Extended indentation for a fastener within an air flow

Abstract

A vane includes a surface with an aperture having an extended indentation at least partially therearound.

What is claimed is: 
     
         1 . A flow path comprising:
 a surface with an aperture having an extended indentation at least partially therearound.   
     
     
         2 . The flow path as recited in  claim 1 , wherein said surface is an inner platform of a structural guide vane. 
     
     
         3 . The flow path as recited in  claim 1 , wherein said surface is an outer platform of a structural guide vane. 
     
     
         4 . The flow path as recited in  claim 1 , wherein said extended indentation is “tear-drop” shaped 
     
     
         5 . The flow path as recited in  claim 1 , wherein said extended indentation is parabola shaped. 
     
     
         6 . The flow path as recited in  claim 1 , wherein said extended indentation is semi-conical. 
     
     
         7 . The flow path as recited in  claim 1 , wherein a leading edge of said extended indentation is coplanar with an upper face of a fastener. 
     
     
         8 . The flow path as recited in  claim 1 , wherein said aperture is a counterbore aperture. 
     
     
         9 . The flow path as recited in  claim 8 , wherein said extended indentation extends aft of said counterbore aperture. 
     
     
         10 . The flow path as recited in  claim 8 , wherein a leading edge of said extended indentation is coplanar with an upper face of a fastener. 
     
     
         11 . The flow path as recited in  claim 10 , wherein said extended indentation defines a centerline generally parallel to an airfoil that extends from said platform. 
     
     
         12 . The flow path as recited in  claim 11 , wherein said extended indentation is parabola shaped. 
     
     
         13 . The flow path as recited in  claim 10 , wherein said extended indentation is parabola shaped. 
     
     
         14 . A gas turbine engine, comprising:
 a fan case;   a core case;   an inner surface adjacent to said core case;   an outer surface adjacent to said fan case;   a first fastener which retains said inner surface to said core case, said first fastener mounted within a first counterbore in said inner surface, said first counterbore having a first extended indentation at least partially therearound; and   a second fastener which retains said outer surface to said fan case, said second fastener mounted within a second counterbore in said outer surface, said second counterbore having a second extended indentation at least partially therearound.   
     
     
         15 . The gas turbine engine as recited in  claim 14 , wherein said inner surface and said outer surface defines a portion of an aerodynamic radial boundary of a tan bypass flow path. 
     
     
         16 . The gas turbine engine as recited in  claim 14 , wherein a leading edge of said first extended indentation and said second extended indentation are matched to the curvature of a flowpath. 
     
     
         17 . The gas turbine engine as recited in  claim 14 , wherein said first extended indentation and said second extended indentation define a centerline generally parallel to an airfoil which extends between said inner surface and said outer surface. 
     
     
         18 . A method of assembling a flow path of a gas turbine engine comprising:
 mounting a fastener into a counterbore of a surface, the counterbore having an extended indentation at least partially therearound such that an edge of the counterbore is coplanar with an upper face of the fastener.   
     
     
         19 . The method as recited in  claim 18 , further comprising:
 orienting the extended indentation generally aftwards in convergent section of the flow path.   
     
     
         20 . The method as recited in  claim 18 , further comprising:
 orienting the extended indentation generally forwards in a divergent section of the flow path.