Patent ID: 8568085

Claim:
A turbine vane for a gas turbine engine comprising an airfoil portion defined by a perimeter wall surrounding an enclosure, the perimeter wall having a plurality of cooling holes defined therethrough and providing fluid communication between the enclosure and a gaspath of the gas turbine engine, the plurality of cooling holes including first, second, third and fourth rows of holes, the first and second rows of holes extending at least substantially radially adjacent a leading edge of the airfoil portion, the third now of holes extending at least substantially radially on one side of the airfoil in proximity of a trailing edge thereof, and the fourth row of holes extending at least substantially radially on the opposed side of the airfoil in proximity of the leading edge, the first, second, third and fourth rows of holes including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.