Bearing assembly with load isolation for gas turbine engine

Patent metadata

Field	Value
Publication number	US-12416329-B2
Application number	US-202318463740-A
Country	US
Kind code	B2
Filing date	Sep 8, 2023
Priority date	Mar 10, 2023
Publication date	Sep 16, 2025
Grant date	Sep 16, 2025

Abstract

A bearing assembly includes an inner race to receive a rotating component having an axis of rotation, and at least one bearing element coupled to the inner race. The at least one bearing element is to rotate with the inner race along the axis of rotation. The bearing assembly includes an outer race coupled to the at least one bearing element, and a bearing housing coupled to the outer race and to be coupled to a static structure. The bearing housing includes a first frangible portion to release upon receipt of a moment load greater than a moment threshold and a second frangible portion to release upon receipt of a radial load greater than a radial threshold.

First claim

What is claimed is:

1. A bearing assembly, comprising:
an inner race configured to receive a rotating component having an axis of rotation;
at least one bearing element coupled to the inner race, the at least one bearing element configured to rotate with the inner race along the axis of rotation;
an outer race coupled to the at least one bearing element; and
a bearing housing coupled to the outer race and configured to be coupled to a static structure, the bearing housing including a first frangible portion configured to release upon receipt of a moment load greater than a moment threshold and a second frangible portion configured to release upon receipt of a radial load greater than a radial threshold.

2. The bearing assembly of claim 1 , wherein the first frangible portion is defined on the bearing housing along an axis substantially perpendicular to the axis of rotation.

3. The bearing assembly of claim 1 , wherein the second frangible portion is defined on the bearing housing along an axis substantially parallel to the axis of rotation.

4. The bearing assembly of claim 1 , wherein the first frangible portion includes at least one first groove that defines a reduced thickness.

5. The bearing assembly of claim 4 , wherein the second frangible portion includes at least one second groove that defines a second reduced thickness.

6. The bearing assembly of claim 4 , wherein the at least one first groove is continuous about a perimeter of the first frangible portion.

7. The bearing assembly of claim 4 , wherein the at least one first groove comprises a pair of opposed grooves that cooperate to define the reduced thickness.

8. The bearing assembly of claim 1 , wherein the first frangible portion includes a plurality of first slots spaced apart about a perimeter of the first frangible portion.

9. The bearing assembly of claim 8 , wherein the second frangible portion includes a plurality of second slots spaced apart about a second perimeter of the second frangible portion.

10. The bearing assembly of claim 9 , wherein each second slot extends along a major axis, and the major axis is substantially parallel to the axis of rotation.

11. The bearing assembly of claim 8 , wherein each first slot extends along a major axis, and the major axis is substantially perpendicular to the axis of rotation.

12. The bearing assembly of claim 1 , wherein the bearing housing includes a first coupling section to be coupled to the outer race, a second coupling section configured to be coupled to the static structure, and the first frangible portion and the second frangible portion are defined between the first coupling section and the second coupling section.

13. The bearing assembly of claim 12 , wherein the first frangible portion extends radially outward from the first coupling section, and the second frangible portion extends axially from the first frangible portion relative to the axis of rotation.

14. The bearing assembly of claim 13 , wherein the second frangible portion is coupled to a first end of the second coupling section, and the second coupling section defines a flange at a second end, with the second end opposite the first end.

15. The bearing assembly of claim 1 , wherein the rotating component is a shaft associated with a gas turbine engine.

16. A bearing assembly for a gas turbine engine, comprising:
an inner race configured to receive a rotating component having an axis of rotation;
at least one bearing element coupled to the inner race, the at least one bearing element configured to rotate with the inner race along the axis of rotation;
an outer race coupled to the at least one bearing element; and
a bearing housing coupled to the outer race and configured to be coupled to a static structure, the bearing housing including a first frangible portion and a second frangible portion, the first frangible portion extending along a first axis substantially perpendicular to the axis of rotation, the first frangible portion configured to release upon receipt of a moment load greater than a moment threshold, the second frangible portion extending along a second axis substantially parallel to the axis of rotation and the second frangible portion is configured to release upon receipt of a radial load greater than a radial threshold.

17. The bearing assembly of claim 16 , wherein the first frangible portion includes a pair of opposed grooves that cooperate to define a reduced thickness and each groove of the pair of opposed grooves is continuous about a perimeter of the first frangible portion.

18. The bearing assembly of claim 16 , wherein the first frangible portion includes a plurality of first slots spaced apart about a perimeter of the first frangible portion and the second frangible portion includes a plurality of second slots spaced apart about a second perimeter of the second frangible portion.

19. The bearing assembly of claim 18 , wherein each second slot extends along a major axis, the major axis is substantially parallel to the axis of rotation.

20. The bearing assembly of claim 18 , wherein each first slot extends along a major axis, and the major axis is substantially perpendicular to the axis of rotation.

Assignees

• Honeywell Int Inc

Inventors

• Devadoss Gnanaraj
• Kumar Avinash
• Thampi Akhil

Classifications

• F16C35/077

  between housing and outer race ring · CPC title

• F01D25/162

  Bearing supports · CPC title

• F16C2360/23

  Gas turbine engines · CPC title

• F05D2240/50

  Bearings · CPC title

• F16C33/585

  of raceways, e.g. ribs to guide the rollers · CPC title