Patent ID: 7509736

Claim:
A process for repairing a metallic shroud of a gas turbine blade comprising an anti-wear layer of cobalt-based alloy over a metallic substrate, wherein said shroud has a leading edge and a trailing edge oriented transversely relative to a direction of flow of gas, the two edges being connected by two lateral edges that have a Z profile with two axial portions interconnected by a substantially transversal portion, said process comprising the steps of: removing a portion of said anti-wear layer of cobalt-based alloy to a removal depth that is greater than a depth of wear of said anti-wear layer; leaving a trace of said anti-wear layer of cobalt-based alloy to subsist above said metallic substrate, wherein said trace of said anti-wear layer extends at least in a re-entrant zone of the Z profile; and applying drops of said cobalt-based alloy to contact said trace thereby soldering a new layer of anti-wear material of cobalt-based alloy on said trace of said anti-wear layer, wherein said removing step is performed such that said trace has a shape that ensures that said drops of the cobalt-based alloy are not brought into a zone free of said trace of cobalt-based alloy.