Gas turbine engine with bearing compartment wall cooling

Patent metadata

Field	Value
Publication number	US-9234439-B2
Application number	US-201213665984-A
Country	US
Kind code	B2
Filing date	Nov 1, 2012
Priority date	Nov 1, 2012
Publication date	Jan 12, 2016
Grant date	Jan 12, 2016

Abstract

A bearing compartment for a gas turbine engine comprises a housing that surrounds an engine axis of rotation and has an inner surface and an outer surface spaced radially outward of the inner surface. The housing defines an open volume for a lubricant and includes a bearing seat to seat a bearing for rotation about the engine axis of rotation. The housing includes at least one cooling protuberance extending into the open volume.

First claim

What is claimed is:

1. A bearing compartment for a gas turbine engine comprising:
a housing surrounding an engine axis of rotation and having an inner surface and an outer surface spaced radially outward of the inner surface, the housing defining an open volume for a lubricant, and wherein the housing includes a seat for a bearing for rotation about the engine axis of rotation, and wherein the housing includes a plurality of cooling protuberances extending into the open volume, and wherein the inner surface comprises a wetted surface, and wherein the cooling protuberances extend radially inward from the wetted surface into the lubricant with each cooling protuberance being spaced apart from an adjacent cooling protuberance by a gap; and
wherein the housing extends from a fore end to an aft end, and wherein the aft end includes an attachment flange configured for attachment to a non-rotating engine structure, and wherein the inner surface of the housing includes an axial portion, and wherein the inner surface tapers inwardly in an aft direction from an aft end of the axial portion to form an inward inclined portion, and wherein the protuberances are formed on at least the axial portion.

2. The bearing compartment according to claim 1 wherein the cooling protuberances comprise a plurality of fins.

3. The bearing compartment according to claim 1 wherein each cooling protuberance extends to a distal end that is spaced from the inner surface of the housing.

4. The bearing compartment according to claim 1 wherein the housing includes a probe boss extending outward from the outer surface of the housing, the probe boss defining an opening configured to receive a probe.

5. The bearing compartment according to claim 1 wherein the inner surface tapers outwardly in an aft direction from an aft end of the inward inclined portion to form an outward inclined portion, and wherein the case attachment flange is formed at the aft end of the outward inclined portion.

6. The bearing compartment according to claim 5 wherein a probe boss is formed in the inward inclined portion, the probe boss defining an opening configured to receive a probe.

7. The bearing compartment according to claim 5 wherein the seat for the bearing is positioned radially inwardly of the outward inclined portion.

8. A gas turbine engine comprising:
a non-rotating engine structure;
a first shaft rotating about an engine axis relative to the non-rotating engine structure;
a first compressor connected to the first shaft;
a first turbine connected to the first shaft; and
at least one bearing system supporting the first shaft for rotation relative to the non-rotating engine structure, the at least one bearing system including a bearing compartment comprising a housing surrounding the engine axis, and wherein the housing has an inner surface and an outer surface spaced radially outward of the inner surface, the housing defining an open volume for a lubricant, and wherein the housing includes a seat for a bearing for rotation about the engine axis, and wherein the housing includes a plurality of cooling protuberances extending into the open volume, and wherein the inner surface comprises a wetted surface, and wherein the cooling protuberances extend radially inward from the wetted surface into the lubricant with each cooling protuberance being spaced apart from an adjacent cooling protuberance by a gap, and wherein the housing extends from a fore end to an aft end, and wherein the aft end includes an attachment flange configured for attachment to a non-rotating engine structure, and wherein the inner surface of the housing includes an axial portion, and wherein the inner surface tapers inwardly in an aft direction from an aft end of the axial portion to form an inward inclined portion, and wherein the protuberances are formed on at least the axial portion.

9. The gas turbine engine according to claim 8 wherein the bearing includes an inner race mounted for rotation with the first shaft and an outer race seated on the bearing seat.

10. The gas turbine engine according to claim 8 wherein the cooling protuberances comprise a plurality of fins.

11. The gas turbine engine according to claim 8 wherein each cooling protuberance extends to a distal tip that has a rounded surface.

12. The gas turbine engine according to claim 8 wherein the housing comprises a single-piece cast component.

13. The gas turbine engine according to claim 8 including a second shaft, a second compressor connected to the second shaft, and a second turbine connected to the second shaft.

14. The gas turbine engine according to claim 13 wherein the first compressor comprises a low pressure compressor and the first turbine comprises a low pressure turbine, and wherein the second compressor comprises a high pressure compressor and the second turbine comprises a high pressure turbine.

15. The gas turbine engine according to claim 14 including a fan driven by the first shaft.

16. The gas turbine engine according to claim 8 wherein the housing includes a probe boss extending outward from the outer surface of the housing, the probe boss defining an opening configured to receive a probe.

17. The gas turbine engine according to claim 8 wherein the inner surface tapers outwardly in an aft direction from an aft end of the inward inclined portion to form an outward inclined portion, and wherein the case attachment flange is formed at the aft end of the outward inclined portion.

18. The gas turbine engine according to claim 17 wherein a probe boss is formed in the inward inclined portion, the probe boss defining an opening configured to receive a probe.

19. The gas turbine engine according to claim 17 wherein the seat for the bearing is positioned radially inwardly of the outward inclined portion.

Assignees

• United Technologies Corp

Inventors

• Demitraszek Sr Anthony
• Soh Woo Y

Classifications

• F01D25/125

  of bearings · CPC title

• F01D25/18

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F16C37/007

  of rolling bearings · CPC title

• F01D25/16 Primary

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

• Y02T50/675

  Cross-Sectional Technologies · mapped topic