| 摘要 |
<p>A vane assembly (20) for a gas turbine engine including a shroud ring (34) with openings (54) and isolating means (28) isolating a vane extremity (24) within each opening (54), the isolating means (28) cooperating to form a continuous gas path surface (52) completely covering at least an axial portion of a surface (37) of the shroud ring (34).</p> |
