| 摘要 |
A turbine shroud segment 24, for a gas turbine engine, comprises low-ductility material (preferable a ceramic matrix composite) and has a cross-sectional shape defined by opposed forward and aft walls 38, 40, and opposed inner and outer walls 34, 36, the walls extending between opposed first and second end faces. At least a portion of each of the forward and aft walls is oriented at an acute angle to the outer wall, and radially inner ends of the forward and aft walls are substantially closer together than radially outer ends thereof. The shroud segment may be one of a plurality of segments in a turbine shroud. An annular stationary structure may include substantially rigid annular forward and aft bearing surfaces 70, 60 which bear against the forward and aft shroud segment walls respectively, so as to restrain the shroud segments from axial movement and radially inward movement relative to the stationary structure.
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