Patent ID: 6551064
Filing Date: 2003-04-22
Classification: C21D,F01D,Y02T,Y10T

Abstract:
An article comprising:an intermetallic body, at least one laser shock peened surface on at least a portion of said intermetallic body, a region having compressive residual stresses imparted by laser shock peening extending into said intermetallic body from said laser shock peened surface, wherein said article is a gas turbine engine component comprising: an intermetallic airfoil having a leading edge and a trailing edge and a pressure side and a suction side, at least one laser shock peened surface on at least one of said sides of said airfoil, said laser shock peened surface extending radially along at least a portion of said leading edge and extending chordwise from said leading edge, and a region having compressive residual stresses imparted by laser shock peening extending into said airfoil from said laser shock peened surface.