Rolling element bearing configured with a channel

Patent metadata

Field	Value
Publication number	US-9599161-B2
Application number	US-201414775430-A
Country	US
Kind code	B2
Filing date	Mar 14, 2014
Priority date	Mar 14, 2013
Publication date	Mar 21, 2017
Grant date	Mar 21, 2017

Abstract

A rolling element bearing includes a plurality of rolling elements, a bearing inner ring and a bearing outer ring. The rolling elements are arranged circumferentially around an axis, and radially between the inner ring and the outer ring. The inner ring includes a plurality of first passages, a second passage and a channel that extends axially into the inner ring. The first passages are arranged circumferentially around the axis. The first passages respectively extend axially through the inner ring from a plurality of first passage inlets to the channel. The second passage includes a second passage inlet that is substantially axially aligned with one of the first passage inlets. The second passage extends radially through the inner ring to a second passage outlet.

First claim

What is claimed is:

1. An assembly for a turbine engine, comprising:
a rolling element bearing and a turbine engine component arranged along an axis, the bearing including an inner ring;
the inner ring including a plurality of first passages and a first channel that extends axially into the inner ring;
the first passages arranged circumferentially around the axis, and respectively extending axially through the inner ring from a plurality of first passage inlets to the first channel; and
the turbine engine component including a component channel that extends axially into the turbine engine component and is fluidly coupled with the first channel;
wherein an outer radius of the component channel is less than an outer radius of the first channel, and the first channel extends axially to and is partially formed by an axial end of the turbine engine component.

2. The assembly of claim 1 , wherein the first channel extends circumferentially around the axis through the inner ring, and the component channel extends circumferentially around the axis through the turbine engine component.

3. The assembly of claim 1 , wherein
the first channel comprises an annular notch, and further extends radially into the inner ring from an inner side of the inner ring; and
the component channel comprises an annular notch, and further extends radially into the turbine engine component from an inner side of the turbine engine component.

4. The assembly of claim 1 , wherein the inner ring further includes a second passage that extends radially through the inner ring to a second passage outlet.

5. The assembly of claim 1 , wherein
the inner ring further includes a second channel that extends axially into the inner ring; and
the first passages extend axially through the inner ring between the first channel and the second channel.

6. The assembly of claim 1 , wherein
the turbine engine component further includes a plurality of component passages;
the component passages are arranged circumferentially around the axis, and respectively extend through the turbine engine component from the component channel to a plurality of component passage outlets; and
the component channel fluidly couples the first channel to the component passages.

7. The assembly of claim 1 , wherein the turbine engine component comprises a seal plate.

8. An assembly for a turbine engine, comprising:
a turbine engine component; and
a rolling element bearing axially engaged with the turbine engine component along an axis, the bearing including an inner ring;
the inner ring including a plurality of axial passages and an outlet channel that extends axially into the inner ring;
the axial passages arranged circumferentially around the axis, and respectively extending axially through the inner ring from a plurality of first passage inlets to the outlet channel; and
the turbine engine component including a component channel that extends axially into the turbine engine component and is fluidly coupled with the outlet channel;
wherein the outlet channel extends axially to and is partially formed by an axial end of the turbine engine component.

9. The assembly of claim 8 , wherein the outlet channel extends circumferentially around the axis through the inner ring, and the component channel extends circumferentially around the axis through the turbine engine component.

10. The assembly of claim 8 , wherein
the outlet channel comprises an annular notch, and further extends radially into the inner ring from an inner side of the inner ring; and
the component channel comprises an annular notch, and further extends radially into the turbine engine component from an inner side of the turbine engine component.

11. The assembly of claim 8 , wherein the inner ring further includes a second passage that extends radially through the inner ring to a second passage outlet.

12. The assembly of claim 8 , wherein
the inner ring further includes a second channel that extends axially into the inner ring; and
the axial passages extend axially through the inner ring between the outlet channel and the second channel.

13. The assembly of claim 8 , wherein
the turbine engine component further includes a plurality of component passages;
the component passages are arranged circumferentially around the axis, and respectively extend through the turbine engine component from the component channel to a plurality of component passage outlets; and
the component channel fluidly couples the outlet channel to the component passages.

14. The assembly of claim 8 , wherein the turbine engine component is configured as a seal plate.

15. An assembly for a turbine engine, comprising:
a rolling element bearing and a turbine engine component arranged along an axis, the bearing including an inner ring;
the inner ring including a plurality of first passages and a first channel that extends axially into the inner ring from an axial end of the inner ring;
the first passages arranged circumferentially around the axis, and respectively extending axially through the inner ring from a plurality of first passage inlets to the first channel; and
the turbine engine component including a component channel that extends axially into the turbine engine component and is fluidly coupled with the first channel;
wherein an outer radius of the component channel is less than an outer radius of the first channel as measured at the axial end of the inner ring.

16. The assembly of claim 15 , wherein the first channel extends circumferentially around the axis through the inner ring, and the component channel extends circumferentially around the axis through the turbine engine component.

17. The assembly of claim 15 , wherein
the outlet channel comprises an annular notch, and further extends radially into the inner ring from an inner side of the inner ring; and
the component channel comprises an annular notch, and further extends radially into the turbine engine component from an inner side of the turbine engine component.

18. The assembly of claim 15 , wherein the inner ring further includes a second passage that extends radially through the inner ring to a second passage outlet.

19. The assembly of claim 15 , wherein
the inner ring further includes a second channel that extends axially into the inner ring; and
the axial passages extend axially through the inner ring between the first channel and the second channel.

20. The assembly of claim 15 , wherein
the turbine engine component further includes a plurality of component passages;
the component passages are arranged circumferentially around the axis, and respectively extend through the turbine engine component from the component channel to a plurality of component passage outlets; and
the component channel fluidly couples the first channel to the component passages.

Assignees

• United Technologies Corp

Inventors

• Walker Brady
• Kovacik Ronnie K
• Shuaib Nasr A

Classifications

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F16C33/6677

  from radial inside, e.g. via a passage through the shaft and/or inner ring · CPC title

• F16C33/6674 Primary

  related to the amount supplied, e.g. gaps to restrict flow of the liquid · CPC title

• F01D25/164

  Flexible supports; Vibration damping means associated with the bearing · CPC title

• F16C2360/23

  Gas turbine engines · CPC title