Wear liner for blade outer air seal

Patent metadata

Field	Value
Publication number	US-10808564-B2
Application number	US-201916356144-A
Country	US
Kind code	B2
Filing date	Mar 18, 2019
Priority date	Mar 18, 2019
Publication date	Oct 20, 2020
Grant date	Oct 20, 2020

Abstract

A blade outer air seal assembly includes a seal segment that has a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first wall is axially spaced from a second wall. The first and second walls extend from the base portion to an outer wall to define a circumferentially extending seal passage. A wear liner is within the seal passage.

First claim

The invention claimed is:

1. A blade outer air seal assembly, comprising:
a seal segment having a base portion extending between a first circumferential side and a second circumferential side and from a first axial side to a second axial side, a first wall axially spaced from a second wall, the first and second walls extending from the base portion to an outer wall to define a circumferentially extending seal passage; and
a wear liner within the seal passage, wherein the wear liner has a first tab and a second tab configured to engage first and second edges of the outer wall.

2. The assembly of claim 1 , wherein the seal segment is a ceramic matrix composite material.

3. The assembly of claim 1 , wherein the first and second tabs are configured to engage a carrier.

4. The assembly of claim 1 , wherein the first and second tabs extend generally axially outward from a radially outer portion of the wear liner.

5. The assembly of claim 1 , wherein the first and second tabs are centered on a radially outer portion of the wear liner in an axial direction.

6. The assembly of claim 1 , wherein the first and second tabs have a length that is smaller than a flat portion of the outer wall.

7. The assembly of claim 1 , wherein the wear liner has radially inner and outer portions joined by axially forward and axially aft portions to form a liner passage.

8. The assembly of claim 7 , wherein the liner passage is configured to engage a carrier.

9. The assembly of claim 7 , wherein the liner passage is arranged coaxially within the seal passage.

10. The assembly of claim 1 , wherein the wear liner extends a circumferential width of the outer wall.

11. The assembly of claim 1 , wherein the wear liner has a height that is less than a height of the seal passage.

12. The assembly of claim 1 , wherein the wear liner is formed from sheet metal.

13. A turbine section for a gas turbine engine, comprising:
a turbine blade extending radially outwardly to a radially outer tip and for rotation about an axis of rotation;
a blade outer air seal having a plurality of segments mounted in a support structure via a carrier, the plurality of segments arranged circumferentially about the axis of rotation and radially outward of the outer tip;
each seal segment having a base portion extending between a first circumferential side and a second circumferential side and from a first axial side to a second axial side, a first wall axially spaced from a second wall, the first and second walls extending from the base portion to an outer wall to define a circumferentially extending seal passage;
a wear liner arranged between each seal segment and the carrier.

14. The turbine section of claim 13 , wherein the wear liner has a radially extending tab engaged with an edge of the outer wall.

15. The turbine section of claim 14 , wherein the tab is arranged between the edge of the outer wall and a post on the carrier.

16. The turbine section of claim 13 , wherein the wear liner has radially inner and outer portions joined by axially forward and axially aft portions to form a liner passage, and a portion of the carrier is arranged within the liner passage.

17. The turbine section of claim 13 , wherein the seal segment is a ceramic matrix composite material, the wear liner is a metallic material, and the carrier is a metallic material.

18. A method of assembly a blade outer air seal assembly, comprising:
providing a seal segment having a base portion extending between a first circumferential side and a second circumferential side and from a first axial side to a second axial side, a first wall axially spaced from a second wall, the first and second walls extending from the base portion to an outer wall to define a circumferentially extending seal passage;
inserting a wear liner having a liner passage into the seal passage; and
inserting a portion of a carrier into the liner passage.

19. The method of claim 18 , wherein the seal segment is a ceramic matrix composite material, the wear liner is a metallic material, and the carrier is a metallic material.

Assignees

• United Technologies Corp
• Raytheon Tech Corporatino

Inventors

• Barker William M
• Clark Thomas E

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D11/005 Primary

  Sealing means between non relatively rotating elements · CPC title