Patent ID: 8328518

Claim:
A turbine vane for a gas turbine engine, comprising: a generally elongated airfoil formed from an outer wall, and having a leading edge, a trailing edge, a pressure side, a suction side generally opposite to the pressure side, a first endwall at a first end, a second endwall at a second end opposite the first end, and an internal cooling system positioned within the generally elongated airfoil; wherein the internal cooling system includes at least one serpentine cooling channel that extends from proximate to the leading edge to proximate to the trailing edge; wherein the at least one serpentine cooling channel includes a first turn manifold in communication with a first pass and positioned at least partially in the first endwall at the first end and includes a plurality of trip strips protruding inwardly from an inner surface of a suction sidewall forming the suction side toward the pressure side and includes a plurality of trip strips protruding inwardly from an inner surface of a pressure sidewall forming the pressure side toward the suction side; wherein the trip strips on the suction sidewall are offset from the trip strips on the pressure sidewall.