Curved beam centering spring for a thrust bearing

Patent metadata

Field	Value
Publication number	US-11118629-B2
Application number	US-201916710667-A
Country	US
Kind code	B2
Filing date	Dec 11, 2019
Priority date	Dec 11, 2019
Publication date	Sep 14, 2021
Grant date	Sep 14, 2021

Abstract

A gas turbine engine component includes a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race, and a bearing housing spaced radially outwardly of the outer race. A curved beam centering spring is positioned between the outer race and the bearing housing. A cylindrical wall is radially outward of the bearing housing and engages the outer race and the bearing housing.

First claim

The invention claimed is:

1. A gas turbine engine component comprising:
a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race;
a bearing housing spaced radially outwardly of the outer race;
a curved beam centering spring positioned between the outer race and the bearing housing;
a fluid damper spaced radially inward of the bearing housing and radially outward of the outer race;
a cylindrical wall radially outward of the bearing housing, wherein the cylindrical wall engages the outer race and the bearing housing, and wherein the cylindrical wall includes a first mounting flange that is connected to the outer race and a second mounting flange that is connected to the bearing housing; and
at least one fluid inlet extending through the bearing housing at a location that is between the first mounting flange and the second mounting flange.

2. The gas turbine engine component according to claim 1 , wherein the first mounting flange is formed at one end of the cylindrical wall and the second mounting flange is formed at an opposite end of the cylindrical wall.

3. The gas turbine engine component according to claim 2 , wherein the first mounting flange extends radially inward and the second mounting flange extends radially outward.

4. The gas turbine engine component according to claim 1 , wherein the outer race includes a bearing flange and wherein the bearing housing includes a housing flange, and wherein the first mounting flange is directly connected to the bearing flange and the second mounting flange is directly connected to the housing flange such that the cylindrical wall is rigid in an axial direction and compliant in a radial direction, and such that the curved beam centering spring is only subject to forces in the radial direction.

5. The gas turbine engine component according to claim 1 , wherein the curved beam centering spring is comprised of a plurality of curved beam segments.

6. The gas turbine engine component according to claim 1 , wherein the curved beam centering spring is a single-piece solid ring curved beam.

7. The gas turbine engine component according to claim 1 , including a cross-over housing that is radially outward of the cylindrical wall and which includes a cross-over housing flange, and wherein the bearing housing includes a bearing housing flange, and wherein the second mounting flange of the cylindrical wall, the bearing housing flange, and the cross-over housing flange are all connected to an intermediate case flange via at least one common fastener.

8. The gas turbine engine component according to claim 7 , wherein the intermediate case flange is sandwiched directly between the housing flange and the second mounting flange.

9. A gas turbine engine component comprising:
a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race;
a bearing housing spaced radially outwardly of the outer race;
a curved beam centering spring positioned between the outer race and the bearing housing;
a cylindrical wall radially outward of the bearing housing, wherein the cylindrical wall engages the outer race and the bearing housing, and wherein the cylindrical wall includes a first mounting flange that is connected to the outer race and a second mounting flange that is connected to the bearing housing;
wherein the outer race includes a bearing flange and wherein the bearing housing includes a housing flange, and wherein the first mounting flange is directly connected to the bearing flange and the second mounting flange is directly connected to the housing flange such that the cylindrical wall is rigid in an axial direction and compliant in a radial direction, and such that the curved beam centering spring is only subject to forces in the radial direction; and
wherein the bearing housing includes an outer housing wall extending circumferentially about the axis, a radial wall extending outwardly of the outer housing wall, and a shoulder portion that transitions from the radial wall to the bearing flange that extends in a radially outward direction, and wherein the radial wall includes an axially extending lip that seats a radially inner surface of the second mounting flange.

10. A gas turbine engine component comprising:
a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race;
a bearing housing spaced radially outwardly of the outer race;
a curved beam centering spring positioned between the outer race and the bearing housing;
a cylindrical wall radially outward of the bearing housing, wherein the cylindrical wall engages the outer race and the bearing housing, wherein the cylindrical wall includes a first mounting flange that is connected to the outer race and a second mounting flange that is connected to the bearing housing;
wherein the outer race includes a bearing flange and wherein the bearing housing includes a housing flange, and wherein the first mounting flange is directly connected to the bearing flange and the second mounting flange is directly connected to the housing flange such that the cylindrical wall is rigid in an axial direction and compliant in a radial direction, and such that the curved beam centering spring is only subject to forces in the radial direction; and
a static structure comprising a cross-over housing that is radially outward of the cylindrical wall, and wherein the housing flange and second mounting flange are connected to a mount flange of the cross-over housing with at least one fastener.

11. A gas turbine engine component comprising:
a bearing configured to support a shaft for rotation about an axis, wherein the bearing includes an outer race and an inner race;
a bearing housing spaced radially outwardly of the outer race;
a curved beam centering spring positioned between the outer race and the bearing housing;
a fluid damper between the bearing housing and the curved beam centering spring;
a cylindrical wall radially outward of the bearing housing, wherein the cylindrical wall engages the outer race and the bearing housing, wherein the cylindrical wall includes a first mounting flange that is connected to the outer race and a second mounting flange that is connected to the bearing housing; and
at least one fluid inlet extending through the bearing housing at a location that is axially between the first mounting flange and the second mounting flange.

12. The gas turbine engine component according to claim 11 , wherein the inner race is fixed for rotation with the shaft and the outer race is fixed to a static engine structure, and wherein the bearing housing surrounds the curved beam centering spring to form at least one fluid damping chamber between an inner surface of the bearing housing and an outer surface of the curved beam centering spring that is sealed by one or more piston rings or o-rings to provide the fluid damper as a squeeze film damper.

13. The gas turbine engine component according to claim 12 , wherein the curved beam centering spring is comprised of a plurality of curved beam segments.

14. The gas turbine engine component according to claim 12 , wherein the curved beam centering spring is a single-piece solid ring curved beam.

15. The gas turbine engine component according to claim 11 , wherein the first mounting flange is formed at one end of the cylindrical wall and the second mounting flange is formed at an opposite end of the cylindrical wall.

16. The gas turbine engine component according to claim 15

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

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

Classifications

• F05D2250/71

  curved · CPC title

• F16C35/063 Primary

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

• F05D2240/52

  Axial thrust bearings · CPC title

• F16C27/045 Primary

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

• F16C33/581

  integral with other parts, e.g. with housings or machine elements such as shafts or gear wheels · CPC title