Conduction pedestals for a gas turbine engine airfoil

Abstract

An airfoil for a gas turbine engine includes an airfoil which defines a leading edge cavity and a forward cavity between a pressure side wall and a suction side wall, the leading edge cavity at least partially defined by a leading edge wall which extends between the pressure side wall and the suction side wall. A rib between the pressure side wall and the suction side wall separates the forward cavity and the leading edge cavity. A pedestal extends between the leading edge wall and the rib.

1 . An airfoil for a gas turbine engine comprising:
 a pressure side wall and a suction side wall which define a leading edge cavity and a forward cavity between said pressure side wall and said suction side wall, said leading edge cavity at least partially defined by a leading edge wall which extends between said pressure side wall and said suction side wall;   a rib between said pressure side wall and said suction side wall to at least partially divide said forward cavity and said leading edge cavity; and   a pedestal which extends between said leading edge wall and said rib.   
     
     
         2 . The airfoil as recited in  claim 1 , wherein said pedestal is aligned along an axis which extends toward a high temperature area in a stagnation region of said leading edge wall. 
     
     
         3 . The airfoil as recited in  claim 2 , further comprising a second pedestal aligned along a second axis different than said axis. 
     
     
         4 . The airfoil as recited in  claim 1 , wherein said rib at least partially defines an impingement leading edge. 
     
     
         5 . The airfoil as recited in  claim 4 , wherein said rib defines a multiple of cooling holes which communicate a cooling flow from said forward cavity into said leading edge cavity through said rib then through a multiple of leading edge cooling holes through said leading edge. 
     
     
         6 . The airfoil as recited in  claim 1 , wherein said rib at least partially defines a radial flow leading edge. 
     
     
         7 . The airfoil as recited in  claim 6 , wherein said leading edge defines a multiple of cooling holes which communicate a cooling flow from within said leading edge cavity through a multiple of leading edge cooling holes through said leading edge. 
     
     
         8 . The airfoil as recited in  claim 1 , wherein said airfoil at least partially defines a turbine vane. 
     
     
         9 . The airfoil as recited in  claim 1 , wherein said airfoil at least partially defines a turbine blade. 
     
     
         10 . An airfoil for a gas turbine engine comprising:
 a pressure side wall and a suction side wall which defines a leading edge cavity and a forward cavity between said pressure side wall and said suction side wall, said leading edge cavity at least partially defined by a leading edge wall which extends between said pressure side wall and said suction side wall;   a rib between said pressure side wall and said suction side wall to at least partially divide said forward cavity and said leading edge cavity; and   a multiple of pedestals which extend between said leading edge wall and said rib, said multiple of pedestals arrayed along a length of said airfoil between a first end portion and a second end portion.   
     
     
         11 . The airfoil as recited in  claim 10 , wherein each of said multiple of pedestals are aligned along an axis which extends toward a high temperature area in a stagnation region of said leading edge wall. 
     
     
         12 . The airfoil as recited in  claim 10 , wherein a first set of said multiple of pedestals are aligned along a first axis which extends toward a first high temperature area in a stagnation region of said leading edge and a second set of said multiple of pedestals are aligned along a second axis which extends toward a second high temperature area in the stagnation region of said leading edge. 
     
     
         13 . The airfoil as recited in  claim 10 , wherein each of said multiple of pedestals are transverse to said rib. 
     
     
         14 . The airfoil as recited in  claim 10 , wherein said airfoil at least partially defines a turbine vane. 
     
     
         15 . The airfoil as recited in  claim 10 , wherein said airfoil at least partially defines a turbine blade.