Turbine airfoil cooling system with perimeter cooling and rim cavity purge channels

摘要

A cooling system for a turbine airfoil of a turbine engine having a perimeter cooling channel formed from a portion of a serpentine cooling channel, an airfoil tip cooling channel, and a leading edge cooling channel. The cooling system also includes cooling channels enabling cooling fluids to be discharged into the root of the airfoil to cool rim cavities and purge air therein. The cooling system may be configured such that the cooling fluids may pass into a mid-chord serpentine cooling channel, flow through the serpentine cooling channel generally in a chordwise direction from the leading edge toward the trailing edge, flow toward the tip section and along the trailing edge, flow from the trailing edge toward the leading edge in the airfoil tip cooling channel, flow along the leading edge in the leading edge cooling channel, through the root of the blade, and be exhausted into a rim cavity.