Leading edge airfoil-to-platform fillet cooling tube

Abstract

A turbine engine component includes an airfoil portion having a leading edge, a platform, a leading edge airfoil to platform fillet, and a cooling tube located within said fillet. The cooling tube has a flared entrance end and a flared exit end.

1 . A turbine engine component comprising:
 an airfoil portion having a leading edge;   a platform;   a leading edge airfoil to platform fillet; and   a cooling tube located within said fillet, said cooling tube having a flared entrance end and a flared exit end.   
     
     
         2 . The turbine engine component of  claim 1 , wherein said entrance end and said exit end are each bellmouth shaped. 
     
     
         3 . The turbine engine component of  claim 1 , wherein said leading edge of said airfoil portion includes a leading edge boxcar and an interior portion of said airfoil portion includes a cavity through which cooling air flows. 
     
     
         4 . The turbine engine component of  claim 3 , further comprising a plurality of cross-over holes for allowing cooling fluid to flow from said cavity to said boxcar. 
     
     
         5 . The turbine engine component of  claim 3 , wherein said boxcar has a plurality of cooling film holes. 
     
     
         6 . The turbine engine component of  claim 1 , wherein said tube has a cross-sectional area which is between 25% and 100% of a cross-sectional area of said boxcar. 
     
     
         7 . The turbine engine component of  claim 1 , wherein said tube has a cross-sectional area which is between 50% and 100% of a cross-sectional area of said boxcar. 
     
     
         8 . The turbine engine component of  claim 1 , wherein said tube has a cross-sectional shape selected from the group consisting of circular, elliptical, triangular, and square. 
     
     
         9 . The turbine engine component of  claim 1 , wherein said cooling tube meets said leading edge boxcar at an end of said leading edge boxcar. 
     
     
         10 . A core for forming part of a turbine engine component, said core comprising:
 a first portion for forming an internal cavity within an airfoil portion of said component;   a second portion for forming a leading edge boxcar in a leading edge of said airfoil portion;   a third portion for forming a cooling tube which extends between said leading edge boxcar and said internal cavity; and   said third portion having a flared entrance end and a flared exit end.   
     
     
         11 . The core according to  claim 10 , wherein said core is formed from a ceramic material. 
     
     
         12 . The core according to  claim 10 , wherein said core has at least one fourth portion adapted to form at least one cross-over hole between said leading edge boxcar and said cavity. 
     
     
         13 . The core according to  claim 10 , wherein said entrance end and said exit end are each bellmouthed shaped.