TURBINE AIRFOIL COOLING SYSTEM WITH NONLINEAR TRAILING EDGE EXIT SLOTS

摘要

A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling channel formed from a central trailing edge cooling channel and at least one trailing edge exit slot with a nonlinear longitudinal axis is disclosed. The trailing edge exit slot may be defined by ribs (24) having wavy side edges that form a jagged edge. As such, the nonlinear longitudinal axis (22) of the trailing edge exit slot reduces the effective flow area, generates impingement and turbulence to increase heat transfer and provides sufficient mechanical strength for better casting yield without overflowing for better performance. The nonlinear trailing edge exit slot may be formed using a ceramic core (106) and investment casting.