Abstract: A hollow, cooled airfoil has a pair of nested, coolant channels therein which carry separate coolant flows back and forth across the span of the airfoil in adjacent parallel paths. The coolant in both channels flows from a rearward to forward location within the airfoil allowing the coolant to be ejected from the airfoil near the leading edge through film coolant holes.

Abstract: A coolable airfoil 10 for rotary machines is disclosed. The airfoil has a passage 54 extending spanwisely through the leading edge region 26 of the blade. The passage has a plurality of trip strips 68 canted toward the direction flow. Each trip strip includes a vortex generator integrally formed with the trip strip which is spaced from the wall of the airfoil. In one embodiment, a plurality of trip strips each having an integral vortex generator are disposed in the passageway and at least one of the vortex generators is of greater height than the remaining vortex generators.

Abstract: A rotor blade design capable of long term reliable operation in a high temperature environment is disclosed. Various cooling concepts adapted to preserve the mechanical properties of the blade material are developed. A cooling system for the blade is built around a multiple supply construction in which cooling medium from a first supply is mixed internally of the blade with cooling medium from a second supply.