US Patent 11021990 Shroud sealing for a gas turbine engine

A shroud assembly for gas turbine engine defining an axial direction, a radial direction, and a circumferential direction includes a shroud segment extending substantially along the circumferential direction and including a forward wall and an aft wall spaced along the axial direction from one another and defining a cavity therebetween; and a hanger assembly including a first attachment member and a seal member, the first attachment member attached to one of the forward wall or the aft wall of the shroud segment, and the seal member positioned within the cavity and interference fit against the other of the forward wall or the aft wall of the shroud segment.