Turbine shroud assemblies with air activated buffer cavity seals

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 forward support wall that extends radially inward from the outer wall, and an aft support wall that extends radially inward from the outer wall at a location spaced apart axially from the forward support wall to define an attachment-receiving space,
• 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 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 first seal member that extends radially into the carrier segment and the blade track segment and a second seal member that extends radially into the carrier segment and the blade track segment, the second seal member spaced apart axially from the first seal member to define a buffer chamber axially therebetween,
• wherein the carrier segment is formed to include at least one buffer air passageway configured to discharge buffer air radially inward away from carrier segment into the buffer chamber axially between the first seal member and the second seal member to pressurize the buffer chamber to urge the first seal member axially forward and the second seal member axially aft away from each other and into engagement with radially-extending surfaces defined by the carrier segment and the blade track segment.