Impigement cooled airfoil

The present invention relates generally to gas turbine engine airfoils and more particularly to airfoils having impingement cooling. An airfoil for use in a gas turbine engine. The airfoil includes a body having an interior surface defining a hollow cavity in the airfoil having an inlet and an outlet. The airfoil also includes a partition within the cavity dividing the cavity into a first cooling passage and a second cooling passage. The first cooling passage communicates with the inlet for delivering cooling air to the first passage and the second cooling passage communicates with the outlet for exhausting cooling air from the second passage. The partition has a cooling hole therein extending between the first passage and the second passage permitting cooling air to pass from the first passage to the second passage. The cooling hole is sized and positioned with respect to the interior surface of the airfoil for directing cooling air toward a portion of the interior surface of the airfoil so the cooling air impinges upon the portion. Thus, cooling air entering the inlet of the cavity travels through the first passage for cooling the body by convective heat transfer, through the cooling hole for impinging upon the portion of the interior surface of the body, through the second passage to cool the body by convective heat transfer, and out the outlet of the cavity.