Turbine shroud assembly with carrier cooling holes for carrier aft flange
A turbine shroud assembly includes a blade track having a shroud wall, and a carrier segment having an aft support wall with at least one axially aft-facing surface. The carrier segment further includes at least one cooling air plenum formed in the aft support wall and at least one cooling air passageway in fluid communication with and extending away from the at least one cooling air plenum through the aft support wall, the at least one cooling air passageway opening at the at least one axially aft-facing surface of the aft support wall so as to conduct cooling air through the carrier segment and direct the cooling air out of the carrier segment so as to cool at least one portion of the aft support wall.
1 . A turbine shroud assembly for use with a gas turbine engine, the turbine shroud assembly comprising
a blade track segment made of ceramic matrix composite materials and arranged circumferentially at least partway around an axis to define a portion of a gas path of the turbine shroud assembly, the blade track segment having a shroud wall that extends circumferentially partway around the axis, and
a carrier segment made of metallic materials that supports the blade track segment to locate the blade track segment radially outward of the axis and arranged circumferentially at least partway around the axis, the carrier segment including an outer wall, a forward support wall that extends radially inward from the outer wall, and an aft support wall that extends radially inward from the outer wall that is located axially aft of the forward support wall, the aft support wall including at least one axially aft-facing surface,
wherein the carrier segment further includes at least one cooling air plenum formed in the aft support wall and at least one cooling air passageway in fluid communication with and extending away from the at least one cooling air plenum through the aft support wall, the at least one cooling air passageway opening at the at least one axially aft-facing surface of the aft support wall so as to conduct cooling air through the carrier segment and direct the cooling air out of the carrier segment so as to cool at least one portion of the aft support wall.
2 . The turbine shroud assembly of claim 1 , wherein the aft support wall includes a main wall having a first end connected to the outer wall and a second end opposite of and radially spaced apart from the first end, and wherein the at least one axially aft-facing surface is a first axially aft-facing surface of the main wall.
3 . The turbine shroud assembly of claim 2 , wherein the at least one cooling air passageway includes an outlet opening formed in the first axially aft-facing surface of the main wall of the aft support wall.
4 . The turbine shroud assembly of claim 3 , wherein the aft support wall further includes an aft support wall flange that extends axially aft away from the first axially aft-facing surface of the main wall at the second end of the main wall, and wherein the cooling air directed out of the outlet opening of the at least one cooling air passageway flows onto a radially outwardly-facing surface of the aft support wall flange so as to cool the aft support wall flange.
5 . The turbine shroud assembly of claim 4 , wherein the at least one cooling air passageway extends at least partially radially inwardly from the at least one cooling air plenum to the outlet opening formed in the first axially aft-facing surface of the main wall of the aft support wall such that the cooling air is directed at least partially radially inwardly as it exits the outlet opening and towards the radially outwardly-facing surface of the aft support wall flange.
6 . The turbine shroud assembly of claim 5 , wherein the at least one cooling air passageway includes an inlet opening formed in a side wall or a bottom surface of the at least one cooling air plenum, and wherein the inlet opening is located axially forward of the outlet opening such that the at least one cooling air passageway extends at an angle relative to the axis.
7 . The turbine shroud assembly of claim 6 , wherein the at least one cooling air passageway includes a plurality of cooling air passageways that each include an outlet opening formed in the first axially aft-facing surface of the main wall of the aft support wall, and wherein each outlet opening of the plurality of cooling air passageways is circumferentially spaced apart from adjacent outlet openings of the plurality of cooling air passageways.
8 . The turbine shroud assembly of claim 7 , wherein the at least one cooling air plenum includes a plurality of cooling air plenums, and wherein a first cooling air passageway of the plurality of cooling air passageways extends from a first cooling air plenum of the plurality of cooling air plenums and a second cooling air passageway of the plurality of cooling air passageways extends from a second cooling air plenum of the plurality of cooling air plenums.
9 . The turbine shroud assembly of claim 2 , wherein the aft support wall further includes an aft support wall flange that extends axially aft away from the first axially aft-facing surface of the main wall at the second end of the main wall, and wherein an axially aft end of the aft support wall flange includes a second axially aft-facing surface that is axially spaced apart from the first axially aft-facing surface in an axially aft direction, and wherein the at least one cooling air passageway extends through the aft support wall flange and includes an outlet opening formed in the second axially aft-facing surface such that the cooling air flows through the aft support wall flange so as to cool the aft support wall flange.
10 . The turbine shroud assembly of claim 9 , wherein the at least one cooling air passageway includes a first portion that extends at least partially radially inwardly from and is in fluid communication with the at least one cooling air plenum and a second portion that extends at least partially axially from and is in fluid communication with the first portion and to the outlet opening formed in the second axially aft-facing surface of the aft support wall flange.
