Strip For Abradable In A Compressor Turbine

Abstract

The invention relates to a sealing device of an axial turbomachine, comprising a circular strip with an outer surface and an inner surface; an annular layer of abradable material on one of the outer and inner surfaces of the strip, designed to provide a sealing with an annular row of rotor blades. The surface of the strip covered by the abradable layer comprises at least two perforated circular zones, each with a series of distributed perforations. The surface of the strip covered by the abradable layer further comprises a smooth circular zone disposed axially between the perforated areas. The smooth zone is centered on the outer ends of the rotor blades. The invention improves the adhesion of the abradable layer on the metal strip, and avoids a premature breakdown of the abradable layer in contact with the rotor blades, despite the presence of perforations.

Dependencies are inferred from the claim text.