METHOD FOR PRODUCING PRODUCTS FROM METAL MATERIAL, METHOD FOR PRODUCING PART COATED AND BLADE OF A GAS-TURBINE ENGINE WITH COATING

摘要

1. A blade of a gas turbine engine containing a platform, a shank extending from the platform downwards, an aerodynamic surface having leading and trailing edges, sides of increased pressure and reduced pressure, characterized in that it contains a substrate with a compressive stress under the first zone of the substrate surface extending over a greater parts of the perimeter of the airfoil in the direction of the flow in the area at a distance from the tip along the span of the blade, which is more than 50% of the local distance "tip-platform", and a coating on at least part of the first surface area, the area including the mentioned area. A blade according to claim 1, characterized in that said first zone comprises most of the span of the blade along the leading edge. A blade according to claim 1, characterized in that the coating is applied mainly over the entire first zone. A blade according to claim 1, characterized in that the first zone occupies essentially the entire outer part of the aerodynamic surface of the section. A blade according to claim 1, characterized in that the coating comprises at least one coating from the group consisting of CoWC and NiCr-CrC. A blade according to claim 1, characterized in that it is a compressor blade. A method of manufacturing an article from a metal material containing a substrate and an erosion-resistant coating, characterized in that the length of the substrate zone is selected to perform smoothing with a reduction in the effect of fatigue due to the effect of the coating, the zone is deformed by roller rolling, and then the coating is applied. The method according to claim 7, characterized in that the size of the zone exceeds the size of the coated zone. The method according to claim 7, characterized in that the zones