Patent ID: 8128365
Filing Date: 2012-03-06
Classification: F01D,F05D

Abstract:
1. A turbine airfoil cooling system, comprising: a hollow, disc post body configured to be positioned between adjacent roots of turbine airfoils, wherein the body includes a central cooling fluid cavity extending from a first end of the disc body to a second end of the disc body along a longitudinal axis of the disc body, and the body includes an opening in an inner surface of an outer wall of the body creating a cooling fluid pathway for cooling fluids to enter the central cooling fluid cavity, and a plurality of impingement orifices in the outer wall extending between the central cooling fluid cavity and an outer surface for providing impingement cooling to inner surfaces of platforms of the turbine airfoils; wherein the hollow disc body includes the outer surface, the inner surface opposite to the outer surface, two side surfaces opposite to each other and both generally orthogonal to the inner and outer side surfaces, the first and second ends opposite to each other and generally orthogonal to the inner and outer surfaces and to the two side surfaces, wherein the two side surfaces include lengthwise indentations that are generally parallel with the longitudinal axis of the disc body, thereby creating a generally anvil shaped cross-section of the disc body.