Gas turbine rotor component and method of manufacture

Abstract

A turbine rotor disk and a method of making the turbine rotor disk using solid state bonding techniques are disclosed. The turbine rotor disk includes a radially inner portion comprising a wrought nickel alloy having a yield strength of at least 126 ksi at 1,000° F. The turbine rotor disk also includes a radially outer portion bonded to the radially inner portion, said radially outer portion comprising a cast nickel alloy configured as a single crystal or with a grain size of ASTM 2 or larger.

What is claimed is: 
     
         1 . A turbine rotor disk, comprising:
 a radially inner portion comprising a wrought nickel alloy having a yield strength of at least 126 ksi at 1,000° F.; and   a radially outer portion bonded to the radially inner portion, said radially outer portion comprising a cast nickel alloy configured as a single crystal or with a grain size of ASTM 2 or larger.   
     
     
         2 . The turbine rotor disk of  claim 1 , wherein a second preform comprises the cast nickel alloy configured as a single crystal. 
     
     
         3 . The turbine rotor disk of  claim 1 , wherein a second preform comprises the cast nickel alloy configured with a grain size of ASTM 2 or larger. 
     
     
         4 . The turbine rotor disk of  claim 3 , wherein the second preform has a grain size of ASTM 1 or larger. 
     
     
         5 . The turbine rotor disk of  claim 3 , wherein the second preform has a grain size of ASTM 0 or larger. 
     
     
         6 . The turbine rotor disk of  claim 1 , wherein a first portion includes a bore of the turbine rotor disk, and a second portion includes a rim of the turbine rotor disk. 
     
     
         7 . A gas turbine engine comprising a compressor, a combustor, and a turbine disposed along an air flow path including the turbine rotor disk of  claim 1 .