Patent ID: 6575702
Filing Date: 2003-06-10
Classification: B23P,F01D,F05C,F05D,Y02T,Y10T

Abstract:
A method for repairing a gas turbine airfoil, comprising:a. providing an airfoil having specified nominal dimensions, said airfoil comprising a first material, said first material having a creep life and a fatigue life, said airfoil further comprising a leading edge section and a trailing edge section; b. removing at least one portion of at least one section of said airfoil to create at least one deficit of material for said airfoil relative to said specified nominal dimensions, said at least one section selected from the group consisting of the leading edge section and the trailing edge section; c. providing at least one insert comprising a second material, said second material having at least one of (1) a creep life that is at least about three times greater than said creep life of said first material, and (2) a fatigue life that is at least three times greater than said fatigue life of said first material; and d. disposing said at least one insert onto said airfoil such that said at least one deficit of material is substantially eliminated.