| 摘要 |
<p>A tip clearance control device for a gas turbine engine having a shroud (20) surrounding a stage of rotor blades (24). The tip clearance control device comprises a one-piece split ring having opposed overlapping end portions (26-27). The split ring is directly supported onto the inner surface (46) of the shroud and is adapted to automatically adjust for thermal growth of the shroud during engine operation.</p> |
