Multi-part cast turbine engine component having an internal cooling channel and method of forming a multi-part cast turbine engine component

Abstract

A multi-part cast component for a turbine engine includes a first component section having a main body portion including at least one cooling flow passage section, and a second component section having a main body including at least one cooling flow passage section. The first and second component sections are joined along a parting line to form a turbine engine component with the at least one cooling flow passage section of the first component section aligning with the at least one cooling flow passage of the second component section to form a cooling flow channel.

1 . A multi-part cast component for a turbine engine comprising:
 a first component section having a main body portion including at least one cooling flow passage section; and   a second component section having a main body portion including at least one cooling flow passage section, said second component section being joined to the first component section along a parting line to form a turbine engine component with the at least one cooling flow passage section of the first component section aligning with the at least one cooling flow passage section of the second component section to form a cooling flow channel.   
   
   
       2 . The multi-part cast component according to  claim 1 , wherein the first and second component sections are joined to form a two-part turbine engine component. 
   
   
       3 . The multi-part cast component according to  claim 1 , wherein the first component section is a first rotor blade section and the second component section is a second rotor blade section, said first and second rotor blade sections being joined along the parting line to form a turbine rotor blade. 
   
   
       4 . The multi-part cast component according to  claim 1 , wherein the at least one cooling flow passage section of the first component section includes first and second cooling flow passage sections. 
   
   
       5 . The multi-part cast component according to  claim 3 , wherein the at least one cooling flow passage section of the second component section includes third and fourth cooling flow passage sections, said first and third cooling flow passage sections being joined to form a first cooling flow channel and said second and fourth cooling flow passage sections being joined to form a second cooling flow channel. 
   
   
       6 . A method of forming a multi-part cast component for a turbine engine comprising:
 forming a first component section;   creating at least one cooling flow passage section in the first component section;   forming a second component section;   creating at least one cooling flow passage section in the second component section; and   joining the first and second component section along a parting line to form a turbine engine component with said at least one cooling flow passage section of the first component section joining to the at least one cooling flow passage section of the second component section to form a cooling flow channel in the turbine component.   
   
   
       7 . The method of  claim 6 , wherein the turbine engine component is a turbine rotor blade. 
   
   
       8 . The method of  claim 6 , further comprising:
 forming first and second cooling flow passage sections in the first component section; and   forming third and fourth cooling flow passage sections in the second component section wherein, upon joining the first and second component sections along the parting line, said first cooling flow passage section registers with the third cooling flow passage section to establish a first cooling flow channel and said second cooling flow passage section registers with the fourth cooling flow passage section to establish a second cooling flow channel in the turbine component.   
   
   
       9 . The method of  claim 6 , wherein the at least one cooling flow passage section is machined from corresponding ones of the first and second component sections. 
   
   
       10 . The method of  claim 6 , wherein the at least one cooling flow passage section is molded into corresponding ones of the first and second component sections. 
   
   
       11 . The method of  claim 5 , wherein the turbine engine component is formed in two parts.