Patent ID: 7270515
Filing Date: 2007-09-18
Classification: B22C,F01D,F05D

Abstract:
1. A turbine airfoil, comprising: a generally elongated airfoil having a leading edge, a trailing edge, a tip section at a first end, a root coupled to the airfoil at an end generally opposite the first end for supporting the airfoil and for coupling the airfoil to a disc, and at least one cavity forming a cooling system in the airfoil; at least one trailing edge cooling channel extending from the root to the tip section of the elongated airfoil; at least one first segmented spanwise rib positioned in the at least one trailing edge cooling channel, extending generally from the root to the tip section of the elongated airfoil, and including a plurality of impingement orifices; at least one second segmented spanwise rib positioned in the at least one trailing edge cooling channel, extending generally from the root to the tip section of the elongated airfoil, positioned between the first segmented spanwise rib and the trailing edge of the generally elongated airfoil, and including a plurality of impingement orifices; at least one crossover orifice positioned between an end of the at least one first segmented spanwise rib and the tip section of the airfoil and between another end of the at least one first segmented spanwise rib and the root; at least one crossover orifice positioned between an end of the at least one second segmented spanwise rib and the tip section of the airfoil and between another end of the at least one second segmented spanwise rib and the root; at least one crossover orifice in the at least one first segmented spanwise rib between the crossover orifices at each end at least one first segmented spanwise rib and extending generally from an inner surface of a suction side of the airfoil to an inner surface of a pressure side of the airfoil; at least one crossover orifice in the at least one second segments spanwise rib between the crossover orifices at each end of the at least one second segmented spanwise rib and extending generally from the inner surface of the suction side of the airfoil to the inner surface of the pressure side of the airfoil; and wherein the crossover orifices each have a larger cross-sectional area than cross-sectional areas of the impingement orifices.