| 摘要 |
A turbine shroud apparatus for a gas turbine engine includes: a plurality of arcuate shroud segments (24, 124) arranged forming an annular shroud, each of the shroud segments (24, 124) comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls (38, 138, 40, 140), and opposed inner and outer walls (34, 134, 36, 136), the walls extending between opposed first and second end faces. At least a portion of each of the forward and aft walls (38, 138, 40, 140) is oriented at an acute angle to the outer wall (36, 136), and radially inner ends of the forward and aft walls (3 8, 13 8, 40, 140) are substantially closer together than radially outer ends thereof. An annular stationary structure includes substantially rigid annular forward and aft bearing surfaces (70, 60) which bear against the forward and aft walls (38, 138, 40, 140), respectively, of the shroud segment (24, 124), so as to restrain the shroud segments (24, 124) from axial movement and radially inward movement relative to the stationary structure.
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