| 摘要 |
The invention relates to a compressor shroud for an aircraft turbomachine, said shroud (20) being arranged between two rotating bladed wheels (16) and radially perpendicularly to a stator (12), and comprising a sealing device (30) comprising at least one sealing element (32), one of which is a downstream sealing element (32a) whereon a downstream-projecting structure (44) for driving and deviating air is provided, said structure being designed to axially straighten the discharge air coming from the sealing element (32a). |
