Turbine airfoil platform segment with film cooling hole arrangement

A gas turbine engine comprising:

• a compressor section;
• a combustor fluidly connected to the compressor section;
• a turbine section fluidly connected to the combustor, the turbine section includes an array of turbine airfoil segments, each turbine airfoil segment comprising:
• inner and outer platforms that are joined by at least one airfoil to form a segment that has an arc, the at least one airfoil includes leading and trailing edges that are joined by spaced apart first and second sides to provide an exterior airfoil surface, and at least one of the inner and outer platforms includes film cooling holes that have external breakout points that are located in substantial conformance with the Cartesian coordinates set forth in Table 1 for the inner platform or Table 2 for the outer platform, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, wherein the zero-coordinate is at point, Pt, located with respect to the curvature of the arc of the segment, and the film cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.20 inches (5.0 mm).