Hydrodynamic Tapered Roller Bearings and Gas Turbine Engine Systems Involving Such Bearings

• US 20090214147A1
• Filed: 02/25/2008
• Published: 08/27/2009
• Est. Priority Date: 02/25/2008
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Duong, Loc
• Granted Patent: US 8,235,599 B2
• Time in Patent Office: Days
• US Class Current: 384/450
• CPC Class Codes: F01D 25/16 Arrangement of bearings; Supporting or mounting bearings in casings bearings per se F16C
• CPC Class Codes: F05D 2240/53 Hydrodynamic or hydrostatic bearings
• CPC Class Codes: F16C 19/225 Details of the ribs supporting the end of the rollers
• CPC Class Codes: F16C 19/364 with tapered rollers, i.e. rollers having essentially the shape of a truncated cone
• CPC Class Codes: F16C 2360/23 Gas turbine engines
• CPC Class Codes: F16C 33/4605 Details of interaction of cage and race, e.g. retention or centring
• CPC Class Codes: F16C 33/4682 of the end walls, e.g. interaction with the end faces of the rollers
• CPC Class Codes: F16C 33/583 Details of specific parts of races
• CPC Class Codes: F16C 33/6677 from radial inside, e.g. via a passage through the shaft and/or inner ring

Abstract

Tapered roller bearings and gas turbine engine systems involving such bearings are provided. In this regard, a representative bearing cage for a gas turbine engine includes: an outer cage rim and an inner cage rim; the outer cage rim having a rounded edge at a location of contact between the outer cage rim and a roller.

Claims

1. A bearing cage for a tapered roller bearing having rollers, said bearing cage comprising:

an outer cage rim and an inner cage rim;

the outer cage rim having a rounded edge at a location of contact between the outer cage rim and a roller.

2. The bearing cage of claim 1, wherein the outer cage rim has a radially disposed annular surface operative to direct a load imparted to the outer cage rim via the roller.

3. The bearing cage of claim 1, wherein the outer cage rim has an axially disposed annular surface operative to direct a load imparted to the outer cage rim via the roller.

4. The bearing cage of claim 1, wherein the bearing cage is a hydrodynamic tapered roller bearing cage.

5. A bearing assembly comprising:

a plurality of rollers, each of the rollers having an end; and

a bearing cage operative to contain the plurality of rollers, the bearing cage having an outer cage rim, the outer cage rim having a rounded edge at a location of contact between the outer cage rim and first end of a first of the rollers.

6. The bearing assembly of claim 5, wherein:

the bearing assembly further comprises an inner race; and

the outer cage rim of the bearing cage is operative to direct load imparted via the rollers to the inner race.

7. The bearing assembly of claim 5, wherein the bearing assembly is a tapered roller bearing.

8. The bearing assembly of claim 7, wherein the bearing assembly is a hydrodynamic tapered roller bearing.

9. The bearing assembly of claim 6, wherein:

the bearing assembly further comprises an inner race having an inner race flange; and

the inner race flange comprises a plurality of lobes operative to interact with an outermost side of the outer cage rim.

10. The bearing assembly of claim 9, wherein the lobes located on the inner race flange are equally spaced about the inner race flange.

11. The bearing assembly of claim 9, wherein the lobes are located on a radially disposed annular surface of the inner race flange.

12. The bearing assembly of claim 9, wherein the lobes are located on an axially disposed annular surface of the inner race flange.

13. The bearing assembly of claim 9, wherein the inner race flange further comprises a plurality of channels for oil distribution.

14. The bearing assembly of claim 13, further comprising a recess area adjacent to the inner race flange, the recess area being operative to provide oil to surfaces of the bearing assembly via the channels.

15. A gas turbine engine comprising:

a compressor;

a shaft interconnected with the compressor;

a turbine operative to drive the shaft; and

a bearing assembly operative to support to the shaft, the bearing assembly having a plurality of rollers, a race and a bearing cage operative to contain the plurality of rollers, the bearing cage having a cage rim, the cage rim of the bearing cage being operative to direct load imparted via the rollers to the race.

16. The gas turbine engine of claim 15, wherein:

the cage rim is an outer cage rim; and

the outer cage rim has a rounded edge at a location of contact between the outer cage rim and a corresponding end of each of the rollers.

17. The gas turbine engine of claim 16, wherein:

the race is an inner race;

the inner race has an inner race flange; and

the inner race flange comprises a plurality of lobes operative to interact with an outermost side of the outer cage rim.

18. The gas turbine engine of claim 17, wherein the lobes located on the inner race flange are equally spaced about the inner race flange.

19. The gas turbine engine of claim 17, wherein the lobes are located on a radially disposed annular surface of the inner race flange.

20. The gas turbine engine of claim 17, wherein the lobes are located on an axially disposed annular surface of the inner race flange.