Gas turbine airfoil with aft internal cooling

摘要

A gas turbine vane or blade having a novel internal structure that allows for cooling under diverse pressure ratios. The vane has an air inlet passage that communicates with an inner cooling cavity positioned between the air passage and the vane's trailing edge. Disposed within this cavity are deflectors, turning members, ribs, and deflecting pins arranged so as to direct the cooling air through the cavity in a manner that minimizes pressure loss. Thus maintaining the velocity and flow of the cooling air.