Patent attributes
A turbine vane for use in a gas turbine engine, the vane including an airfoil portion and a endwall in which fillets extend around the airfoil at the junction to the endwall. A leading edge outer fillet surface is located over an inner fillet surface and forms an impingement cavity between the leading edge fillet surfaces. Metering and impingement cooling holes discharge impingement cooling air to the backside of the outer fillet surface, and film cooling holes of the outer fillet surface provide film cooling to the outer fillet surface. The outer fillet surface forms slots on the ends of both the pressure side and suction side to discharge cooling air along the fillets formed between the airfoil walls and the endwall. An internal partition separates the fillet impingement cavity into a pressure side cavity and a suction side cavity. Cooling air flows through the metering and impingement holes to provide backside cooling of the outer fillet surface, then flows out the film cooling holes and the slots to provide film cooling of the outer fillet surface and to direct cooling air along the fillets between the airfoil walls and the endwall.
