Systems and methods involving multiple torque paths for gas turbine engines

• US 8,621,871 B2
• Filed: 05/08/2012
• Issued: 01/07/2014
• Est. Priority Date: 10/09/2007
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: McCune, Michael E., Merry, Brian D., Suciu, Gabriel L.
• Primary Examiner(s): SUNG, GERALD LUTHER
• Application Number:
  US13/466,745
• Publication Number:
  US 20120216548A1
• Time in Patent Office: 609 Days
• Field of Search: 607/79, 60/390.91, 602/261, 60/391.62, 60/391.63, 602/68, 602/55, 602/04, 415/122.1, 415/61, 415 68- 69, 416128-129
• US Class Current: 60/779
• CPC Class Codes: F01D 21/02 Shutting-down responsive to overspeed
• CPC Class Codes: F01D 21/04 responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
• CPC Class Codes: F01D 25/16 Arrangement of bearings; Supporting or mounting bearings in casings bearings per se F16C
• CPC Class Codes: F02C 3/107 with two or more rotors connected by power transmission
• 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 2270/091 in particular sudden load loss

Abstract

Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative method for reducing overspeed potential of a turbine of a gas turbine engine includes: providing a first load to the turbine via a first torque path; providing a second load to the turbine via a second torque path; and operating the turbine such that: mechanical failure of a component defining at least a portion of the first torque path does not inhibit the second load from being applied to the turbine via the second torque path; and mechanical failure of a component defining the second torque path does not inhibit the first load from being applied to the turbine via the first torque path.

Claims

1. A method for reducing overspeed potential of a turbine of a gas turbine engine, comprising:

providing a first load associated with a compressor to the turbine via a first torque path and a shaft;

providing a second load to the turbine via a second torque path and the shaft; and

operating the turbine such that;

mechanical failure of a component defining at least a portion of the first torque path does not inhibit the second load from being applied to the turbine via the second torque path and the shaft; and

mechanical failure of a component defining the second torque path does not inhibit the first load from being applied to the turbine via the first torque path and the shaft;

wherein the shaft is supported by a thrust bearing that is connected to an intersection between the first torque path and the shaft, and wherein the thrust bearing comprises a tapered roller bearing and is located aft of the first torque path.

2. The method of claim 1, wherein, in providing the second load, the second load is associated with a gear-driven fan.

3. The method of claim 1, further comprising enabling portions of the turbine driven by the shaft to move aft and contact vanes of the turbine responsive to mechanical failure of the shaft aft of the thrust bearing.

4. The method of claim 1, further comprising inhibiting aft movement of the shaft via the thrust bearing.

5. The method of claim 1, wherein the first torque path includes a first spool segment that is mechanically connected to the shaft.

6. The method of claim 1, wherein the second torque path includes a second spool segment that is mechanically connected to the shaft.

7. The method of claim 1, wherein the thrust bearing is located aft of the second torque path.

8. A turbine engine, comprising:

a compressor;

a gear assembly;

a turbine;

a shaft coupled to the turbine;

a thrust bearing supporting the shaft, and comprising a tapered roller bearing;

a first spool segment coupling the compressor to the shaft; and

a second spool segment coupling the gear assembly to the shaft;

wherein the first and the second spool segments are each mechanically connected to the shaft at an intersection, and the thrust bearing is located aft of the first spool segment at the intersection between the shaft and the spool segments.

9. The engine of claim 8, wherein the intersection is located at an end of the shaft.

10. The engine of claim 8, wherein the shaft is operative to drive the compressor through the first spool segment independent of the second spool segment, and the shaft is operative to drive the gear assembly through the second spool segment independent of the first spool segment.

11. The engine of claim 8, wherein the gear assembly couples the second spool segment to a fan.

12. The engine of claim 8, further comprising:

a casing annularly surrounding the turbine; and

an electronic engine control operative to receive inputs corresponding to engine operating parameters and to provide outputs to control operation of the engine, the electronic engine control being further operative to configure the outputs to reduce rotational speed of the turbine responsive to a failure of at least one of the first spool segment and the second spool segment such that a portion of the turbine does not penetrate the casing.

16. The engine of claim 8, wherein the first spool segment diverges from the second spool segment and the shaft as the first spool segment extends in a forward direction away from the intersection.

13. A turbine engine, comprising:

a compressor;

a fan;

a turbine;

a shaft coupled to the turbine;

a thrust bearing supporting the shaft, and comprising a tapered roller bearing;

a first spool segment coupling the compressor to the shaft; and

a second spool segment coupling the fan to the shaft;

wherein the first and the second spool segments are each mechanically connected to the shaft at an intersection, and the thrust bearing is located aft of the first spool segment at the intersection between the shaft and the spool segments.

14. The engine of claim 13, wherein the intersection is located at an end of the shaft.

15. The assembly of claim 13, wherein the shaft is operative to drive the compressor through the first spool segment independent of the second spool segment, and the shaft is operative to drive the fan through the second spool segment independent of the first spool segment.