US Patent 10156143 Gas turbine engines and related systems involving air-cooled vanes

Gas turbine engines and related systems involving air-cooled vanes are provided. In this regard, a representative vane for a gas turbine engine includes: an airfoil having a leading edge, a pressure surface, a trailing edge and a suction surface; and a cooling air channel; the suction surface being formed by an exterior surface of a first wall portion and an exterior surface of a second wall portion, the first wall portion spanning a length of the suction surface between the second wall portion and the trailing edge; the cooling air channel being defined, at least in part, by an interior surface of the first wall portion, the first wall portion exhibiting a thickness that is thinner than a thickness exhibited by the second wall portion.