Cooling flow control members for turbomachine buckets and method

Abstract

A turbomachine bucket includes a base portion having a first end that extends to a second end, and an airfoil portion extending from the first end of the base portion. The airfoil portion includes a first end section that extends to a tip section. A plurality of cooling channels extend through the turbomachine bucket from the first end of the base portion to the tip portion, and a cooling flow control member is arranged in one of the plurality of cooling channels. The cooling flow control member creates at least a partial flow restriction in the one of the plurality of cooling channels to modify cooling flow passing through the turbomachine bucket.

1 . A turbomachine bucket comprising:
 a base portion including a first end that extends to a second end;   an airfoil portion extending from the first end of the base portion, the airfoil portion including a first end section that extends to a tip section;   a plurality of cooling channels extending through the turbomachine bucket from the first end of the base portion to the tip portion; and   a cooling flow control member arranged in one of the plurality of cooling channels, the cooling flow control member creating at least a partial flow restriction in the one of the plurality of cooling channels to modify cooling flow passing through the turbomachine bucket.   
     
     
         2 . The turbomachine bucket according to  claim 1 , wherein the cooling flow control member comprises a plug that completely block cooling flow passing through the one of the plurality of cooling channels. 
     
     
         3 . The turbomachine bucket according to  claim 1 , wherein the cooling flow control member includes a first end portion that extends to a second end portion, and a passage that extends between the first and second end portions. 
     
     
         4 . The turbomachine bucket according to  claim 3 , wherein the passage includes a tapered profile. 
     
     
         5 . The turbomachine bucket according to  claim 3 , wherein the passage includes a circular cross-section. 
     
     
         6 . The turbomachine bucket according to  claim 3 , wherein the passage includes a non-circular cross-section. 
     
     
         7 . The turbomachine bucket according to  claim 1 , wherein each of the plurality of cooling channels includes a first cooling channel section having a first diameter and a second cooling channel section having a second diameter, the second diameter being smaller than the first diameter, the first cooling channel section being arranged in the base portion and the second cooling channel section being arranged in the airfoil portion. 
     
     
         8 . The turbomachine bucket according to  claim 7 , wherein the cooling flow control member is arranged in the first section of the one of the plurality of cooling channels. 
     
     
         9 . The turbomachine bucket according to  claim 1 , wherein the cooling flow control member is arranged at the first end of the base portion. 
     
     
         10 . The turbomachine bucket according to  claim 1 , wherein the turbomachine bucket comprises a turbine bucket. 
     
     
         11 . A method of controlling cooling flow passing through a plurality of cooling passages formed in a turbomachine bucket, the method comprising:
 exposing the plurality of cooling passages formed in the turbomachine bucket;   inserting a cooling flow control member into at least one of the cooling passages; and   controlling a cooling fluid flow passing through the turbomachine bucket with the cooling flow control member.   
     
     
         12 . The method of  claim 11 , wherein controlling the cooling fluid flow comprises completely blocking cooling fluid flow through the at least one of the plurality of cooling passages. 
     
     
         13 . The method of  claim 12 , wherein completely blocking cooling fluid flow comprises preventing cooling fluid from entering the one of the plurality of cooling flow passages. 
     
     
         14 . The method of  claim 11 , wherein controlling fluid flow comprises partially blocking the one of the plurality of cooling passages with the cooling flow control member. 
     
     
         15 . The method of  claim 14 , wherein partially blocking the one of the cooling passages comprises passing the cooling flow through an orifice formed in the cooling flow control member. 
     
     
         16 . The method of  claim 11 , further comprising: removing the cooling flow control member from the one of the plurality of cooling passages without damaging the turbomachine bucket. 
     
     
         17 . A turbomachine comprising:
 a compressor portion;   a turbine portion; and   a turbomachine bucket arranged in one of the compressor portion and the turbine portion, the turbomachine bucket comprising:   a base portion including a first end that extend to a second end;   an airfoil portion extending from the first end of the base portion, the airfoil portion including a first end section that extends to a tip section;   a plurality of cooling channels extending through the turbomachine bucket from the first end of the base portion to the tip portion; and   a cooling flow control member arranged in one of the plurality of cooling channels, the cooling flow control member creating at least a partial flow restriction in the one of the plurality of cooling channels to modify cooling flow passing through the turbomachine bucket.   
     
     
         18 . The turbomachine according to  claim 17 , wherein the cooling flow control member comprises a plug that completely block cooling flow from passing into the one of the plurality of cooling channels. 
     
     
         19 . The turbomachine according to  claim 17 , wherein the cooling flow control member includes a first end portion that extends to a second end portion, and a passage that extends between the first and second end portions. 
     
     
         20 . The turbomachine according to  claim 19 , wherein the passage includes a tapered profile.