Turbine shroud assemblies with retainer features for blocking seal migration

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

• a carrier segment made of metallic materials and 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 is formed to include a recess that opens radially inwardly and extends circumferentially at least partway around the axis, and a first cantilevered wall extending radially inwardly from a top wall of the recess and spaced apart from opposing inner walls of the recess so as to form a first groove between a first inner wall of the recess and a first outer wall of the first cantilevered wall that faces the first inner wall, the first cantilevered wall and the first groove extending circumferentially at least partway around the axis, the carrier segment further including at least one buffer air passageway that extends radially through the first support wall and the first cantilevered wall and is configured to discharge high-pressure buffer air,
• a blade track segment made of ceramic matrix composite materials and including a shroud wall that extends circumferentially partway around the axis and an attachment feature coupled to the carrier segment, and
• a buffer air seal assembly located radially between the carrier segment and the shroud wall of the blade track segment and including a first tandem seal arranged in the first groove, wherein the first tandem seal includes first, second, and third seal members that each extend circumferentially at least partway about the axis, wherein the second and third seal members are aligned with each other, circumferentially spaced apart, and arranged radially outward of the first seal member, wherein the first cantilevered wall further includes a main portion having a first axial width and a barrier portion having a second axial width greater than the first axial width such that a first axial extension of the barrier portion extends at least partially into the first groove, and wherein the second and third seal members are arranged on opposing circumferential sides of the barrier portion such that the barrier portion blocks circumferential movement of the second and third seal members.