Patent ID: 7217096

Claim:
A turbine stage comprising: a row of airfoils integrally joined to corresponding platforms and spaced laterally apart to define respective flow passages therebetween for channeling combustion gases; each of said airfoils including a concave pressure side and a laterally opposite convex suction side bounding an internal cooling circuit, and extending in chord between opposite leading and trailing edges; each of said airfoils blending with said platforms in an arcuate fillet being larger in size along said pressure side than along said suction side around said leading edge, and forming a local depression in said platform being larger on said pressure side than on said suction side; and each of said fillets including a film cooling root hole joined in flow communication with said cooling circuit for discharging cooling air along said fillet for energizing boundary layer flow of said combustion gases and weakening horseshoe vortices in said flow passages.