Insert-mounted turbine assembly for a gas turbine engine

A turbine assembly adapted for use in a gas turbine engine, the turbine assembly comprising

• a seal segment comprising ceramic matrix composite materials, the seal segment including a shroud wall that extends circumferentially partway around an axis to define a gas path boundary of the turbine assembly and a mount post that extends radially outward away from the shroud wall,
• a carrier comprising metallic materials and configured to support the seal segment in position radially relative to the axis, the carrier including an outer wall that extends circumferentially at least partway about the axis, a first attachment flange that extends radially inward from the outer wall, and a second attachment flange that extends radially inward from the outer wall and spaced apart axially from the first attachment flange to define a radially inwardly opening channel that receives the mount post of the seal segment, and
• a mounting insert coupled with the carrier and engaged with the mount post of the seal segment to bias the seal segment into engagement with the carrier with a predetermined force, the mounting insert including an insert body fixed to the first attachment flange, a protrusion that extends axially between a first end coupled with the insert body and a second end engaged with the mount post of the seal segment to define a receiving space between the first end and the second end of the protrusion, and a bias member located in the receiving space and engaged with the insert body and the mount post to apply a force to the mount post and limit axial movement of the seal segment relative to the carrier,
• wherein the receiving space has a predetermined axial length between the first end and the second end of the protrusion to control an amount of compression of the bias member between the insert body and the mount post so that the force applied by the bias member to the seal segment is within a predetermined force threshold range.