RESILIENT BEARING MOUNT WITH INTEGRAL DAMPER FLUID PASSAGE FOR A GEARED TURBOFAN ENGINE

• US 20180051706A1
• Filed: 08/18/2016
• Published: 02/22/2018
• Est. Priority Date: 08/18/2016
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: DiBenedetto, Enzo
• Granted Patent: US 10,436,065 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 25/162 Bearing supports
• CPC Class Codes: F01D 25/164 Flexible supports; Vibration damping means associated with the bearing
• CPC Class Codes: F01D 25/18 Lubricating arrangements of machines or engines in general F01M
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/52 Axial thrust bearings
• CPC Class Codes: F05D 2240/53 Hydrodynamic or hydrostatic bearings
• CPC Class Codes: F05D 2240/54 Radial bearings
• CPC Class Codes: F16C 2360/23 Gas turbine engines in general F02C
• CPC Class Codes: F16C 27/045 with a fluid film, e.g. squeeze film damping
• CPC Class Codes: F16C 33/586 outside the space between the races, e.g. end faces or bore of inner ring
• CPC Class Codes: F16C 33/6637 with liquid lubricant
• CPC Class Codes: F16C 33/6659 Details of supply of the liquid to the bearing, e.g. passages or nozzles

Abstract

A gas turbine engine includes a bearing support ring with a first annular body and a second annular body disposed radially inward of the first annular body. A radial spring is connected to the first annular body and the second annular body. The gas turbine engine includes a frame with a case that extends around the first annular body. The frame includes an annular member connected to the case and positioned radially between the radial spring and the second annular body. A fluid port extends radially through the annular member. A seal is disposed around the annular member and forward of the fluid port. A first fluid passage extends through the case. A second fluid passage is formed between the bearing support ring and the frame and extends from the first fluid passage to the fluid port. A bearing outer race is disposed inward of the second annular body.

Claims

1. A gas turbine engine comprises:

a bearing support ring, wherein the bearing support ring comprises;

a first annular body;

a second annular body disposed radially inward of the first annular body relative a center axis of the gas turbine engine; and

a radial spring connected to the first annular body and the second annular body, wherein the radial spring extends circumferentially about the center axis and extends radially between the first annular body and the second annular body;

a frame comprising;

a case extending circumferentially around the first annular body of the bearing support ring;

an annular member connected to the case and positioned radially between the radial spring and the second annular body of the bearing support ring, wherein the annular member extends circumferentially around the second annular body; and

a fluid port extending radially through the annular member;

a seal disposed around the annular member of the frame, disposed axially forward of the fluid port, and extending radially between the annular member and the radial spring of the bearing support ring;

a first fluid passage extending through the case and positioned axially over the first annular body;

a second fluid passage formed between the bearing support ring and the case and the annular member of the frame, wherein the second fluid passage extends from the first fluid passage to the fluid port; and

a bearing outer race disposed radially inward of the second annular body of the bearing support ring.

2. The gas turbine engine of claim 1 further comprising:

a second seal extending circumferentially around the second annular body of the bearing support ring, disposed axially forward of the fluid port, and extending radially between the second annular body and the annular member of the frame; and

a third seal extending circumferentially around the second annular body of the bearing support ring, disposed axially aft of the fluid port, and extending radially between the second annular body and the annular member of the frame.

3. The gas turbine engine of claim 2, wherein the seal, the second seal, and the third seal are piston seals.

4. The gas turbine engine of claim 1, wherein the bearing support ring further comprises:

a mounting flange connected to a forward end of the first annular body, wherein the mounting flange extends radially outward from the forward end of the first annular body.

5. The gas turbine engine of claim 4, wherein the gas turbine engine further comprises:

at least one fastener connecting the mounting flange to the case of the frame.

6. The gas turbine engine of claim 1, wherein the gas turbine engine further comprises:

a bearing inner race disposed radially inward of the bearing outer race; and

a plurality of roller bearing elements disposed radially between the bearing outer race and the bearing inner race.

7. The gas turbine engine of claim 1 further comprising:

a squirrel cage disposed radially inward of the case and positioned forward of the bearing support ring,

wherein the squirrel cage comprises a forward end, an aft end, and a plurality of circumferentially spaced beams extending between the forward end and the aft end of the bearing support cage.

8. The gas turbine engine of claim 7 further comprising:

a ball bearing housing disposed radially inward of the squirrel cage and connected to the aft end of the squirrel cage;

a ball bearing outer race disposed radially inward of the ball bearing housing;

a ball bearing inner race disposed radially inward of the ball bearing outer race; and

a plurality of ball bearing elements disposed radially between the ball bearing outer race and the ball bearing inner race.

