Patent ID: 8813361

Claim:
A method for manufacturing a gas turbine blade in which a part of the blade base material composed of a γ′ phase precipitation strengthened type Ni-based superalloy, comprising the steps of: stripping said blade base material; applying a solution heat treatment in which the γ′ phase of said blade base material is dissolved; welding to form the part composed of a weld metal by welding in an inert gas chamber using a TIG method which uses a welding wire composed of a Ni-base material containing Ta from 4.8 to 5.3 wt. %, Cr from 18 to 23 wt %, Co from 12 to 17 wt %, W from 14 to 18 wt. %, C from 0.03 to 0.1 wt. %, Mo from 1 to 2 wt. % and Al from 1 wt % or less, in which an oxygen content is 0 to 30 ppm, a Ti content is 0 to 0.1 wt. %, and a Re content is 0 to 0.5 wt. %; applying a HIP treatment in which the HIP treatment is performed at a temperature from 1100 to 1150° C. after said welding step; and applying an aging treatment in which the aging treatment is performed at a temperature from 835 to 855° C. after the HIP treatment.