Concentric axial oil scoop

Patent metadata

Field	Value
Publication number	US-2016376947-A1
Application number	US-201514754124-A
Country	US
Kind code	A1
Filing date	Jun 29, 2015
Priority date	Jun 29, 2015
Publication date	Dec 29, 2016
Grant date	—

Abstract

Aspects of the disclosure are directed to a shaft configured with a first hole, a bearing race coupled to the shaft and configured with a second hole and a third hole, and an oil scoop configured to receive oil and provide the oil to the shaft, where the first and second holes are oriented axially with respect to the shaft, and where the third hole is oriented radially with respect to the shaft. In some embodiments, a second oil scoop is configured to receive oil and provide the oil to the shall. The oil scoop and the second oil scoop may be concentric with respect to one another.

First claim

What is claimed is:

1 . A system associated with an engine of an aircraft, comprising:
a shaft configured with a first hole; a bearing race coupled to the shaft and configured with a second hole and a third hole; and an axial oil scoop configured to receive oil and provide the oil to the shaft, wherein the first and second holes are oriented axially with respect to the shaft, and wherein the third hole is oriented radially with respect to the shaft.

2 . The system of claim 1 , further comprising:
at least one oil jet configured to provide the oil to the oil scoop.

3 . The system of claim 1 , further comprising:
a second axial oil scoop configured to receive and provide oil to the shaft.

4 . The system of claim 1 , further comprising:
a spline configured to convey the oil axially forward to the third hole after the oil traverses at least one of the first hole and the second hole.

5 . The system of claim 4 , further comprising:
the third hole configured to convey the oil from the spline to at least one of a seal runner and a hearing.

6 . The system of claim 1 , further comprising:
a seal runner coupled to the shaft configured to transfer heat o at least a portion of the oil.

7 . The system of claim 1 , further comprising:
a bearing coupled to the shaft configured to transfer heat to at least a portion of the oil.

8 . A method comprising:
forming at least one axially-oriented hole in a shaft of an aircraft engine; forming at least one axially-oriented hole and at least one radially-oriented hole in a bearing race; coupling the shaft and the bearing race; manufacturing an axial oil scoop; and assembling the oil scoop onto the shaft.

9 . The method of claim 8 , further comprising:
applying heat to the oil scoop to assemble the oil scoop onto the shaft.

10 . The method of claim 8 , further comprising:
assembling a seal runner on the shaft.

11 . The method of claim 10 , further comprising:
assembling a bearing associated with the bearing race onto the shaft.

12 . The method of claim 11 , further comprising:
assembling a nut to clamp at least one of the seal runner or the bearing.

13 . The method of claim 12 , further comprising:
assembling a sub assembly formed from the bearing, the nut, the seal runner, and the shaft into a bearing housing.

14 . The method of claim 13 , further comprising:
assembling at least one oil jet into the bearing housing.

15 . The method of claim 14 , wherein the at least one oil jet comprises plurality of oil jets.

16 . The method of claim 15 , further comprising:
configuring a first of the oil jets to provide first oil to the oil scoop; and configuring a second of the oil jets to provide second oil to a second axial oil scoop.

17 . The method of claim 8 , further comprising:
forming threads on the shaft to accommodate a nut; forming at least one hole in a bearing; forming an annulus in the bearing; assembling the bearing onto the shaft via a bearing race; and manufacturing the nut with a second axial oil scoop.

18 . The method of claim 17 , wherein the axial oil scoop and the second axial oil scoop are concentric with respect to one another.

19 . The method of claim 17 , wherein the second axial oil scoop is located radially outboard of the axial oil scoop.

20 . The method of claim 17 , further comprising:
manufacturing a nut locking device; and coupling the nut locking device and the nut.

Assignees

• United Technologies Corp

Inventors

• Lucas James L

Classifications

• F16C2360/23

  Gas turbine engines · CPC title

• F01D25/186

  for sliding contact bearing · CPC title

• F16C33/6677

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

• F02C7/06

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

• F16C19/06

  with a single row or balls · CPC title