| 摘要 |
An arrangement for a gas turbine engine comprises a compressor and its surrounding casing. The casing has a generally cylindrical inner surface, one cylindrical section of the inner casing being provided with a circumferential array of recesses. An axially adjacent cylindrical section of the inner casing surface is provided with an abradable lining. The tips of the rotor blades of the compressor are provided with a treated portion at least partly axially aligned with the recesses in the inner casing, the remaining untreated portion of the rotor blade tips being at least partly axially aligned with the lined section of the inner casing. |
