Component with cooling hole having helical groove

Abstract

One exemplary embodiment of this disclosure relates to a component for a gas turbine engine. The component includes a cooling hole having a wall with at least one helical groove formed in the wall.

What is claimed is: 
     
         1 . A component for a gas turbine engine, comprising:
 a cooling hole having a wall with at least one helical groove formed in the wall.   
     
     
         2 . The component as recited in  claim 1 , wherein the cooling hole is provided about a cooling hole axis, and wherein the at least one helical groove curves about the cooling hole axis as the at least one helical groove translates along the cooling hole axis. 
     
     
         3 . The component as recited in  claim 2 , wherein the cooling hole axis is inclined at an acute angle relative a central longitudinal axis of the engine. 
     
     
         4 . The component as recited in  claim 1 , wherein the wall includes a plurality of helical grooves. 
     
     
         5 . The component as recited in  claim 1 , wherein the component includes a plurality of cooling holes, each of the plurality of cooling holes having a wall with at least one helical groove. 
     
     
         6 . The component as recited in  claim 1 , including an internal cavity, the cooling hole in communication with the internal cavity. 
     
     
         7 . The component as recited in  claim 1 , wherein the internal cavity is in communication with a source of cooling fluid. 
     
     
         8 . The component as recited in  claim 1 , wherein the component is one of a rotor blade, a stator vane, and a blade outer air seal. 
     
     
         9 . The component as recited in  claim 8 , wherein the component is a rotor blade, and wherein the cooling hole is provided in an airfoil section of the rotor blade. 
     
     
         10 . The component as recited in  claim 9 , wherein the cooling hole is a showerhead cooling hole provided in a leading edge of the rotor blade. 
     
     
         11 . A gas turbine engine, comprising:
 a compressor section, a combustor section, and a turbine section; and   a component provided within one of the compressor section, the combustor section, and the turbine section, the component including a cooling hole having a wall with at least one helical groove formed in the wall.   
     
     
         12 . The engine as recited in  claim 11 , wherein the cooling hole is provided about a cooling hole axis, and wherein the at least one helical groove curves about the cooling hole axis as the at least one helical groove translates along the cooling hole axis. 
     
     
         13 . The engine as recited in  claim 12 , wherein the cooling hole axis is inclined at an acute angle relative a central longitudinal axis of the engine. 
     
     
         14 . The engine as recited in  claim 11 , wherein the component includes a plurality of cooling holes, each of the plurality of cooling holes having a wall with at least one helical groove. 
     
     
         15 . The engine as recited in  claim 11 , wherein the component includes an internal cavity, the cooling hole in communication with the internal cavity. 
     
     
         16 . The engine as recited in  claim 15 , wherein the internal cavity is in communication with a source of cooling fluid. 
     
     
         17 . The engine as recited in  claim 11 , wherein the component is one of a rotor blade, a stator vane, and a blade outer air seal. 
     
     
         18 . The engine as recited in  claim 17 , wherein the component is a rotor blade, and wherein the cooling hole is a showerhead cooling hole provided in a leading edge of the rotor blade.