MANUFACTURING PROCESS OF Ni BASED SUPERALLOY MEMBER, BOILER TUBE, COMBUSTOR LINER, GAS TURBINE BLADE, AND GAS TURBINE DISK

Abstract

The solution-aging step for obtaining a Ni based superalloy member by performing a solution treatment for solid-dissolving a gamma prime incoherent phase and an aging treatment for re-precipitating a gamma prime coherent phase after the working step.

What is claimed is: 
     
         1 . A manufacturing process of a Ni based superalloy member comprising:
 a working step for working the Ni based superalloy softening material into a desired shape, wherein the composition of the Ni based superalloy contains, in mass %, 10% or more and 25% or less of Cr, 30% or less of Co, 3% or more and 9% or less of the total of Ti, Nb and Ta, 1% or more and 6% or less of Al, 10% or less of Fe, 10% or less of Mo, 8% or less of W, 0.03% or less of B, 0.1% or less of C, 0.08% or less of Zr, 2.0% or less of Hf, and 5.0% or less of Re, with the balance including Ni and inevitable impurities,   vickers hardness at the room temperature of the Ni based superalloy softening material is 400 or less, 0.2% proof stress at 900° C. is 250 MPa or less, and a solvus of the gamma prime phase is 1,050° C. or above; and   a solution-aging step for obtaining a Ni based superalloy member by performing a solution treatment for solid-dissolving a gamma prime incoherent phase and an aging treatment for re-precipitating a gamma prime coherent phase after the working step.   
     
     
         2 . The manufacturing process of a Ni based superalloy member according to  claim 1 , wherein the solution-aging step precipitating the gamma prime coherent phase by 30 vol % or more at 700° C. 
     
     
         3 . The manufacturing process of a Ni based superalloy member according to  claim 1 , further comprising forming a boiler tube using the Ni based superalloy member produced according to  claim 1 . 
     
     
         4 . The manufacturing process of a Ni based superalloy member according to  claim 1 , further comprising forming a combustor liner using the Ni based superalloy member produced according to  claim 1 . 
     
     
         5 . The manufacturing process of a Ni based superalloy member according to  claim 1 , further comprising forming a gas turbine blade using the Ni based superalloy member produced according to  claim 1 . 
     
     
         6 . The manufacturing process of a Ni based superalloy member according to  claim 1 , further comprising forming a gas turbine disk using the Ni based superalloy member produced according to  claim 1 .