Gas turbine vane with integral cooling system

A turbine vane, comprising:

• a generally elongated hollow airfoil formed from an outer wall having a leading edge, a trailing edge, a pressure side, a suction side, a first end adapted to be coupled to a hook attachment, a second end opposite the first end adapted to be coupled to an inner endwall, and a cooling system in the hollow airfoil formed from at least one internal cooling cavity;
• a plurality of first diffusors, each formed from a plurality of cavities in the outer wall of the generally elongated hollow airfoil aligned spanwise into rows;
• a plurality of interior metering orifices creating fluid pathways between the internal cooling cavity and the plurality of cavities in the outer wall forming the first diffusors, wherein at least one of the interior metering orifices is generally orthogonal relative to an inner surface of the outer wall;
• a plurality of second diffusors, each formed from a plurality of exterior metering orifices creating fluid pathways between the plurality of cavities forming the first diffusors in the outer wall and an outer surface of the generally elongated hollow airfoil;
• and
• wherein each of the first diffusors are formed from a linear flowpath in direct fluid communication with and aligned with a linear flow path of the second diffusors;
• a third diffusor formed from a diffusion slot extending spanwise in the airfoil and coupled to the plurality of exterior metering orifices;
• wherein the diffusion slot extends spanwise between adjacent sets of exterior metering slots at the outer surface of the generally elongated hollow airfoil, thereby placing the diffusion slot in fluid communication with a plurality of first diffusors.