BEARING SYSTEM FOR GAS TURBINE ENGINE

• US 20120189429A1
• Filed: 01/24/2011
• Published: 07/26/2012
• Est. Priority Date: 01/24/2011
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Witlicki, Russell B.
• Granted Patent: US 8,747,054 B2
• Time in Patent Office: Days
• US Class Current: 415/119
• CPC Class Codes: F01D 25/164 Flexible supports; Vibration damping means associated with the bearing
• 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: F16C 19/26 with a single row of rollers
• CPC Class Codes: F16C 2360/23 Gas turbine engines in general F02C
• CPC Class Codes: F16C 27/045 with a fluid film, e.g. squeeze film damping
• CPC Class Codes: Y10T 29/4932 Turbomachine making

Abstract

A bearing system for a gas turbine engine includes a spring defined about an axis of rotation. The spring has a multiple of beams which extend between a flange structure and an attachment structure. A damper defined about the axis of rotation and mounted to the spring to at least partially axially overlap the multiple of beams.

Claims

1. A bearing system for a gas turbine engine comprising:

a spring defined about an axis of rotation, said spring having a multiple of beams which extend between a flange structure and an attachment structure; and

a damper defined about said axis of rotation, said damper mounted to said spring to at least partially axially overlap said multiple of beams.

2. The bearing system as recited in claim 1, wherein said damper is mounted to an outer diameter of said spring.

3. The bearing system as recited in claim 2, wherein said damper is mounted to a damper interface adjacent to said attachment structure.

4. The bearing system as recited in claim 1, further comprising a fastener assembly mountable to said attachment structure to axially retain said damper to said spring.

5. The bearing system as recited in claim 1, further comprising a centering spring that extends radially inward from said attachment structure.

6. The bearing system as recited in claim 5, wherein said centering spring includes a cylindrical beam supported upon a radial web.

7. The bearing system as recited in claim 6, further comprising a bearing mountable to said cylindrical beam.

8. The bearing system as recited in claim 7, wherein a bearing element of said bearing is axially aligned with said damper.

9. A gas turbine engine comprising:

a static structure;

a rotor shaft defined about an axis of rotation;

a spring defined about said axis of rotation, said spring having a multiple of beams which extend between an attachment structure and a flange structure, a centering spring that extends radially inward from said attachment structure and said flange structure mounted to said static structure;

a damper defined about said axis of rotation, said damper mounted to said spring to at least partially axially overlap said multiple of beams; and

a bearing mounted to said centering spring and said rotor shaft to rotationally support said rotor shaft.

10. The gas turbine engine as recited in claim 9, further comprising a fastener assembly mounted to said attachment structure to axially retain said damper to said spring.

11. The gas turbine engine as recited in claim 9, wherein a bearing element of said bearing is axially aligned with said damper.

12. The gas turbine engine as recited in claim 11, wherein said static structure includes a static cylindrical beam supported upon a static radial web, said static radial web axially centered relative to said damper and said bearing element.

13. The gas turbine engine as recited in claim 9, wherein said static structure is a static bearing support and a mid-turbine frame static structure.

14. A method for assembling a rotor within static structure of a gas turbine engine comprising:

mounting a damper to a spring defined about an axis of rotation, the spring having a multiple of beams which extend between an attachment structure and a flange structure, the damper at least partially axially overlapping the multiple of beams;

mounting the flange to a static structure;

mounting the damper to the static structure;

rotationally supporting a rotor shaft about the axis of rotation within a bearing supported by the spring.

15. The method as recited in claim 14, further comprising:

axially retaining the damper to the spring with a fastener assembly.

16. The method as recited in claim 14, further comprising:

mounting the damper to a static cylindrical beam supported upon a static radial web, the static radial web axially centered relative to the damper and a bearing element of the bearing.