Unified curved beam bearing damper

Patent metadata

Field	Value
Publication number	US-11035252-B2
Application number	US-201916668684-A
Country	US
Kind code	B2
Filing date	Oct 30, 2019
Priority date	Oct 30, 2019
Publication date	Jun 15, 2021
Grant date	Jun 15, 2021

Abstract

A gas turbine engine component includes a ring comprising a single-piece component having an outer peripheral surface and an inner peripheral surface that surrounds an engine center axis, a plurality of outer diameter pedestals formed in the outer peripheral surface and circumferentially spaced apart from each other, and a plurality of inner diameter pedestals formed in the inner peripheral surface and circumferentially spaced apart from each other. A plurality of recesses are formed in the outer peripheral surface and are circumferentially spaced apart from each other.

First claim

The invention claimed is:

1. A gas turbine engine component comprising:
a ring comprising a single-piece component having an outer peripheral surface and an inner peripheral surface that surrounds an engine center axis;
a plurality of outer diameter pedestals formed in the outer peripheral surface and circumferentially spaced apart from each other;
a plurality of inner diameter pedestals formed in the inner peripheral surface and circumferentially spaced apart from each other; and
a plurality of recesses formed in the outer peripheral surface and circumferentially spaced apart from each other.

2. The gas turbine engine component according to claim 1 , wherein the plurality of recesses alternate with the plurality of outer diameter pedestals circumferentially about the engine center axis.

3. The gas turbine engine component according to claim 1 , wherein the plurality of outer diameter pedestals are circumferentially offset from the plurality of inner diameter pedestals.

4. The gas turbine engine component according to claim 3 , wherein each inner diameter pedestal is radially aligned with a corresponding one of the plurality of recesses.

5. The gas turbine engine component according to claim 1 , wherein the ring has an axial width that extends from an upstream end to a downstream end, and including a first groove formed in the outer peripheral surface at the upstream end and a second groove formed in the outer peripheral surface at the downstream end.

6. The gas turbine engine component according to claim 5 , including a first seal or piston ring in the first groove and a second seal or piston ring in the second groove.

7. The gas turbine engine component according to claim 1 , wherein the ring has a radial thickness extending from the inner peripheral surface to the outer peripheral surface, and wherein the radial thickness varies circumferentially about the engine center axis.

8. The gas turbine engine component according to claim 7 , wherein the radial thickness at the plurality of recesses is less than the radial thickness at the outer diameter pedestals.

9. The gas turbine engine component according to claim 1 , wherein
each recess is defined by a recess circumferential length and a recess axial width,
each outer diameter pedestal is defined by an OD circumferential length and an OD axial width,
each inner diameter pedestal is defined by an ID circumferential length and an ID axial width, and
wherein the recess circumferential length is greater than the OD circumferential length.

10. The gas turbine engine component according to claim 9 , wherein the OD axial width is the same as the recess axial width.

11. The gas turbine engine component according to claim 9 , wherein the ID axial width is greater than the OD axial width.

12. The gas turbine engine component according to claim 9 , wherein the recess circumferential length is greater than the ID circumferential length.

13. The gas turbine engine component according to claim 1 , wherein the plurality of outer diameter pedestals have a static structure abutment surface, and wherein the plurality of inner diameter pedestals have a bearing race abutment surface, and wherein the plurality of recesses are configured to receive a fluid.

14. A gas turbine engine comprising:
an engine static structure;
at least one bearing supporting an engine shaft for rotation relative to the engine static structure; and
a unified curved beam bearing damper positioned radially between the engine static structure and the at least one bearing, the unified curved beam bearing damper comprising a ring that is a single-piece component having an outer peripheral surface and an inner peripheral surface that surrounds an engine center axis, a plurality of outer diameter pedestals formed in the outer peripheral surface and circumferentially spaced apart from each other, a plurality of inner diameter pedestals formed in the inner peripheral surface and circumferentially spaced apart from each other, and a plurality of fluid recesses formed in the outer peripheral surface and circumferentially spaced apart from each other.

15. The gas turbine engine according to claim 14 , wherein the plurality of fluid recesses alternate with the plurality of outer diameter pedestals circumferentially about the engine center axis.

16. The gas turbine engine according to claim 14 , wherein the plurality of outer diameter pedestals are circumferentially offset from the plurality of inner diameter pedestals.

17. The gas turbine engine according to claim 14 , wherein each inner diameter pedestal is radially aligned with a corresponding one of the plurality of fluid recesses.

18. The gas turbine engine according to claim 14 , wherein the ring has an axial width that extends from an upstream end to a downstream end, and including a first groove formed in the outer peripheral surface at the upstream end, a second groove formed in the outer peripheral surface at the downstream end, a first seal or piston ring in the first groove and a second seal or piston ring in the second groove.

19. The gas turbine engine according to claim 14 , wherein the ring has a radial thickness extending from the inner peripheral surface to the outer peripheral surface, and wherein the radial thickness varies circumferentially about the engine center axis, and wherein the radial thickness at the plurality of fluid recesses is less than the radial thickness at the outer diameter pedestals.

20. The gas turbine engine according to claim 14 , wherein
each fluid recess is defined by a recess circumferential length and a recess axial width,
each outer diameter pedestal is defined by an OD circumferential length and an OD axial width,
each inner diameter pedestal is defined by an ID circumferential length and an ID axial width, and wherein
the recess circumferential length is greater than the OD circumferential length,
the OD axial width is the same as the recess axial width,
the ID axial width is greater than the OD axial width, and/or
the recess circumferential length is greater than the ID circumferential length.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Davis Todd A
• Witlicki Russell B
• Valva Christopher M
• Newton Andrew
• Kiely David C

Classifications

• F16C19/00

  Bearings with rolling contact, for exclusively rotary movement (adjustable bearings F16C23/00, F16C25/00 {; electrically insulating bearings H02K5/173}) · CPC title

• F16C27/045

  with a fluid film, e.g. squeeze film damping · CPC title

• F05D2240/54

  Radial bearings · CPC title

• F05D2250/29

  machined; miscellaneous · CPC title

• F05D2250/294

  grooved · CPC title