Patent ID: 7500828

Claim:
A turbine airfoil for use in a turbine of a gas turbine engine, the turbine airfoil comprising: An airfoil frame having an airfoil shape with a leading edge and a trailing edge and a pressure side and a suction side extending between the leading and the trailing edges, the airfoil frame forming an internal cooling air supply passage; The airfoil frame includes an array of ribs forming a plurality of cavities on the outer side of the airfoil frame; A cooling air supply hole in the base of each cavity connected to the internal cooling air supply passage to supply cooling air to the respective cavity; A porous metallic material substantially filling each cavity; A TBC secured to the porous metallic material and the ribs to form an outer airfoil surface; and, A film cooling hole formed in the TBC for each cavity to discharge film cooling air onto the airfoil outer surface.