| 摘要 |
PROBLEM TO BE SOLVED: To provide a shroud segment and a shroud assembly of a gas turbine engine formed out of a ceramic matrix composite material. SOLUTION: A radially outer surface 24 of the shroud segment 12 includes opposed first and second edge portion surface depressions 32, 34 spaced circumferentially. The surface depressions have a seal surface 40 shaped to receive a radially outer fluid seal member 44 in a surface depression 36 formed between the segments 12, 14 or the segment and an engine member. The depression seal surface 40 is joined with the radially outer surface 24 of the shroud segment through an arcuate transition surface 42. The surface depressions 32, 34 have a first shape, and the fluid seal member 44 disposed at the depression 32, 34 has a surface 46 of a second shape matched in shape with the first shape. COPYRIGHT: (C)2004,JPO&NCIPI |
