Patent ID: 7581924

Claim:
A turbine vane system comprising: a first turbine vane including a first airfoil with a unitary first outer platform, the first airfoil having an outer end region, an inner end region, an outer peripheral surface, a pressure side, a suction side, a leading edge, a trailing edge, and an airfoil mean line extending from the leading edge to the trailing edge, wherein the first outer platform transitions into the first airfoil in the outer end region, wherein the first outer platform is located substantially entirely on one of the pressure side and the suction side of the first airfoil; and a second turbine vane including a second airfoil with a unitary second outer platform, the second airfoil having an outer end region, an inner end region, a pressure side, a suction side, a leading edge, a trailing edge, and an airfoil mean line extending from the leading edge to the trailing edge, wherein the second outer platform transitions into the second airfoil in the outer end region, wherein the second outer platform is located substantially entirely on the same one of the pressure side and the suction side of the second airfoil as the first outer platform of the first turbine vane, the second outer platform extending substantially circumferentially from the second airfoil to a circumferential side that is contoured to engage at least a portion of the side of the first airfoil opposite the first outer platform, the first vane being positioned substantially adjacent the second vane such that the outer end region of the first airfoil is substantially cooperatively enclosed by the first outer platform and the circumferential end of the second outer platform, wherein a seam is formed between the substantially adjacent portions of the first and second vanes, the seam including a cooling gap extending proximate the side of the first airfoil opposite the first outer platform.