Patent ID: 8641371

Claim:
A turbine shroud attached to an inner circumferential surface of a turbine casing and surrounding tips of turbine rotor blades in a gas turbine engine coaxially with respect to a center line of the engine, the turbine shroud comprising a plurality of arcuate shroud segments combined into an annular configuration, each shroud segment including a main body defining an inner circumferential surface opposing the tips of the turbine rotor blades at a small clearance and an engagement feature including an axial wall having a prescribed circumferential length and a prescribed axial length, the turbine casing including an axial slot extending coaxially around the center line of the engine and configured to receive the axial wall of each shroud segment, wherein a clearance defined between each circumferential end part of an inner circumferential surface of the axial wall and an opposing outer circumferential surface of the turbine casing is smaller than that defined between a circumferentially middle part of the inner circumferential surface of the axial wall and an opposing outer circumferential surface of the turbine casing, under a cool condition of the engine.