Patent ID: 8257035

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, a first endwall at a first end, a second endwall at a second end opposite the first end, and an internal cooling system positioned internally of the outer wall; wherein the outer wall is formed of a non-uniform thickness such that an outer surface of the outer wall extends generally linearly between the first and second ends of the generally elongated airfoil and an inner surface of the outer wall is nonlinear because of accommodating the non-uniform wall thickness; wherein the outer wall is formed of a non-uniform thickness such that aspects of the outer wall positioned between an outboardmost portion of the outer wall and an inboardmost portion of the outer wall are thinner than the outboardmost and inboardmost portions of the outer wall; wherein the outer wall at a midpoint between the outboardmost and inboardmost portions of the outer wall has a thickness that is less than thicknesses of the outer wall at the outboardmost and inboardmost portions of the outer wall; wherein the outer wall between the midpoint and the outboardmost portion has a linearly increasing wall thickness going from the midpoint to the outboardmost portion.