Turbine shroud assemblies with channels for buffer cavity seal thermal management

Patent metadata

Field	Value
Publication number	US-12352176-B1
Application number	US-202418680562-A
Country	US
Kind code	B1
Filing date	May 31, 2024
Priority date	May 31, 2024
Publication date	Jul 8, 2025
Grant date	Jul 8, 2025

Abstract

A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier segment, a blade track segment, and a seal system. The carrier segment arranged circumferentially at least partway around an axis. The blade track segment is coupled to the carrier segment and defines a portion of a gas path of the gas turbine engine. The seal system includes seals arranged radially between the carrier segment and the blade track segment to block gases from flowing between the carrier segment and the blade track segment.

First claim

What is claimed is:

1. A turbine shroud assembly adapted for use with a gas turbine engine, the turbine shroud assembly comprising
a carrier segment arranged circumferentially at least partway around an axis, the carrier segment including an outer wall, a first support wall that extends radially inward from the outer wall, and a second support wall that extends radially inward from the outer wall at a location spaced apart axially from the first support wall to define an attachment-receiving space, and wherein the first support wall is formed to include a radially-inwardly opening first channel that extends circumferentially relative to the axis, a radially-inwardly opening second channel spaced apart axially from the first channel that extends circumferentially relative to the axis, and at least one buffer air passageway that extends radially into the first support wall axially between the first channel and the second channel and configured to discharge buffer air radially inward away from the carrier segment,
a blade track segment arranged circumferentially at least partway around the axis to define a portion of a gas path of the gas turbine engine, the blade track segment having a shroud wall that extends circumferentially partway around the axis and an attachment feature that extends radially outward from the shroud wall into the attachment-receiving space formed in the carrier segment, and
a buffer air seal assembly located radially between the carrier segment and the shroud wall of the blade track segment to block gases from flowing between the carrier segment and the blade track segment into the attachment-receiving space of the carrier segment, the buffer air seal assembly including a first seal arranged in the first channel and engaged with the shroud wall and a second seal arranged in the second channel and engaged with the shroud wall,
wherein the first and second channel cooperate to define a partition wall therebetween that extends circumferentially relative to the axis, the partition wall having a terminal end that faces the blade track segment, and wherein the at least one buffer air passageway extends radially through the partition wall,
wherein the first and second seals each include a first seal member that extends circumferentially at least partway about the axis and a second seal member that extends circumferentially at least partway about the axis, the second seal member arranged entirely radially outward of the terminal end of the partition wall and radially outward of the first seal member so that the second seal member is positioned out of a direct flow path of the buffer air discharged by the at least one buffer air passageway to reduce a risk of oxidation of the second seal member, and
wherein the second seal member is compressed between the carrier segment and the first seal member and urges the first seal member into engagement with the shroud wall of the blade track segment.

2. The turbine shroud assembly of claim 1 , wherein the second support wall is formed to include a radially-inwardly opening third channel that extends circumferentially relative to the axis, and the turbine shroud assembly further comprises a third seal arranged in the third channel.

3. The turbine shroud assembly of claim 2 , wherein the third seal includes a first seal member that extends circumferentially at least partway about the axis and a second seal member that extends circumferentially at least partway about the axis, the second seal member arranged radially outward of the first seal member.

4. The turbine shroud assembly of claim 3 , wherein the second support wall is further formed to include a radially-inwardly opening fourth channel spaced apart axially from the radially-inwardly opening third channel that extends circumferentially relative to the axis, and the turbine shroud assembly further comprises a fourth seal arranged in the fourth channel, and wherein the fourth seal includes a first seal member that extends circumferentially at least partway about the axis and a second seal member that extends circumferentially at least partway about the axis, the second seal member arranged radially outward of the first seal member.

5. The turbine shroud assembly of claim 1 , wherein the first channel and the second channel are each defined by a partition-wall surface of the partition wall, an end surface that extends axially from the partition-wall surface, and a support-wall surface that extends from the end surface towards the blade track segment, and wherein the support-wall surface has a radially-extending section that extends radially-inward from the end surface and an angled section that extends radially-inward and axially from the radially-extending section of the support-wall surface, and wherein the second seal member of the first seal and the second seal engages the radially-extending section of the support-wall surface and the partition-wall surface of the partition wall.

6. The turbine shroud assembly of claim 5 , wherein the first seal member of the first seal and the second seal engages the angled section of the support-wall surface.

7. The turbine shroud assembly of claim 6 , wherein the angled section of the support-wall surface included in the first channel extends radially-inward and axially forward from the radially-extending section, and wherein the angled section of the support-wall surface included in the second channel extends radially-inward and axially aft from the radially-extending section.

8. The turbine shroud assembly of claim 1 , wherein the second seal member of the first seal and the second seal does not engage the blade track segment.

9. The turbine shroud assembly of claim 1 , wherein the second seal member comprises a braid of metallic material.

10. The turbine shroud assembly of claim 9 , wherein the second seal member has a rectangular cross-section when viewed circumferentially relative to the axis.

11. The turbine shroud assembly of claim 1 , wherein the second seal member is a hollow tube of metallic material.

12. The turbine shroud assembly of claim 11 , wherein the hollow tube is formed to include at least one notch that extends through a wall of the hollow tube.

13. The turbine shroud assembly of claim 1 , wherein the first seal member comprises a single strand of solid metallic material.

14. The turbine shroud assembly of claim 1 , wherein the first channel is defined by a first partition-wall surface of the partition wall, a first end surface that extends axially from the first partition-wall surface, and a first support-wall surface that extends from the first end surface towards the blade track segment, and wherein the first support-wall surface has a radially-extending section that extends radially-inward from the first end surface and an angled section that extends radially-inward and axially forward from the radially-extending section of the first support-wall surface.

15. The turbine shroud assembly of claim 14 , wherein the second channel is defined by a second partition-wall surface of the partition wall, a second end surface that extends axially from the second partition-wall surface, and a second support-wall surface that extends from the second end surface towards the blade track segment, and wherein the second support-wall surface has a radially-extending section that extends radially-inward from the second end surface and an angled section that extends radially-inward and axially aft from the radially-extending section of the second support-wall surface.

16. A turbine shroud assembly adapted for use with a gas turbine engine, the turbine shroud asse

Assignees

• Rolls Royce Corp

Inventors

• Freeman Ted J
• Sippel Aaron D
• Thomas David J
• Snyder Clark J

Classifications

• F01D11/08

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D11/04 Primary

  using sealing fluid, e.g. steam · CPC title

• F05D2240/55

  Seals · CPC title

• F05D2240/11

  Shroud seal segments · CPC title