Patent ID: 8944750
Filing Date: 2015-02-03
Classification: F01D,F05D

Abstract:
1. 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 and third rows of holes, the first and second rows of holes extending at least substantially radially adjacent a leading edge of the airfoil portion, and the third row of holes extending at least substantially radially on one side of the airfoil in proximity of a trailing edge thereof, the first, second, and third rows of holes including the holes numbered HA-1 to HA-13, HB-1 to HB-13 and PA-1 to PA-9, 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.