Gas turbine engine and foil bearing system

Patent metadata

Field	Value
Publication number	US-9689277-B2
Application number	US-201614997039-A
Country	US
Kind code	B2
Filing date	Jan 15, 2016
Priority date	Dec 29, 2009
Publication date	Jun 27, 2017
Grant date	Jun 27, 2017

Abstract

A gas turbine engine including a compressor, a turbine and a static structure is disclosed herein. The gas turbine engine further includes a foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure. The foil bearing system includes a foil bearing and a self-aligning foil bearing mount to align the foil bearing with an axis of rotation of the compressor and the turbine. A snubber operative to transmit rotor loads to the static structure in parallel with the foil bearing is also disclosed.

First claim

What is claimed is:

1. In a foil bearing system for transmitting rotor loads from a rotor to a static structure having:
a foil bearing surrounding a rotatable shaft;
a housing surrounding the foil bearing; and
a bearing mount affixed to the static structure and surrounding the housing,
a method of self-aligning the foil bearing with the axis of rotation of the shaft comprising:
providing a crown extending radially outward having a convex surface circumferentially disposed about a portion of the housing;
providing a receiver having a concave surface circumferentially disposed about a portion of the bearing mount; and
slideably mating the convex surface of the crown with a concave surface of the bearing mount to thereby permit rotation of the housing about an axis that is perpendicular to the axis of rotation of the shaft.

2. The method of claim 1 wherein the rotor is at least one of a compressor rotor or a turbine rotor.

3. The method of claim 1 wherein the convex surface of the crown is spherical in axial cross-section.

4. The method of claim 3 wherein the foil bearing is preloaded against the shaft.

5. The method of claim 4 wherein the crown is integral with the housing.

6. The method of claim 5 wherein said receiver is split.

7. A foil bearing system for a turbine engine comprising:
at least one foil bearing and a housing disposed between a rotor of the turbine engine and a static structure of the turbine engine, said housing having a convex crown circumferentially disposed about an axis of rotation of said rotor,
a bearing mount affixed to said static structure, said bearing mount having a concave receiver,
wherein said convex crown is slideably mated with said concave receiver to thereby permit rotation of said housing about an axis that is perpendicular to the axis of rotation of said rotor to thereby self-align said foil bearing to the axis of rotation of said rotor.

8. The system of claim 7 wherein said convex crown and said concave receiver comprise spherical surfaces in axial cross-section.

9. The system of claim 7 wherein a radially-outward surface of said convex crown has a friction reducing coating.

10. The system of claim 7 wherein said at least one foil bearing comprises a bump foil and a top foil.

11. The system of claim 10 wherein said top foil is preloaded against said rotor.

12. The system of claim 7 wherein said housing is adapted to rotate about an axis that is perpendicular to the axis of rotation of said rotor to thereby effect self-alignment of said convex crown to said concave receiver.

13. The system of claim 8 wherein the convex crown is formed separately from and affixed to the housing.

14. A system comprising:
a rotor;
a static structure;
a foil bearing circumferentially disposed about said rotor;
a housing circumferentially disposed about said foil bearing, said housing comprising a convex crown extending radially outward; and
a bearing mount affixed to said static structure circumferentially disposed about said housing, said bearing mount comprising a concave recess,
wherein said housing is positioned so that said convex crown is mated with said concave recess to permit sliding displacement between said housing and said bearing mount to thereby permit rotation of said housing about an axis that is perpendicular to the axis of rotation of said rotor.

15. The system of claim 14 wherein said convex crown and said concave recess comprise spherical surfaces in axial cross-section.

16. The system of claim 15 wherein said bearing mount is split.

17. The system of claim 16 wherein said bearing mount is secured to said static structure by a threaded nut.

18. The system of claim 15 wherein said bearing mount is integral with said static structure.

19. The system of claim 15 wherein said convex crown is integral to said housing.

20. The system of claim 19 wherein said foil bearing is preloaded against said rotor.

Assignees

• Rolls Royce Corp

Inventors

• Klusman Steven A

Classifications

• F01D25/16 Primary

  Arrangement of bearings; Supporting or mounting bearings in casings (bearings per se F16C) · CPC title

• F05D2240/53

  Hydrodynamic or hydrostatic bearings · CPC title

• F16C23/045

  for radial load mainly, e.g. radial spherical plain bearings · CPC title

• F16C17/024

  with flexible leaves to create hydrodynamic wedge, e.g. radial foil bearings · CPC title

• F05D2250/241

  spherical · CPC title