Patent ID: 8905709

Claim:
A turbine shroud apparatus for a gas turbine engine, comprising: a plurality of arcuate shroud segments arranged to form an annular shroud, each of the shroud segments comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein an open channel is formed through the outer wall of each shroud segment, wherein the open channel is shorter than the shroud segment in a circumferential direction, and the shroud segment includes offset stub walls extending radially inward from each of the forward and aft walls; an annular stationary structure surrounding the shroud segments; and a hanger received in the open channel of each shroud segment, each of the hangers passing through the respective open channel and having a T-shaped cross section comprising a central portion extending through the open channel and contacting the annular stationary structure, the central portion being flanked by at least one laterally-extending rail which engages the outer wall of the respective shroud segment, so as to retain the shroud segment in a radial direction relative to the stationary structure, wherein the central portion of each hanger is mechanically coupled to the stationary structure by a mechanical fastener.