Turbine engine rotor, method of producing the same, method of joining ni-based superalloy member and steel member, and junction structure of ni-based superalloy member and steel member

Abstract

A method of producing a turbine engine rotor includes: joining a first rotor disc ( 25 H) and an intermediate member ( 26 ) together by electronic beam welding, the first rotor disc ( 25 H) being formed of a precipitation hardened Ni-based superalloy, the intermediate member ( 26 ) being formed of a solid solution strengthened Ni-based superalloy; performing age-hardening treatment on the joined body at a first temperature which is a suitable temperature for age-hardening the precipitation hardened Ni-based superalloy; joining the intermediate member ( 26 ) and a second rotor disc ( 25 L) together by electronic beam welding, the second rotor disc ( 25 L) being formed of a steel; and performing annealing treatment on the joined body at a second temperature which is a suitable temperature for annealing the steel.

1 . A method of producing a turbine engine rotor, the method comprising:
 joining a first rotor disc and an intermediate member together by electronic beam welding, the first rotor disc being formed of a solution heat treated precipitation hardened Ni-based superalloy, the intermediate member being formed of a solid solution strengthened Ni-based superalloy;   performing age-hardening treatment on a joined body of the first rotor disc and the intermediate member at a first temperature which is a suitable temperature for age-hardening the precipitation hardened Ni-based superalloy;   joining the intermediate member and a second rotor disc together by electronic beam welding, the second rotor disc being formed of a heat-resistant steel; and   performing annealing treatment on a joined body of the first rotor disc, the intermediate member, and the second rotor disc at a second temperature which is a suitable temperature for annealing the steel.   
     
     
         2 . The method of producing a turbine engine rotor according to  claim 1 , wherein the solid solution strengthened Ni-based superalloy is Inconel 625 (IN625) [Inconel=IN, registered trademark; indication of trademark registration is omitted hereinafter]. 
     
     
         3 . The method of producing a turbine engine rotor according to  claim 1 , wherein
 the precipitation hardened Ni-based superalloy is Inconel 718 (IN718), and   the first temperature is in a temperature range from 710 to 726° C.   
     
     
         4 . The method of producing a turbine engine rotor according to  claim 1 , wherein
 the steel is 12% Cr steel, and   the second temperature is in a temperature range from 570 to 590° C.   
     
     
         5 . A turbine engine rotor including a plurality of rotor discs connected to each other in an axial direction, the turbine engine rotor comprising:
 two rotor discs which are a first rotor disc and a second rotor disc adjacent to each other, the first rotor disc being formed of a precipitation hardened Ni-based superalloy, the second rotor disc being formed of a heat-resistant steel, wherein   the first rotor disc and an intermediate member are joined together by electronic beam welding, the intermediate member being formed of a solid solution strengthened Ni-based superalloy, and   the second rotor disc and the intermediate member are joined together by electronic beam welding.   
     
     
         6 . The turbine engine rotor according to  claim 5 , wherein the solid solution strengthened Ni-based superalloy is Inconel 625 (IN625). 
     
     
         7 . The turbine engine rotor according to  claim 5 , wherein the precipitation hardened Ni-based superalloy is Inconel 718 (IN718). 
     
     
         8 . The turbine engine rotor according to  claim 5 , wherein the steel is 12% Cr steel. 
     
     
         9 . A method of joining a Ni-based superalloy member and a steel member, which is a method of joining a first member and a second member, the first member being formed of a solution heat treated precipitation hardened Ni-based superalloy, the second member being formed of a heat-resistant steel, the method comprising:
 joining the first member and an intermediate member together by electronic beam welding, the intermediate member being formed of a solid solution strengthened Ni-based superalloy;   performing age-hardening treatment on a joined body of the first member and the intermediate member at a first temperature which is a suitable temperature for age-hardening the first member;   joining the intermediate member and the second member together by electronic beam welding; and   performing annealing treatment on a joined body of the first member, the intermediate member, and the second member at a second temperature which is a suitable temperature for annealing the second member.   
     
     
         10 . The method of joining a Ni-based superalloy member and a steel member according to  claim 9 , wherein
 the solid solution strengthened Ni-based superalloy is Inconel 625 (IN625).   
     
     
         11 . The method of joining a Ni-based superalloy member and a steel member according to  claim 9 , wherein
 the precipitation hardened Ni-based superalloy is Inconel 718 (IN718), and   the first temperature is in a temperature range from 710 to 726° C.   
     
     
         12 . The method of joining a Ni-based superalloy member and a steel member according to  claim 9 , wherein
 the steel is 12% Cr steel, and   the second temperature is in a temperature range from 570 to 590° C.   
     
     
         13 . A junction structure of a Ni-based superalloy member and a steel member, comprising:
 a first member formed of a precipitation hardened Ni-based superalloy; and   a second member formed of a heat-resistant steel, wherein   the first member and an intermediate member are joined together by electronic beam welding, the intermediate member being formed of a solid solution strengthened Ni-based superalloy, and   the second member and the intermediate member are joined together by electronic beam welding.   
     
     
         14 . The junction structure of a Ni-based superalloy member and a steel member according to  claim 13 , wherein the solid solution strengthened Ni-based superalloy is Inconel 625 (IN625). 
     
     
         15 . The junction structure of a Ni-based superalloy member and a steel member according to  claim 13 , wherein the precipitation hardened Ni-based superalloy is Inconel 718 (IN718). 
     
     
         16 . The junction structure of a Ni-based superalloy member and a steel member according to  claim 13 , wherein the steel is 12% Cr steel. 
     
     
         17 . The method of producing a turbine engine rotor according to  claim 2 , wherein
 the precipitation hardened Ni-based superalloy is Inconel 718 (IN718), and   the first temperature is in a temperature range from 710 to 726° C.   
     
     
         18 . The turbine engine rotor according to  claim 6 , wherein the precipitation hardened Ni-based superalloy is Inconel 718 (IN718). 
     
     
         19 . The method of joining a Ni-based superalloy member and a steel member according to  claim 10 , wherein
 the precipitation hardened Ni-based superalloy is Inconel 718 (IN718), and   the first temperature is in a temperature range from 710 to 726° C.   
     
     
         20 . The junction structure of a Ni-based superalloy member and a steel member according to  claim 14 , wherein the precipitation hardened Ni-based superalloy is Inconel 718 (IN718).