Granted Patent B1

US 12,410,725 · App. 18/680,758 · Granted Sep 9, 2025

Inventors: Ted J. Freeman (Indianapolis, IN); Aaron D. Sippel (Indianapolis, IN); David J. Thomas (Indianapolis, IN); Clark J. Snyder (Indianapolis, IN); Grant Cook (Indianapolis, IN)

Assignee: Rolls-Royce Corporation

F01D11/08F05D2230/60F05D2240/11F05D2240/55F05D2260/30

Abstract

Claims (37)

1. A turbine shroud assembly 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 the first support wall formed to include a radially-inwardly opening first channel that extends circumferentially relative to the axis and at least one buffer air passageway that extends radially into the forward support wall and opens into the first channel,

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 arranged in the first channel between the forward support wall of 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, the buffer air seal assembly including a seal that extends circumferentially relative to the axis and axially across the first channel,

wherein the at least one buffer air passageway is configured to discharge buffer air radially inward away from the carrier segment into the first channel to urge the seal radially inward into engagement with the shroud wall of the blade track segment,

wherein the buffer air seal assembly further includes a bias member compressed radially between the carrier segment and the seal to apply a bias force to the seal to bias the seal radially inward towards the shroud wall of the blade track segment, and

wherein the seal is formed to include an inner groove that extends radially inward into the seal and circumferentially relative to the axis and at least one through hole that extends radially through the seal and opens into the inner groove to allow the buffer air to flow through the seal into the inner groove.

2. The turbine shroud assembly of claim 1 , wherein the seal includes a first seal member and a second seal member coupled to the first seal member for movement therewith, wherein the first seal member has a rectangular cross-sectional shape when viewed in the circumferential direction that defines an inner surface engaged with the shroud wall of the blade track segment, an outer surface spaced apart radially from the inner surface, and two side surfaces spaced apart axially that extend radially between the inner surface and the outer surface, and wherein the second seal member is arranged axially between a first side surface of the first seal member and the carrier segment.

3. The turbine shroud assembly of claim 2 , wherein the first seal member is formed to include a side groove that extends axially into a first side surface of the first seal member and circumferentially relative to the axis and the second seal member is arranged in the side groove and engages the carrier segment in the first channel.

4. The turbine shroud assembly of claim 2 , wherein the first seal member is formed to include the inner groove that extends radially into the inner surface of the first seal member and circumferentially relative to the axis and the at least one through hole that extends radially through the first seal member and opens into the inner groove to allow the buffer air to flow through the first seal member into the inner groove.

5. The turbine shroud assembly of claim 1 , wherein the seal includes an outer seal member, a forward seal member that extends radially inward from the outer seal member, and an aft seal member that extends radially inward from the outer seal member, the aft seal member spaced apart axially from the forward seal member to define the inner groove therebetween, and the outer seal member, the forward seal member, and aft seal member are free to move relative to each other.

6. The turbine shroud assembly of claim 5 , wherein the outer seal member is formed to include the at least one through hole that extends radially through the outer seal member and opens into the inner groove to allow the buffer air to flow through the outer seal member into the inner groove to urge the forward seal member axially forward and the aft seal member axially aft into engagement with the carrier segment.

7. The turbine shroud assembly of claim 1 , wherein the seal includes a first seal member and a second seal member coupled to the first seal member for movement therewith, wherein the first seal member has a rectangular cross-sectional shape when viewed in the circumferential direction that defines an inner surface, an outer surface spaced apart radially from the inner surface, and two side surfaces spaced apart axially that extend radially between the inner surface and the outer surface, and wherein the second seal member extends around a portion of the first seal member so that the second seal member engages the carrier segment and the blade track segment.

8. The turbine shroud assembly of claim 7 , wherein the first seal member is formed to include the inner groove that extends radially into the inner surface of the first seal member and circumferentially relative to the axis and the at least one through hole that extends radially through the first seal member and opens into the inner groove to allow the buffer air to flow through the first seal member into the inner groove.

9. The turbine shroud assembly of claim 1 , wherein the first channel has a rectangular cross-sectional shape viewed circumferentially relative to the axis.