9. The gas turbine engine of claim 8, wherein the ball bearing housing, the ball bearing outer race, the ball bearing inner race, and the plurality of ball bearing elements are positioned axially forward of the second annular body of the bearing support ring, the bearing outer race, the bearing inner race, and the plurality of roller bearing elements.

10. The gas turbine engine of claim 9, wherein the ball bearing housing comprises a forward end and an aft end, wherein the aft end of the ball bearing housing is positioned axially aft of a forward end of the first annular body of the bearing support ring and positioned axially forward of the radial spring of the bearing support ring.

11. An assembly for a gas turbine engine comprises:

a frame comprising;

a case extending circumferentially around a center axis of the gas turbine engine;

an annular member connected to the case and disposed radially inward of the case, wherein the annular member extends circumferentially around the center axis;

a fluid port extending radially through the annular member;

a bearing support ring, wherein the bearing support ring comprises;

a first annular body disposed radially inward of the case and radially outward of the annular member, wherein the first annular body extends axially between a forward end and an aft end;

a second annular body disposed radially inward of the annular member of the frame;

wherein the second annular body extends axially between a forward end and an aft end;

a first bow connected to the aft end of the first annular body and curving radially inward and extending axially forward; and

a second bow connected to the first bow and curving radially inward to connect with the forward end of the second annular body,

wherein the annular member of the frame extends axially forward toward the second bow and is disposed radially between the first bow and the second annular body;

a seal disposed around the annular member of the frame, disposed axially forward of the fluid port, and extending radially between the annular member and the first bow of the bearing support ring;

a first fluid passage extending through the case;

a second fluid passage formed between the bearing support ring and the case and the annular member of the frame, wherein the second fluid passage extends from the first fluid passage to the fluid port; and

a bearing outer race disposed radially inward of the second annular body of the bearing support ring and connected to the second annular body.

12. The assembly of claim 11, wherein the frame further comprises:

a strut extending radially outward from the case.

13. The assembly of claim 12, wherein the first fluid passage extends radially through the strut.

14. The assembly of claim 11, wherein the frame further comprises:

a scavenge passage extending axially through an entire axial length of the annular member of the frame,

wherein the scavenge passage does not intersect the radial fluid port.

15. The assembly of claim 14, wherein the bearing support ring further comprises:

a drain hole extending axially through the second bow of the bearing support ring and in fluidic communication with the scavenge passage.

16. The assembly of claim 11 further comprising:

a second seal extending circumferentially around the second annular body of the bearing support ring, disposed axially forward of the fluid port, and extending radially between the second annular body and the annular member of the frame; and

a third seal extending circumferentially around the second annular body of the bearing support ring, disposed axially aft of the fluid port, and extending radially between the second annular body and the annular member of the frame.

17. A gas turbine engine comprises:

a bearing support ring, wherein the bearing support ring comprises;

a first annular body extending axially aftward from a first end of the bearing support ring relative a center axis of the gas turbine engine;

a second annular body extending axially forward from a second end of the bearing support ring, wherein the second annular body and the second end of the bearing support ring are disposed radially inward from the first annular body and the first end; and

a resilient member connected to the first annular body and the second annular body, wherein the resilient member extends circumferentially about the center axis and extends radially between the first annular body and the second annular body;

a frame comprising;

a case extending circumferentially around the first annular body of the bearing support ring;

an annular member connected to the case and positioned radially between the resilient member and the second annular body of the bearing support ring, wherein the annular member extends circumferentially around the second annular body; and

a fluid port extending radially through the annular member;

a seal disposed around the annular member of the frame, disposed axially forward of the fluid port, and extending radially between the annular member and the resilient member of the bearing support ring;

a first fluid passage extending through the case and positioned axially over the first annular body;

a second fluid passage formed between the bearing support ring and the case and the annular member of the frame, wherein the second fluid passage extends from the first fluid passage to the fluid port; and

a bearing outer race disposed radially inward of the second annular body of the bearing support ring and connected to the second annular body.

18. The gas turbine engine of claim 17 further comprising:

a second seal extending circumferentially around the second annular body of the bearing support ring, disposed axially forward of the fluid port, and extending radially between the second annular body and the annular member of the frame; and

a third seal extending circumferentially around the second annular body of the bearing support ring, disposed axially aft of the fluid port, and extending radially between the second annular body and the annular member of the frame.

19. The gas turbine engine of claim 17, wherein the gas turbine engine further comprises:

a bearing inner race disposed radially inward of the bearing outer race; and

a plurality of roller bearing elements disposed radially inward of the bearing outer race.

20. The gas turbine engine of claim 19 further comprising:

a ball bearing assembly disposed radially inward of the case and positioned axially forward of the second annular body of the bearing support ring.