| 摘要 |
A shroud apparatus for a gas turbine engine includes: a shroud segment (18) comprising low-ductility material and having a cross-sectional shape defined by opposed forward (24) and aft (26) walls, and opposed inner (20) and outer (22) walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface (32), wherein the shroud segment (18) includes: a radially-inward facing chordal forward mounting surface (36); and a radially-inward facing chordal aft mounting surface (40); and an annular case (48) surrounding the shroud segment (18), the case including: a radially-outward facing chordal forward bearing surface (58) which engages the forward mounting surface (36); and a radially-outward facing chordal aft bearing surface (68) which engages the aft mounting surface (40) of the shroud segment. |
