Turbine vanes with airfoil-proximate cooling seam

A turbine vane system comprising:

• a first turbine vane including a first airfoil with a unitary first inner 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, and a trailing edge, wherein the first inner platform transitions into the first airfoil in the inner end region, wherein the first inner 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 inner platform, the second airfoil having an outer end region, an inner end region, a pressure side, a suction side, a leading edge, and a trailing edge, wherein the second inner platform transitions into the second airfoil in the inner end region, wherein the second inner platform is located substantially entirely on the same one of the pressure side and the suction side of the second airfoil as the first inner platform of the first turbine vane, the second inner 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 inner platform,
• the first vane being positioned substantially adjacent the second vane such that the inner end region of the first airfoil is substantially cooperatively enclosed by the first inner platform and the circumferential end of the second inner 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 inner platform.

A method of cooling a portion of an airfoil comprising:

• providing a turbine engine, the turbine engine including a first turbine vane and a second turbine vane,
• the first turbine vane including a first airfoil with a unitary first 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, and a trailing edge, wherein the first platform transitions into the first airfoil in one of the inner end region and the outer end region, wherein the first platform is located substantially entirely on one of the pressure side and the suction side of the first airfoil;
• and
• the second turbine vane including a second airfoil with a unitary second platform, the second airfoil having an outer end region, an inner end region, a pressure side, a suction side, a leading edge, and a trailing edge, wherein the second platform transitions into the second airfoil in one of the outer end region and the inner end region, wherein the second platform is located substantially entirely on the same one of the pressure side and the suction side of the second airfoil as the first platform of the first turbine vane, the second 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 platform,
• the first vane being positioned substantially adjacent the second vane such that one of the outer end region and the inner end region of the first airfoil is substantially cooperatively enclosed by the first platform and the circumferential end of the second 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 platform;
• and
• supplying a coolant to the first and second platforms such that a portion of the coolant leaks through the cooling gap, whereby a portion of the first airfoil proximate the cooling gap is cooled by the leaking coolant.