Patent ID: 8047789
Filing Date: 2011-11-01
Classification: F01D,F05D

Abstract:
1. An air cooled turbine airfoil for use in a gas turbine engine, the turbine airfoil comprising: a support spar having an airfoil shape with a pressure side and a suction side and a trailing edge; a plurality of modules formed on the pressure side of the support spar, each module having an impingement compartment and a diffusion compartment separated by a compartment rib; the compartment ribs having at least one crossover hole connecting the impingement compartment to the diffusion compartment; a thermal skin secured onto the support spar to form the airfoil surface of the turbine airfoil; a plurality of impingement holes connecting the impingement compartment to a first cavity formed within the spar; and, a plurality of spent air return holes connecting the diffusion compartment to a second cavity formed within the spar, wherein cooling air flows from the first cavity in the spar through the impingement holes and into the impingement compartment to provide impingement cooling to the thermal skin, through the crossover hole and into the diffusion compartment, and then into the second cavity.