Casing for supporting series of fixed vanes in high pressure axial compressor of turbojet of aircraft, has blades, where radial external end of blades passes through whole of opposite areas of casing devoid of spiral grooves

摘要

The casing (24) has a set of crowns (24A-24C) that is located with regard to a series of mobile blades (22), where the set of crowns is covered with an abrasive material at a casing treatment zone that faces a radial external end of the series of mobile blades. The casing treatment zone comprises spiral grooves (30) that are arranged such that the radial external end of the blades passes through whole of opposite areas of the casing devoid of spiral grooves for each complete rotation of the blades. An independent claim is also included for a high pressure axial compressor.