Ceramic matrix composite blade track segment with attachment flange cooling chambers

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

• a blade track assembly including a blade track segment arranged circumferentially at least partway around an axis, the blade track segment including a shroud wall that extends circumferentially partway around the axis, a first attachment flange that extends radially outward from the shroud wall, and a second attachment flange that extends radially outward from the should wall, the second attachment flange spaced apart axially from the first attachment flange, and
• a carrier assembly including a carrier segment arranged circumferentially at least partway around the axis that supports the blade track segment, the carrier segment having an outer wall and an intermediate mount that extends radially inward from the outer wall axially between the first and second attachment flanges of the blade track segment axially between the first and second attachment flanges of the blade track segment,
• wherein the intermediate mount is formed to include a cooling chamber that extends circumferentially partway about the axis and at least one impingement passageway in fluid communication with the cooling chamber such that cooling air conducted into the cooling chamber is directed toward the blade track segment, and
• wherein at least one of the impingement passageways directs the cooling air toward the first attachment flange and at least one of the impingement passageways directs the cooling air toward the second attachment flange.

A method comprising

• providing a blade track segment arranged circumferentially at least partway around an axis, the blade track segment formed to include a shroud wall, a first attachment flange that extends radially outward from the shroud wall, and a second attachment flange that extends radially outward from the should wall,
• providing a carrier assembly including a carrier segment arranged circumferentially at least partway around the axis, the carrier segment formed to include an outer wall, first and second walls that extend radially inward from the outer wall, and an intermediate mount that extends radially inward from the outer wall axially between the first and second walls, wherein the intermediate mount is formed to include a cooling chamber and impingement passageways in fluid communication with the cooling chamber,
• arranging the blade track segment adjacent the carrier segment so that the intermediate mount of the carrier segment is located axially between the first and second attachment flanges of the blade track segment,
• inserting a pin into the first attachment flange of the blade track segment, through the intermediate mount of the carrier segment, and into the second attachment flange of the blade track segment to couple the blade track segment with the carrier segment, and
• conducing a flow of cooling air to the cooling chamber formed in the intermediate mount of the carrier segment so that at least one of the impingement passageways directs the flow of cooling air toward the first attachment flange of the blade track segment and at least one of the impingement passageways directs the flow of cooling air toward the second attachment flange of the blade track segment to cool the blade track segment.