Gas turbine engine variable vane end wall insert

Patent metadata

Field	Value
Publication number	US-10557371-B2
Application number	US-201715649946-A
Country	US
Kind code	B2
Filing date	Jul 14, 2017
Priority date	Jul 14, 2017
Publication date	Feb 11, 2020
Grant date	Feb 11, 2020

Abstract

A variable vane assembly for a gas turbine engine includes a case having a bore and a recess. The case provides a first portion of a flow path surface. A vane includes a journal that extends along an axis from a vane end and received in the bore. An insert is arranged in the recess and provides a second portion of the flow path surface adjacent to the first flow path surface. The insert includes a pocket that slidably receives the vane end. The vane end is configured to move axially relative to the insert.

First claim

What is claimed is:

1. A variable vane assembly for a gas turbine engine comprising:
a case having a bore and a recess, the case providing a first portion of a flow path surface;
a vane includes a journal extending along an axis from a vane end and received in the bore; and
an insert arranged in the recess and providing a second portion of the flow path surface adjacent to the first flow path surface, the insert includes a pocket that slidably receives the vane end, the vane end is configured to move axially relative to the insert, wherein the insert includes opposing sides, and the pocket is provided on one side, and a neck is provided on the other side and includes an aperture through which the journal extends, the neck has a portion that extends radially inward into the aperture to provide a first face, and the journal includes a collar that provides a second face, a spring is arranged between the first and second faces and is configured to bias the insert and the vane end apart from one another.

2. The variable vane assembly of claim 1 , wherein a circumferential groove is provided in the portion of the neck opposite the aperture, and a piston seal is received in the groove and engages the bore.

3. The variable vane assembly of claim 2 , comprising a bearing or a bushing in the bore and supporting the journal for rotation relative to the case.

4. The variable vane assembly of claim 1 , wherein the first and second portions of the flow path surfaces are flush with one another.

5. A variable vane assembly for a gas turbine engine comprising:
a case having a bore and a recess, the case providing a first portion of a flow path surface;
a vane includes a journal extending along an axis from a vane end and received in the bore; and
an insert arranged in the recess and providing a second portion of the flow path surface adjacent to the first flow path surface, the insert includes a pocket that slidably receives the vane end, the vane end is configured to move axially relative to the insert, wherein a fillet circumscribes at least some of the pocket on a side of the insert, the fillet providing a transition from the second portion of the flow path surface to an exterior airfoil surface of the vane.

6. The variable vane assembly of claim 5 , wherein the fillet provides at least one of a leading edge airfoil fillet and a trailing edge airfoil fillet.

7. The variable vane assembly of claim 1 , wherein the insert is a different material than the vane.

8. The variable vane assembly of claim 1 , wherein the case includes radially spaced apart inner and outer cases, and the vane has opposing ends, one of the recess is provided in each of the inner and outer cases include, and one of the insert is provided in each of the recesses with the pocket of each one of the recess receiving a respective one of the opposing ends.

9. An insert for a variable vane assembly comprising:
a body having a circular periphery and with opposing sides, a pocket is provided on one side, and a neck is provided on the other side and includes an aperture, the neck has a portion that extends radially inward into the aperture to provide an annular face, and a circumferential groove is provided in the portion of the neck opposite the aperture.

10. The insert of claim 9 , wherein a fillet circumscribes at least some of the pocket on the one side.

11. The insert of claim 10 , wherein the fillet is interrupted at the aperture.

12. The insert of claim 10 , wherein the fillet provides a leading edge airfoil fillet.

13. The insert of claim 10 , wherein the fillet provides a trailing edge airfoil fillet.

14. The insert of claim 9 , wherein the neck is cylindrical in shape.

15. The insert of claim 9 , wherein a piston seal is received in the circumferential groove.

16. The insert of claim 9 , wherein the insert is constructed from a ceramic material.

17. A method of operating a variable vane assembly, comprising:
rotatably receiving a journal of a vane and an insert in a case, wherein the vane and insert are configured to rotate together with respect to the case, the insert and the case together providing a flow path surface; and
biasing the insert and the vane radially apart with the end of the vane slidably received in a pocket of the insert.

18. The method of claim 17 , comprising sealing the insert with respect to the case.

19. The method of claim 17 , comprising carrying the journal with respect to the case with a bearing or bushing.

Assignees

• United Technologies Corp

Inventors

• Ruberte Sanchez Jose E

Classifications

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F01D25/16

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

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F05D2220/32

  in gas turbines · CPC title