Methods and devices able to reduce the stresses on the tips of the blades of turbine or compressor, as well as the motors or compressors, using such processes and devices.

摘要

A blade according to the invention is intended to be used in a turbine engine where the blade comes into contact with a circumferential seal. & br / the blade (20) comprises a base and a tip (29), the tip comprising the upstream edges (24) and downstream (26), the opposite surfaces (27) and a central portion defined by the upstream and downstream edges and the opposite surfaces, as well as a chamfer (30) which is disposed at the intersection of at least one of the opposite surfaces (27) and the central part, where there are high stresses and which extends at least partially between the upstream and downstream edges; the blade further includes an abrasive lining (46) arranged at the central part of the blade (20) and extending at least partially between the upstream and downstream edges (24, 26). br / the application of the gas turbine engines having a very small clearance between the rotating blades and a circumferential seal.