Abstract: A turbine engine component has an airfoil portion having a leading edge, a suction side, and a pressure side and a radial flow leading edge cavity through which a cooling fluid flows for cooling the leading edge. The turbine engine component further has a first set of trip strips and a second set of trip strips which meet at the leading edge nose portion of the leading edge cavity to form a plurality of chevron shaped trip strips and for generating a vortex in the leading edge cavity which impinges on the nose portion of the leading edge cavity and enhances convective heat transfer.

Abstract: A rotor blade is provided that includes a root, a hollow airfoil, and a conduit disposed within the root. The hollow airfoil has a cavity defined by a suction side wall, a pressure side wall, a leading edge, a trailing edge, a base, and a tip. An internal passage configuration is disposed within the cavity. The configuration includes a first radial passage, a second radial passage, a rib disposed between and separating the first radial passage and second radial passage, a plurality of crossover apertures disposed within the rib, and a plurality of trip strips disposed within the second radial passage. The trip strips are attached to an interior surface of one or both of the pressure side wall and the suction side wall. The trip strips are disposed within the first radial passage at an angle ? that is skewed relative to a cooling airflow direction within the first radial passage, and positioned such that each of the plurality of trip strips converges toward the rib.

Abstract: An internally cooled gas turbine engine turbine vane has an outboard shroud and an airfoil extending from an outboard end at the shroud to an inboard end. A cooling passageway has an inlet in the shroud, a first turn at least partially within the airfoil, a first leg extending from the inlet inboard through the airfoil to the first turn, and a second leg extending from the first turn. A dividing wall is in the passageway and has an upstream end in an outboard half of a span of the airfoil and has a plurality of vents. The vane may be formed as a reengineering of a baseline configuration lacking the dividing wall.