assembly according to claim 1, wherein the turbine engine further comprises an electricity generator directly connected to the gas generator shaft.

5. The assembly according to claim 1, wherein the turbine engine further comprises a non-lubricated air or magentic axial abutment arranged axially between the gas generator shaft and the casing.

6. The assembly according to claim 1, wherein the turbine engine further comprises another lubricated rolling bearing for taking up axial forces from the gas generator shaft, the another lubricated rolling bearing being arranged radially between the free turbine shaft and the gas generator shaft.

7. The assembly according to claim 6, wherein the turbine engine further comprises a sealing gasket arranged radially between the free turbine shaft and the gas generator shaft.

8. The assembly according to claim 7, wherein the sealing gasket is immediately adjacent to the another lubricated rolling bearing.

9. A helicopter comprising:

a rotor;

and

an assembly comprising a turbine engine and a main gearbox according to claim 1, the 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.

10. The helicopter according to claim 9, 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.

11. An assembly comprising:

a turbine engine and a main gearbox for a helicopter having a rotor, said main gearbox comprising a speed-reducing device including gearing and housed entirely within the main gearbox while also being connected to the rotor, the turbine engine, not having a speed reducer, 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 the casing of the turbine engine is fastened to the main gearbox,

wherein a sealing member is arranged between the main gearbox and the casing of the turbine engine,

wherein the free turbine shaft extends axially into the main gearbox to be connected directly to the speed-reducer device via a coupling sleeve provided on a free end of the free turbine shaft, the coupling sleeve being supported by a first lubricated rolling bearing, and the first lubricated rolling bearing cooperating with an axial abutment of the main gearbox,

wherein an axis of the free turbine shaft is perpendicular to an axis of the rotor, and

wherein the turbine engine further comprises a second lubricated rolling bearing for taking up axial forces from the gas generator shaft, the second lubricated rolling bearing being arranged radially between the free turbine shaft and the gas generator shaft, a sealing gasket being arranged radially between the free turbine shaft and the gas generator shaft.

12. The assembly according to claim 11, wherein the sealing gasket is immediately adjacent to the second lubricated rolling bearing.