Outer diameter platform cooling hole system and assembly

A gas turbine engine comprising:

• a compressor section;
• a combustor section;
• and
• a turbine section including a plurality of airfoils, wherein each airfoil projects from an outer diameter platform;
• the outer diameter platform comprising:
• a non-gaspath face;
• and
• a gaspath face coupled to the non-gaspath face via a plurality of cooling holes,
• wherein the plurality of cooling holes comprise a plurality of groups of cooling holes disposed in the outer diameter platform proximate a suction side of a vane and a pressure side of the vane:
• wherein a second group of the plurality of cooling holes is disposed in the outer diameter platform proximate the pressure side and near a leading edge of the airfoil,
• wherein the second group of the plurality of cooling holes has five cooling holes disposed within two rows.

An apparatus, comprising:

• an outer diameter platform comprising:
• a non-gaspath face;
• and
• a gaspath face coupled to the non-gaspath face via a plurality of cooling holes;
• and an airfoil extending from the outer diameter platform, wherein the plurality of cooling holes are formed in substantial conformance with platform cooling hole locations, wherein the locations of the cooling holes are described in terms of Cartesian coordinates defined by along x, y, and z axes and the coordinates of the cooling holes are:
• Hole No.
• X
• Y
• Z
• First Hole
• 0.406
• 0.808
• 2.493
• Second Hole
• 0.278
• 0.884
• 2.504
• Third Hole
• 0.263
• 0.747
• 2.508
• Fourth Hole
• 0.250
• 0.597
• 2.510
• Fifth Hole
• 0.237
• 0.138
• 2.500
• Sixth Hole
• 0.222
• 0.292
• 2.509
• Seventh Hole
• 0.237
• 0.450
• 2.510
• Eighth Hole
• 1.326
• 0.440
• 2.347
• Ninth Hole
• 1.187
• 0.324
• 2.356
• Tenth Hole
• 1.050
• 0.209
• 2.377
• Eleventh Hole
• 0.913
• 0.094
• 2.394
• Twelfth Hole
• 1.424
• 0.982
• 7.341
• Thirteenth Hole
• 1.274
• 0.875
• 2.344
• Fourteenth Hole
• 1.431
• 1.217
• 2.327
• Fifteenth Hole
• 1.313
• 1.250
• 2.321.