Abstract: A turbine blade system for a gas turbine engine includes 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 includes a plurality of riblets extending in the lengthwise direction from the pressure side surface toward the trailing edge. The trailing edge region defines a plurality of ejection slots each laterally disposed between two of the riblets. The plurality of riblets each define an upper surface having at least a portion in the lengthwise direction being curved relative to the pressure side surface so as to generally shield the upper surface from a high heat load propagating from the pressure side surface and to facilitate cooling air flowing from the ejection slots to flow over the upper surface.

Abstract: A turbine blade cooling system for a gas turbine engine includes a turbine blade having a trailing edge, a concave side, and a convex side. The trailing edge defines at least one set of impingement holes each having a central longitudinal axis which is closer to a nearest portion of an edge of the blade at one of the concave and convex sides relative to a nearest portion of an edge of the blade at the other of the concave and convex sides. Alternatively or in addition to the foregoing, the trailing edge can define at least one set of impingement holes each having a central longitudinal axis which is angled in a direction of a flow of cooling medium toward one of the concave and convex sides relative to the other of the concave and convex sides.