Boas rail shield

Patent metadata

Field	Value
Publication number	US-10161258-B2
Application number	US-201615071485-A
Country	US
Kind code	B2
Filing date	Mar 16, 2016
Priority date	Mar 16, 2016
Publication date	Dec 25, 2018
Grant date	Dec 25, 2018

Abstract

A seal assembly includes a seal arc segment that defines radially inner and outer sides with the radially outer side including radially-extending sidewalls. A radially inner surface joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket. A rail shield has radially-extending walls lines the radially-extending sidewalls.

First claim

What is claimed is:

1. A blade outer air seal assembly for a gas turbine engine comprising:
a seal arc segment defining radially inner and outer sides and first and second circumferential ends, the first and second circumferential ends defining first and second seal supports, the radially outer side including radially-extending sidewalls and a radially inner surface joining the radially-extending sidewalls, the radially-extending sidewalls and the radially inner surface defining a pocket between the first and second seal supports; and
a rail shield having radially-extending walls lining the radially-extending sidewalls.

2. The blade outer air seal assembly as recited in claim 1 , further comprising a seal between the rail shield and the radially-extending sidewalls.

3. The blade outer air seal assembly as recited in claim 1 , wherein the rail shield includes a plurality of walls extending from a first radial end to a second radial end, the first radial end of the plurality of walls defines a first opening, the second radial end of the plurality of walls defines a second opening, and the first opening is in fluid communication with the second opening.

4. The blade outer air seal assembly as recited in claim 3 , further comprising a seal between the rail shield and the radially-extending sidewalls, wherein the seal and the rail shield seal the radially-extending sidewalls from fluid entering the first radial end of the rail shield.

5. The blade outer air seal assembly as recited in claim 4 , wherein the rail shield defines a groove adjacent the second radial end, and the seal is disposed in the groove.

6. The blade outer air seal assembly as recited in claim 4 , wherein the seal is a rope seal contiguous with the radially-extending sidewalls.

7. The blade outer air seal assembly as recited in claim 1 , wherein the seal arc segment is a first material, the rail shield is a second material, and the first material is different from the second material.

8. The blade outer air seal assembly as recited in claim 7 , wherein the second material is a metallic alloy.

9. The blade outer air seal assembly as recited in claim 1 , wherein a radially outer surface of the rail shield is radially flush with a radially outer surface of the seal arc segment.

10. The blade outer air seal assembly as recited in claim 1 , wherein the pocket extends circumferentially a majority of the circumferential length of the seal arc segment.

11. The blade outer air seal assembly as recited in claim 10 , wherein the pocket extends axially a majority of the axial length of the seal arc segment.

12. The blade outer air seal assembly as recited in claim 1 , comprising
a carriage defining first and second support members, the first support member supporting the first seal support in a first ramped interface and the second support member supporting the second seal support in a second ramped interface.

13. The blade outer air seal assembly as recited in claim 1 , wherein the rail shield is received within the pocket.

14. A gas turbine engine comprising:
a rotor section including a rotor having a plurality of blades and at least one annular seal system circumscribing the rotor, the annular seal system comprising:
a plurality of seal arc segments suspended by seal supports at their respective circumferential ends from a plurality of carriages, and a plurality of corresponding rail shields, each of the seal arc segments defining radially inner and outer sides, the radially outer side including radially-extending sidewalls and a radially inner surface joining the radially-extending sidewalls, the radially-extending sidewalls and the radially inner surface defining a pocket, and
the corresponding rail shield having radially-extending walls lining the radially-extending sidewalls of the pocket.

15. The gas turbine engine as recited in claim 14 , wherein the corresponding rail shield includes a plurality of walls extending from a first radial end to a second radial end, the first radial end of the plurality of walls defines a first opening, the second radial end of the plurality of walls defines a second opening, and the first opening is in fluid communication with the second opening.

16. The gas turbine engine as recited in claim 14 , wherein the annular seal system further comprises a plurality of corresponding seals, and the corresponding seal is between the corresponding rail shield and the radially-extending sidewalls.

17. The gas turbine engine as recited in claim 14 , wherein the seal arc segment is a first material, the rail shield is a second material, and the first material is different from the second material.

18. The gas turbine engine as recited in claim 14 , wherein the corresponding rail shield is received within the pocket.

19. A method of assembling a blade outer air seal, the method comprising:
providing a seal arc segment that defines radially inner and outer sides, the radially outer side includes radially-extending sidewalls and a radially inner surface joins the radially-extending sidewalls, the radially-extending sidewalls and the radially inner surface define a pocket;
inserting a rail shield in the pocket, the rail shield having radially extending walls lining the radially-extending sidewalls; and
suspending from a carriage a first seal support defined at a first circumferential end of the seal arc segment and a second seal support defined at a second circumferential end of the seal arc segment.

20. The method as recited in claim 19 , comprising:
inserting a seal in the pocket, wherein the seal is between the rail shield and the radially-extending sidewalls.

21. The method as recited in claim 20 , wherein the seal is disposed in a groove of the rail shield.

Assignees

• United Technologies Corp

Inventors

• Mccaffrey Michael G
• Hagan Benjamin F
• Griffin David Richard
• Balawajder Peter
• Corcoran Christopher

Classifications

• F05D2240/11

  Shroud seal segments · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2300/10

  Metals, alloys or intermetallic compounds · CPC title

• F05D2230/60

  Assembly methods · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title