| 主权项 |
1. A turbine shroud apparatus for a gas turbine engine, comprising:
(a) 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 at least a portion of each of the forward and aft walls is oriented at an acute angle to the outer wall, and wherein radially inner ends of the forward and aft walls are substantially closer together than radially outer ends thereof; and (b) an annular stationary structure including substantially rigid annular forward and aft bearing surfaces which bear directly against the forward and aft walls, respectively, of the shroud segment, so as to restrain the shroud segments from axial movement and radially inward movement relative to the stationary structure, wherein one of the bearing surfaces includes at least one tab extending therefrom, each of the at least one tabs received in a notch formed in one of the shroud segments so as to prevent relative rotation of the shroud segment and the stationary structure.
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