CPC F01D 5/186 (2013.01) [F05D 2240/81 (2013.01); F05D 2260/202 (2013.01)] | 18 Claims |
1. A turbine vane assembly for a gas turbine engine, comprising:
a turbine vane including a leading edge, a pressure edge, a suction edge, and a trailing edge;
a core defined by the turbine vane;
an outer platform end wall connected to the turbine vane, the outer platform end wall defining an interior space, the interior space being in fluid communication with the core; and
a plurality of cooling holes formed in the turbine vane, the plurality of cooling holes being in fluid communication with the core, wherein the plurality of cooling holes are located in the vane according to coordinates of Table 1, wherein the coordinates of Table 1 are distances from a point of origin on the turbine vane assembly.
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