Offset drive for gas turbine engine

• US 6,735,954 B2
• Filed: 12/21/2001
• Issued: 05/18/2004
• Est. Priority Date: 12/21/2001
• Status: Expired due to Term

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Morgan, Keith Martin, Szlanta, Zenon, MacFarlane, Ian Alexander, Mitrovic, Lazar
• Primary Examiner(s): Gartenberg, Ehud
• Application Number:
  US10/026,844
• Publication Number:
  US 20030115885A1
• Time in Patent Office: 879 Days
• Field of Search: 607/93, 74D/IG.5
• US Class Current: 60/793
• CPC Class Codes: F02C 6/206 the vehicles being airscrew driven
• 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: F02K 3/068 being characterised by a short axial length relative to the diameter
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine including a gas generator module and a reduction gearbox module. The gas generator module has an axis which extends longitudinally along a centreline of the gas generator module, and the reduction gearbox module has an axis which extending longitudinally along the centreline of the reduction gearbox and is offset from said generator axis. The reduction gearbox is driven by an intermediate shaft angled relative to the turbine output shaft.

Claims

1. A gas turbine engine comprising:

a gas generator module having a turbine shaft for providing rotating output power; and

a reduction gearbox module having a gearbox input shaft and a main output power shaft, wherein the gearbox input shaft is drivingly connected to an intermediate drive shaft, the intermediate drive shaft being drivingly connected to the turbine shaft, and wherein the intermediate drive shaft is disposed at an angle to the turbine shaft.

2. The gas turbine engine as defined in claim 1, wherein the main output power shaft is laterally offset from the turbine shaft.

3. The gas turbine engine as defined in claim 1, wherein the gas generator module has an inlet air path, and wherein the inlet air path is substantially straight and substantially unobstructed by the reduction gearbox module.

4. The gas turbine engine as defined in claim 1, wherein the gas generator module has an inlet air path, and wherein the inlet air path is substantially parallel to a longitudinal axis of the gas generator module.

5. The gas turbine engine as defined in claim 1, wherein the turbine shaft and the gearbox input shaft are substantially parallel.

6. The gas turbine engine as defined in claim 1, wherein the turbine shaft includes a bevel gear adapted to rotatingly drive the intermediate shaft.

7. The gas turbine engine as defined in claim 1, wherein the reduction gearbox module has shaft speed reduction means operatively interposed between the gearbox input shaft and the main output power shaft.

8. The gas turbine engine as defined in claim 1, wherein the intermediate drive shaft extends generally perpendicularly to the turbine shaft.

9. The gas turbine engine as defined in claim 1, wherein main output power shaft is adapted to permit a propeller to be mounted thereto.

16. The gas turbine engine as defined in claim 1, wherein the reduction gearbox module is adapted to permit a propeller to be mounted thereto.

10. A gas turbine engine comprising:

a gas generator module, the gas generator module including a compressor portion, a combustor portion, and a turbine portion; and

a reduction gearbox module adapted to drivingly connect the gas generator module to an output power shaft, the reduction gearbox module being disposed substantially laterally beside the gas generator module.

11. The gas turbine engine as defined in claim 10, wherein the gas generator module and the reduction gearbox module are drivingly connected by an intermediate shaft, and wherein the intermediate shaft is disposed at an angle to a longitudinal axis of the gas generator.

12. The gas turbine engine as defined in claim 11, wherein the intermediate shaft is drivingly connected by a bevel gear set to a turbine shaft of the turbine module.

13. The gas turbine engine as defined in claim 11, wherein the intermediate drive shaft extends generally perpendicularly to the turbine shaft.

14. The gas turbine engine as defined in claim 10, wherein the gas generator module has an inlet air path, and wherein the inlet air path is substantially straight and substantially unobstructed by the reduction gearbox module.

15. The gas turbine engine as defined in claim 10, wherein the gas generator module has an inlet air path, and wherein the inlet air path is substantially parallel to a longitudinal axis of the gas generator module.

17. A gas turbine engine comprising:

a gas generator module having an turbine shaft for providing rotating output power; and

a reduction gearbox module adapted to drivingly connect the gas generator module to an output shaft,

wherein the reduction gearbox module has an input shaft which is drivingly connected to an output turbine shaft of the gas generator module through a bevel gear on the turbine shaft.

18. The gas turbine engine as defined in claim 17, wherein an intermediate shaft is operatively interposed between the reduction gearbox module input shaft and the turbine shaft bevel gear.

19. The gas turbine engine as defined in claim 18, wherein the intermediate shaft is disposed at an angle to the turbine shaft.

20. The gas turbine engine as defined in claim 18, wherein the gas generator module has front portion which is substantially aligned with a front portion of the reduction gearbox module.