Method and device for airfoil film cooling

摘要

An airfoil (40) for a gas turbine engine including an inflection (70) that facilitates enhancing film cooling of the airfoil, without adversely affecting aerodynamic efficiency of airfoil is described. The airfoil includes a generally concave first sidewall (46) and a generally convex second sidewall (44) joined at a leading edge (48) and at a trailing edge (50) of the airfoil. A plurality of cooling openings (80) extend between an internal cooling chamber (58) and an external surface (62) of the first sidewall. One cooling opening (82) extends from the cooling chamber into the inflection at a relatively shallow injection angle (M) with respect the airfoil external surface.