Patent ID: 7371048

Claim:
A turbine blade system for a gas turbine engine, the turbine blade system comprising a turbine blade having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface to a trailing edge, the trailing edge region including a plurality of riblets extending in the lengthwise direction from the pressure side surface toward the trailing edge, the trailing edge region defining a plurality of ejection slots, each laterally disposed between two of the riblets, the riblets each having an upper surface comprising an extension of said pressure side surface, said extension being external of said turbine blade, each said upper riblet surface having a substantial portion thereof in the lengthwise direction which is of increased curvature relative to the pressure side surface wherein the upper surface of each said riblet is shielded from a high heat load propagating from the pressure side surface and wherein the flow of cooling air flowing from the ejection slots over the upper surface of each said riblet is facilitated.