11 . The turbine shroud assembly of claim 10 , wherein the first portion of the at least one cooling air passageway extends in a radial direction and the second portion of the at least one cooling air passageway extends in an axial direction such that an orthogonal angle is formed at a junction between the first and second portions.
12 . The turbine shroud assembly of claim 11 , wherein the at least one cooling air passageway includes a plurality of cooling air passageways that each include an outlet opening formed in the second axially aft-facing surface of the aft support wall flange of the aft support wall, and wherein each outlet opening of the plurality of cooling air passageways is circumferentially spaced apart from adjacent outlet openings of the plurality of cooling air passageways.
13 . The turbine shroud assembly of claim 12 , wherein the at least one cooling air plenum includes a plurality of cooling air plenums, and wherein a first cooling air passageway of the plurality of cooling air passageways extends from a first cooling air plenum of the plurality of cooling air plenums and a second cooling air passageway of the plurality of cooling air passageways extends from a second cooling air plenum of the plurality of cooling air plenums.
14 . A turbine shroud assembly for use with a gas turbine engine, the turbine shroud assembly comprising
a blade track segment arranged circumferentially at least partway around an axis, the blade track segment having a shroud wall that extends circumferentially partway around the axis, the shroud wall including an aft flange at an aft end of the shroud wall, and
a carrier segment that supports the blade track segment and is arranged circumferentially at least partway around the axis, the carrier segment including an aft support wall, the aft support wall including at least one axially aft-facing surface,
wherein the carrier segment further includes a cooling air plenum formed in the aft support wall and a cooling air passageway in fluid communication with and extending away from the cooling air plenum, the cooling air passageway opening at the at least one axially aft-facing surface of the aft support wall so as to cool at least one portion of the aft support wall.
15 . The turbine shroud assembly of claim 14 , wherein the aft support wall includes a main wall, wherein the at least one axially aft-facing surface is a first axially aft-facing surface of the main wall, and wherein the at least one cooling air passageway includes an outlet opening formed in the first axially aft-facing surface of the main wall of the aft support wall.
16 . The turbine shroud assembly of claim 15 , wherein the at least one cooling air passageway extends at least partially radially inwardly from the at least one cooling air plenum to the outlet opening formed in the first axially aft-facing surface of the main wall of the aft support wall such that the cooling air is directed at least partially radially inwardly as it exits the outlet opening.
17 . The turbine shroud assembly of claim 14 , wherein the aft support wall includes a main wall, wherein the at least one axially aft-facing surface is a first axially aft-facing surface of the main wall, wherein the aft support wall further includes an aft support wall flange that extends axially aft away from the first axially aft-facing surface of the main wall, wherein an axially aft end of the aft support wall flange includes a second axially aft-facing surface that is axially spaced apart from the first axially aft-facing surface in an axially aft direction, and wherein the at least one cooling air passageway extends through the aft support wall flange and includes an outlet opening formed in the second axially aft-facing surface.
18 . The turbine shroud assembly of claim 17 , wherein the at least one cooling air passageway includes a first portion that extends at least partially radially inwardly from and is in fluid communication with the at least one cooling air plenum and a second portion that extends at least partially axially from and is in fluid communication with the first portion and to the outlet opening formed in the second axially aft-facing surface of the aft support wall flange.
19 . The turbine shroud assembly of claim 14 , wherein the at least one cooling air passageway includes a plurality of cooling air passageways that each include an outlet opening formed in the at least one axially aft-facing surface of the aft support wall, and wherein each outlet opening of the plurality of cooling air passageways is circumferentially spaced apart from adjacent outlet openings of the plurality of cooling air passageways.
20 . A method, comprising
arranging a blade track segment made of ceramic matrix composite materials and arranged circumferentially at least partway around an axis to define a portion of a gas path of a turbine shroud assembly, the blade track segment having a shroud wall that extends circumferentially partway around the axis,
arranging a carrier segment made of metallic materials circumferentially at least partway around the axis, the carrier segment supporting the blade track segment to locate the blade track segment radially outward of the axis, the carrier segment including an outer wall, a forward support wall that extends radially inward from the outer wall, and an aft support wall that extends radially inward from the outer wall that is located axially aft of the forward support wall, the aft support wall including at least one axially aft-facing surface,
forming at least one cooling air plenum in the aft support wall of the carrier segment, and
forming at least one cooling air passageway in the carrier segment, the at least one cooling air passageway being in fluid communication with and extending away from the at least one cooling air plenum through the aft support wall, the at least one cooling air passageway opening at the at least one axially aft-facing surface of the aft support wall such that the at least one cooling air passageway is configured to conduct cooling air through the carrier segment and direct the cooling air out of the carrier segment so as to cool at least one portion of the aft support wall.