Turbine shroud assembly with radially and axially biased ceramic matrix composite shroud segments

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

• a shroud segment comprising ceramic matrix composite materials, the shroud segment including a shroud wall that extends circumferentially partway around an axis to define a gas path boundary of the turbine shroud assembly and a first attachment feature that extends radially outward away from the shroud wall,
• a carrier comprising metallic materials and configured to support the shroud segment in position radially relative to the axis, the carrier including a carrier segment and a pin that extends axially into the carrier segment of the carrier and the first attachment feature of the shroud segment to couple the shroud segment to the carrier segment, and the carrier segment having a body and an axial location feature that extends circumferentially along and axially forward from the body and engages the first attachment feature of the shroud segment, and
• a retainer system including a first bias member that extends circumferentially at least partway around the axis, the first bias member located axially forward of the first attachment feature of the shroud segment and located radially between the shroud wall and the carrier segment so as to apply a first bias force to the shroud segment in a radially inward direction to minimize radial movement of the shroud segment relative to the carrier and in an axially aft direction to axially locate the shroud segment on the axial location feature of the carrier segment during use of the turbine shroud assembly.