10. The turbine shroud assembly of claim 9 , wherein the first channel defines a first end surface, a first support-wall surface that extends radially inward from the first end surface, and a second support-wall surface that extends radially inward from the first end surface at a location spaced apart axially from the first support-wall surface.

11. A turbine shroud assembly 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 the first support wall formed to include a radially-inwardly opening first channel that extends circumferentially relative to the axis and at least one buffer air passageway that extends radially into the forward support wall and opens into the first channel,

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 arranged in the first channel between the forward support wall of 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, the buffer air seal assembly including a seal that extends circumferentially relative to the axis and axially across the first channel,

wherein the at least one buffer air passageway is configured to discharge buffer air radially inward away from the carrier segment into the first channel to urge the seal radially inward into engagement with the shroud wall of the blade track segment,

wherein the seal includes a first seal member and a second seal member coupled to the first seal member for movement therewith, wherein the first seal member has a rectangular cross-sectional shape when viewed in the circumferential direction that defines an inner surface engaged with the shroud wall of the blade track segment, an outer surface spaced apart radially from the inner surface, and two side surfaces spaced apart axially that extend radially between the inner surface and the outer surface, and wherein the second seal member is arranged axially between a first side surface of the first seal member and the carrier segment, and

wherein the first seal member is formed to include an inner groove that extends radially into the inner surface of the first seal member and circumferentially relative to the axis and at least one through hole that extends radially through the first seal member and opens into the inner groove to allow the buffer air to flow through the first seal member into the inner groove.

12. The turbine shroud assembly of claim 11 , wherein the first seal member is formed to include a side groove that extends axially into a first side surface of the first seal member and circumferentially relative to the axis and the second seal member is arranged in the side groove and engages the carrier segment in the first channel.

13. A method comprising:

providing a carrier segment arranged circumferentially at least partway around an axis, the carrier segment formed to include a radially-inwardly opening first channel and at least one buffer air passageway that extends radially into the carrier segment,

providing a blade track segment arranged circumferentially at least partway around the axis, 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, and the shroud wall formed to include a radially-outwardly opening second channel,

providing a buffer air seal assembly including a seal that extends circumferentially relative to the axis and at least one bias member,

arranging the at least one bias member of the buffer air seal assembly in the first channel formed in the carrier segment,

arranging the seal of the buffer air seal assembly in the first channel formed in the carrier segment so that the bias member is located radially between the carrier segment and the seal,

arranging the blade track segment adjacent to the carrier segment so that the seal engages the shroud wall of the blade track segment, and

discharging a flow of buffer air through the at least one buffer air passageway radially inward away from the carrier segment toward the seal to urge the seal radially inward into engagement with the blade track segment,

wherein the seal is formed to include an inner groove that extends radially inward into the seal and circumferentially relative to the axis and at least one through hole that extends radially through the seal and opens into the inner groove to allow the buffer air to flow through the seal into the inner groove.

14. The method of claim 13 , wherein the seal includes a first seal member and a second seal member, and wherein arranging the seal of the buffer air seal assembly in the first channel formed in the carrier segment includes arranging the second seal member in a side groove formed in the first seal member and arranging the first and second seal members in the first channel formed in the carrier segment after arranging the second seal member in the side groove of the first seal member.

15. The method of claim 13 , wherein the seal includes an outer seal member, a forward seal member, and an aft seal member, and wherein arranging the seal of the buffer air seal assembly in the first channel formed in the carrier segment includes arranging the outer seal member in the first channel so that the at least one bias member is located radially between the carrier segment and the outer seal member, arranging the forward and aft seal members in the first channel after arranging the outer seal member in the first channel, and spacing the aft seal member apart axially from the forward seal member to define the inner groove therebetween.

16. The method of claim 13 , wherein the seal includes a first seal member and a second seal member coupled to the first seal member for movement therewith, wherein the first seal member has a rectangular cross-sectional shape when viewed in the circumferential direction that defines an inner surface, an outer surface spaced apart radially from the inner surface, and two side surfaces spaced apart axially that extend radially between the inner surface and the outer surface, and wherein the second seal member extends around the inner surface of the first seal member.

17. The method of claim 13 , further comprising providing at least one retainer and inserting the at least one retainer axially into the carrier segment and through the attachment feature of the blade track segment to couple the blade track segment to the carrier segment.

Assignments (1)

References Cited (168)