Intensively cooled trailing edge of thin airfoils for turbine engines

摘要

A cooling system designed to cool the trailing edge of a turbine blade usable in rear stages of a turbine engine. The turbine blade may have a leading edge cooling cavity and a trailing edge cooling cavity separated by an impingement rib. The cooling system may exhaust cooling fluids through the tip of the turbine blade rather than through the trailing edge of the turbine blade to prevent premature failure at the trailing edge of the turbine blade.