Rotor support system having a shape memory alloy

Patent metadata

Field	Value
Publication number	US-10634007-B2
Application number	US-201715811169-A
Country	US
Kind code	B2
Filing date	Nov 13, 2017
Priority date	Nov 13, 2017
Publication date	Apr 28, 2020
Grant date	Apr 28, 2020

Abstract

A rotor support system for a gas turbine engine is disclosed. The rotor support system includes a bearing support flange, a frame support flange proximate to the bearing support flange, a fastener between the bearing support flange and the frame support flange, a damping component, and an axial retainer. The damping component includes a super-elastic shape memory alloy. The fastener is configured to fail when a load on the fastener exceeds a threshold value and the damping component is configured to deform from a normal state to a deformed state after the fastener fails. The axial retainer is configured to retain the bearing support flange and the frame support flange within an axial displacement from each other after the fastener fails. A radial gap exists between the bearing support flange and the frame support flange when the damping component is in the normal state.

First claim

The invention claimed is:

1. A rotor support system for a gas turbine engine, the rotor support system comprising:
a bearing support flange;
a frame support flange proximate to the bearing support flange;
a fastener between the bearing support flange and the frame support flange, the fastener configured to fail when a load on the fastener exceeds a threshold value;
a damping component comprising a super-elastic shape memory alloy, wherein the damping component is in contact with at least one of the bearing support flange or the frame support flange, and configured to deform from a normal state to a deformed state after the fastener fails; and
an axial retainer, the axial retainer configured to retain the bearing support flange and the frame support flange within an axial displacement from each other after the fastener fails,
wherein a radial gap exists between the bearing support flange and the frame support flange when the damping component is in the normal state, the radial gap being greater when the damping component is in the normal state than when the damping component is in the deformed state.

2. The rotor support system of claim 1 , wherein the damping component in the normal state provides a higher stiffness than the damping component in the deformed state.

3. The rotor support system of claim 1 , wherein the bearing support flange is in radial contact with the frame support flange when the damping component is in the deformed state.

4. The rotor support system of claim 1 , wherein the bearing support flange is a bearing housing flange, and the frame support flange is a forward mounting flange of a bearing cone.

5. The rotor support system of claim 1 , wherein the bearing support flange is an aft mounting flange of a bearing cone, and the frame support flange is a frame housing flange.

6. The rotor support system of claim 1 , wherein the fastener between the bearing support flange and the frame support flange is an axial, fusible fastener.

7. The rotor support system of claim 1 , wherein the damping component is in contact with the frame support flange and disposed between the bearing support flange and the frame support flange.

8. The rotor support system of claim 1 , wherein at least a portion of the damping component is disposed within a body of the bearing support flange.

9. The rotor support system of claim 1 , further comprising a circumferential gap between the bearing support flange and the frame support flange.

10. The rotor support system of claim 1 , wherein at least a portion of the damping component is in the form of a honeycomb structure.

11. The rotor support system of claim 1 , wherein the damping component is in the form of a circumferential ring.

12. The rotor support system of claim 1 , wherein the damping component is in the form of a plurality of radial struts, a plurality of solid blocks, a plurality of springs, or a plurality of corrugated plates.

13. The rotor support system of claim 1 , wherein the axial retainer is a retainer bolt, a retainer flange, a retainer block, or combinations thereof.

14. The rotor support system of claim 1 , wherein the bearing support flange is an inner bearing cone flange, and the frame support flange is an outer bearing cone flange.

15. A rotor support system for a gas turbine engine, the rotor support system comprising:
a bearing support flange;
a frame support flange proximate to the bearing support flange;
a shear bolt fastening the bearing support flange and the frame support flange, the shear bolt configured to fail when a load on the shear bolt exceeds a threshold value;
a damping component comprising a super-elastic shape memory alloy, wherein the damping component is in contact with at least one of the bearing support flange or the frame support flange, and configured to deform from a normal state to a deformed state after the shear bolt fails; and
an axial retainer bolt fastened to the frame support flange, the retainer bolt configured to retain the bearing support flange and the frame support flange within an axial displacement from each other after the shear bolt fails,
wherein a radial gap and a circumferential gap exist between the bearing support flange and the frame support flange when the damping component is in the normal state.

16. The rotor support system of claim 15 , wherein the shear bolt is an axial fusible shear bolt, configured to fail when a load on the shear bolt exceeds a threshold value.

17. The rotor support system of claim 15 , wherein the damping component is in contact with the frame support flange, and is disposed between the bearing support flange and the frame support flange.

18. The rotor support system of claim 15 , wherein the damping component is in the form of a circumferential ring.

19. The rotor support system of claim 15 , wherein the damping component is in the form of a plurality of radial struts, a plurality of solid blocks, a plurality of springs, or a plurality of corrugated plates.

20. The rotor support system of claim 15 , wherein at least a portion of the damping component is in the form of a honeycomb structure.

21. A rotor support system for a gas turbine engine, the rotor support system comprising:
a bearing support flange;
a frame support flange proximate to the bearing support flange;
a fastener between the bearing support flange and the frame support flange, the fastener configured to fail when a load on the fastener exceeds a threshold value;
a damping component comprising a super-elastic shape memory alloy, wherein the damping component is in contact with at least one of the bearing support flange or the frame support flange, and configured to deform from a normal state to a deformed state after the fastener fails; and
an axial retainer, the axial retainer configured to retain the bearing support flange and the frame support flange within an axial displacement from each other after the fastener fails,
wherein a radial gap exists between the bearing support flange and the frame support flange when the damping component is in the normal state,
wherein the damping component is in contact with the frame support flange and disposed between the bearing support flange and the frame support flange.

Assignees

• Gen Electric

Inventors

• Ghosh Shuvajyoti
• Ganiger Ravindra Shankar
• Sharma Praveen
• Sehgal Ishita
• Bhujabal Prashant
• Mittal Shivam

Classifications

• F05D2240/20

  Rotors · CPC title

• F05D2250/283

  honeycomb · CPC title

• F16C19/06

  with a single row or balls · CPC title

• F01D21/045

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• F16C35/063

  Fixing them on the shaft (with interposition of an element F16C35/07) · CPC title