Oil transfer passage arrangement for a shaft of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9932860-B2
Application number	US-201414774013-A
Country	US
Kind code	B2
Filing date	Mar 12, 2014
Priority date	Mar 13, 2013
Publication date	Apr 3, 2018
Grant date	Apr 3, 2018

Abstract

A shaft for a gas turbine engine includes a shaft bore along an axis, a circumferential groove within the shaft bore, a multiple of first axial grooves from said circumferential groove and a multiple of second axial grooves from said circumferential groove.

First claim

What is claimed is:

1. A shaft for a gas turbine engine comprising:
a shaft bore along an axis;
a circumferential groove within said shaft bore, wherein the circumferential groove extends continuously circumferentially at least 180 degrees around the axis;
a multiple of first axial grooves extending in a first axial direction along the axis from said circumferential groove; and
a multiple of second axial grooves extending in the first axial direction along the axis from said circumferential groove, wherein said multiple of second axial grooves extend axially beyond said multiple of first axial grooves.

2. The shaft as recited in claim 1 , wherein at least one of said multiple of first axial grooves includes an aperture.

3. The shaft as recited in claim 1 , wherein at least one of said multiple of first axial grooves includes an aperture that communicates with a passage toward a bearing.

4. The shaft as recited in claim 1 , wherein each of said multiple of first axial grooves includes an aperture.

5. The shaft as recited in claim 1 , wherein each of said multiple of first axial grooves includes an aperture that communicates with a passage toward a bearing.

6. The shaft as recited in claim 1 , further comprising a multiple of apertures in a radial step that communicates with said shaft bore.

7. The shaft as recited in claim 6 , further comprising an axial oil scoop that extends from said radial step.

8. The shaft as recited in claim 1 , further comprising a multiple of inner splines within said shaft bore downstream of said multiple of second axial grooves and said multiple of first axial grooves.

9. A shaft for a gas turbine engine comprising:
a shaft bore along an axis;
a first groove within said shaft bore, wherein the first groove extends circumferentially and uninterrupted at least 180 degrees around the axis;
a multiple of first axial grooves extending in a first axial direction along the axis from said first groove; and
a multiple of second axial grooves extending in the first axial direction along the axis from said first groove, wherein said multiple of second axial grooves extend axially beyond said multiple of first axial grooves.

10. A gas turbine engine comprising:
a shaft with a shaft bore along an axis;
a circumferential groove within said shaft bore, wherein the circumferential groove extends circumferentially and uninterrupted at least one hundred and eighty degrees around the axis;
a multiple of first axial grooves extending in a first axial direction along the axis from said circumferential groove;
a multiple of second axial grooves extending in the first axial direction along the axis from said circumferential groove, wherein an axial length of each of said multiple of second axial grooves is greater than an axial length of each of said multiple of first axial grooves; and
a multiple of splines within said shaft bore downstream of said multiple of second axial grooves.

11. The gas turbine engine as recited in claim 10 , wherein each of said multiple of first axial grooves include an aperture that communicates with a passage toward a bearing.

12. The gas turbine engine as recited in claim 10 , wherein said multiple of second axial grooves extend axially beyond said multiple of first axial grooves.

13. The gas turbine engine as recited in claim 10 , further comprising a multiple of apertures downstream of said multiple of splines.

14. The gas turbine engine as recited in claim 13 , wherein said multiple of apertures communicate with a respective radial passage through said shaft.

15. A method of cooling a bearing that supports a shaft comprising:
directing oil though a multiple of axial apertures toward a circumferential groove within a bore of the shaft, wherein the circumferential groove extends circumferentially and uninterrupted at least 180 degrees around an axis of the shaft; and
distributing oil from the circumferential groove to a multiple of first axial grooves and a multiple of second axial grooves.

16. The method as recited in claim 15 , further comprising:
terminating each of the multiple of first axial grooves at an aperture.

17. The method as recited in claim 15 , wherein the multiple of first axial grooves extend in a first axial direction along an axis from said circumferential groove, wherein the multiple of second axial grooves extends in the first axial direction along the axis from said circumferential groove, and wherein said multiple of second axial grooves extend axially beyond said multiple of first axial grooves.

Assignees

• United Technologies Corp

Inventors

• Stutz Robert C
• Grillo Joseph

Classifications

• Y10T464/10

  Cross-Sectional Technologies · mapped topic

• F05D2260/98

  Lubrication · CPC title

• F16C3/02

  Shafts; Axles · CPC title

• F05D2240/61

  Hollow · CPC title

• F04D29/053

  Shafts · CPC title