SUPPORT FOR ELECTRIC MACHINE IN A TURBINE ENGINE

• US 20130133336A1
• Filed: 11/28/2011
• Published: 05/30/2013
• Est. Priority Date: 11/28/2011
• Status: Active Grant

• 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: Barnett, Barry, Denis, David
• Granted Patent: US 9,003,811 B2
• Time in Patent Office: Days
• US Class Current: 60/802
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F01D 25/04 Antivibration arrangements
• CPC Class Codes: F01D 25/164 Flexible supports; Vibration damping means associated with the bearing
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49009 Dynamoelectric machine

Abstract

Devices and methods for supporting an accessory (32) in a gas turbine engine (10) are disclosed. The accessory (32) may have an interface (36) for coupling to a shaft (24) of the gas turbine engine (10). The device may comprise a first support (38) configured to support a first portion (34) of the accessory (32) proximal the interface (36) and a second support (40) configured to support a second portion (35) of the accessory (32) distal from the interface (36). The second support (40) may be configured to provide a lower resistance to relative displacement between the accessory (32) and structure (42) of the engine (10) than does the first support (34).

Claims

1. A device for supporting an electric machine in a gas turbine engine wherein the electric machine includes an interface for coupling to a shaft of the gas turbine engine, the device comprising:

a first support configured to secure the electric machine to a structure of the engine, the first support being configured to support a first portion of the machine proximal to the interface and substantially maintain positioning of the interface relative to the shaft; and

a second support configured to secure the electric machine to the structure of the engine, the second support being configured to support a second portion of the machine distal from the interface and to provide a lower resistance to relative displacement between the electric machine and the structure of the engine than does the first support.

2. The device as defined in claim 1, wherein the first support and the second support are configured to support the electric machine substantially coaxially with the shaft of the gas turbine engine.

3. The device as defined in claim 1, wherein the second support has a lower resistance to relative axial displacement between the electric machine and the structure of the engine than does the first support.

4. The device as defined in claim 1, wherein the second support comprises a plurality of substantially radially extending fingers securing the electric machine to the structure of the engine.

5. The device as defined in claim 1, wherein the second support comprises an annular member configured for attachment to the structure of the engine and a plurality of substantially radial fingers extending from the annular member, the fingers being configured for attachment to the electric machine.

6. The device as defined in claim 5, wherein the fingers are curved in an axial direction of the electric machine.

7. The device as defined in claim 5, wherein the fingers have at least a portion that is substantially C-shaped.

8. The device as defined in claim 1 wherein the second support supports a substantially mid portion of the electric machine.

9. The device as defined in claim 1, wherein the first support comprises a radially outer flange configured for attachment to the structure of the engine and a radially inner flange configured for attachment to the electric machine.

10. The device as defined in claim 9, wherein the first support includes at least a portion which is curved in an axial direction of the electric machine.

11. A gas turbine engine comprising:

a high pressure spool and a cooperating low pressure spool;

an accessory mounted substantially coaxially with the low pressure spool, the accessory having an interface for coupling with the low pressure spool;

a first support securing the accessory to a structure of the engine, the first support supporting a first portion of the accessory proximal to the interface and substantially maintaining alignment between the interface and the low pressure spool; and

a second support securing the accessory to the structure of the engine, the second support supporting a second portion of the accessory distal from the interface, the second support providing a lower resistance to relative displacement between the electric machine and the structure of the engine than does the first support.

12. The gas turbine engine as defined in claim 11, wherein the accessory is mounted in a tail portion of the engine.

13. The gas turbine engine as defined in claim 11, wherein the second support has a lower resistance to relative axial displacement between the accessory and the structure of the engine than does the first support.

14. The gas turbine engine as defined in claim 11, wherein the second support comprises an annular member configured for attachment to the structure of the engine and a plurality of substantially radial fingers extending from the annular member, the fingers being configured for attachment to the accessory.

15. The gas turbine engine as defined in claim 11, wherein the first support comprises a radially outer flange configured for attachment to the structure of the engine and a radially inner flange configured for attachment to the accessory.

16. A method for supporting an electric machine in a gas turbine engine, wherein the electric machine has an interface for coupling to a shaft of a gas turbine engine, the method comprising:

supporting a first portion of the electric machine proximal to the interface to substantially maintain positioning of the interface relative to the shaft;

supporting a second portion of the electric machine distal from the interface; and

providing a lower resistance to relative displacement between the second portion of the electric machine and the structure of the engine than between the first portion of the electric machine and the structure of the engine.

17. The method as defined in claim 16, wherein the resistance to relative displacement includes a resistance to axial displacement.

18. The method as defined in claim 17, wherein the electric machine is supported substantially coaxially with a low pressure shaft of the gas turbine engine.

19. The method as defined in claim 16, wherein the second portion of the electrical machine distal from the interface comprises a substantially mid portion of the electric machine.

20. The method as defined in claim 16, comprising supporting a majority of the weight of the electric machine at the forward portion of the electric machine.