Method for manufacturing a coated compressor blade

摘要

The invention relates to a gas turbine engine blade (40) and a method of making an article of a metallic material, the article comprising a substrate and an erosion coating (70).
The gas turbine engine blade (40) has a platform (44). A root (46) depends from the platform (44) and an airfoil (42) extends from the platform (44). The airfoil (42) has leading and trailing edges (48,50) and pressure and suction sides (52,54). The blade (40) has a substrate having a surface. A compressive stress exists below a first region of the surface. The first region extends over a majority of a streamwise perimeter of the airfoil at a location at a spanwise distance from the tip or more than 50% of a tip-to-platform span. A coating (70) is on the surface including at the location.