Axial locating features for blade track segments in turbine shroud assemblies

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

Assignee: Rolls-Royce Corporation

F01D25/246 F05D2260/30

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Quick Facts

Patent No.: US 12680476
App. No.: 19/287,171
Granted: Jul 14, 2026
Kind: B1

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Abstract

A turbine shroud assembly includes a carrier segment, a blade track segment, and a locating feature. The carrier segment includes an outer wall, a first flange that extends radially inward from the outer wall, and a second flange axially spaced apart from the first flange and extending radially inward from the outer wall. The blade track segment includes a shroud wall and a first attachment flange that extends radially outward from the shroud wall. The locating feature extends axially forward from the second flange of the carrier segment to engage the first attachment flange of the blade track segment to axially locate the blade track segment relative to the carrier segment.

Claims (29)

1 . A turbine shroud assembly for use with a gas turbine engine, the turbine shroud assembly comprising:

a carrier segment arranged to extend circumferentially at least partway around an axis, the carrier segment including an outer wall, a first flange that extends radially inward from the outer wall, and a second flange axially spaced apart from the first flange and extending radially inward from the outer wall,

a blade track segment supported by the carrier segment to define a portion of a gas path of the turbine shroud assembly, the blade track segment including a shroud wall that extends circumferentially partway around the axis and a first attachment flange that extends radially outward from the shroud wall, the first attachment flange formed to define a first recess that extends axially forward into the first attachment flange toward the first flange of the carrier segment and a second recess circumferentially spaced apart from the first recess and extending axially forward into the first attachment flange toward the first flange of the carrier segment, and

a locating feature engaged with the blade track segment to axially locate the blade track segment relative to the carrier segment so that an axial position of the blade track segment relative to the carrier segment is maintained during use of the turbine shroud assembly, the locating feature extending axially forward from the second flange of the carrier segment into the first recess formed in the first attachment flange of the blade track segment to engage the first attachment flange of the blade track segment.

2 . The turbine shroud assembly of claim 1 , wherein the locating feature is a first locating feature, and wherein the turbine shroud assembly further includes a second locating feature circumferentially spaced apart from the first locating feature and extending axially forward from the second flange of the carrier segment into the second recess formed in the first attachment flange of the blade track segment to engage the first attachment flange of the blade track segment.

3 . The turbine shroud assembly of claim 1 , wherein the locating feature is integrally formed with the carrier segment.

4 . The turbine shroud assembly of claim 1 , wherein the blade track segment further includes a second attachment flange axially spaced apart from the first attachment flange and extending radially outward from the shroud wall, and wherein the carrier segment further includes a third flange located axially between the first flange and the second flange and extending radially inward from the outer wall and a fourth flange located axially between the third flange and the second flange and extending radially inward from the outer wall.

5 . The turbine shroud assembly of claim 4 , wherein the first attachment flange of the blade track segment is located axially between the fourth flange and the second flange of the carrier segment, and the second attachment flange of the blade track segment is located axially forward of the first attachment flange and axially between the first flange and the third flange of the carrier segment.

6 . The turbine shroud assembly of claim 1 , wherein the first attachment flange of the blade track segment defines an axially-forward facing surface facing toward the first flange of the carrier segment and an axially-aft facing surface facing toward the second flange of the carrier segment, and wherein the first recess extends into the first attachment flange from the axially-aft facing surface toward the axially-forward facing surface.

7 . The turbine shroud assembly of claim 1 , wherein the first recess is open on a circumferential end of the first attachment flange.

8 . The turbine shroud assembly of claim 1 , further comprising a mount pin that extends axially forward into the second flange of the carrier segment, through the first attachment flange of the blade track segment, and into the first flange of the carrier segment so as to couple the blade track segment to the carrier segment.

9 . The turbine shroud assembly of claim 8 , wherein the locating feature is located circumferentially between the mount pin and a circumferential end of the turbine shroud assembly.

10 . The turbine shroud assembly of claim 1 , wherein the locating feature includes a ridge that extends axially forward and radially outwardly along the second flange of the carrier segment and a protrusion that extends axially forward from a radial outer portion of the ridge to engage the first attachment flange.

11 . A turbine shroud assembly for use with a gas turbine engine, the turbine shroud assembly comprising:

a locating feature engaged with the blade track segment to axially locate the blade track segment relative to the carrier segment, the locating feature including (i) a ridge that extends axially forward from the second flange of the carrier segment and radially outwardly along the second flange and (ii) a protrusion that extends axially forward from a radial outer portion of the ridge to engage the first attachment flange of the blade track segment.

12 . The turbine shroud assembly of claim 11 , wherein the protrusion of the locating feature extends into the first recess to engage the first attachment flange of the blade track segment.

13 . The turbine shroud assembly of claim 12 , wherein the first attachment flange of the blade track segment defines an axially-forward facing surface facing toward the first flange of the carrier segment and an axially-aft facing surface facing toward the second flange of the carrier segment, and wherein the first recess extends into the first attachment flange from the axially-aft facing surface toward the axially-forward facing surface.

14 . The turbine shroud assembly of claim 12 , wherein the first recess is open on a circumferential end of the first attachment flange.

15 . The turbine shroud assembly of claim 11 , wherein the locating feature is integrally formed with the carrier segment.

16 . The turbine shroud assembly of claim 11 , wherein the blade track segment further includes a second attachment flange axially spaced apart from the first attachment flange and extending radially outward from the shroud wall, and wherein the carrier segment further includes a third flange located axially between the first flange and the second flange of the carrier segment and extending radially inward from the outer wall and a fourth flange located axially between the third flange and the second flange of the carrier segment and extending radially inward from the outer wall.

17 . The turbine shroud assembly of claim 11 , further comprising a mount pin that extends axially forward into the second flange of the carrier segment, through the first attachment flange of the blade track segment, and into the first flange of the carrier segment so as to couple the blade track segment to the carrier segment, and wherein the locating feature is located circumferentially between the mount pin and a circumferential end of the turbine shroud assembly.

18 . A method comprising:

coupling a blade track segment with a carrier segment to support the blade track segment radially inward of the carrier segment, the carrier segment including an outer wall, a first flange that extends radially inward from the outer wall, and a second flange axially spaced apart from the first flange and extending radially inward from the outer wall, the blade track segment including a shroud wall and a first attachment flange that extends radially outward from the shroud wall and is formed to define a first recess that extends axially forward into the first attachment flange and a second recess circumferentially spaced apart from the first recess and extending axially forward into the first attachment flange,

positioning a protrusion of a locating feature in the first recess of the first attachment flange, the locating feature extending axially forward from the second flange of the carrier segment, and

engaging the first attachment flange of the blade track segment with the protrusion of the locating feature to axially locate the blade track segment relative to the carrier segment.

19 . The method of claim 18 , further comprising inserting a mount pin axially forward through the second flange, through the first attachment flange, and into the first flange so as to couple the blade track segment to the carrier segment, and wherein the locating feature is located circumferentially between the mount pin and a circumferential end of the carrier segment.

20 . The method of claim 18 , further comprising positioning a second protrusion of a second locating feature in the second recess of the first attachment flange, the second locating feature extending axially forward from the second flange of the carrier segment.