Turbine engine airfoil with cooling hole pattern

An apparatus for a turbine engine, comprising:

• a rotor blade including an attachment, a platform, an airfoil and a plurality of cooling holes;
• the platform between and integral with the attachment and the airfoil;
• the airfoil including a tip end, a leading edge, a trailing edge, a first side and a second side, the airfoil projecting spanwise out from the platform to the tip end, and the first side and the second side extending longitudinally between and meeting at the leading edge and the trailing edge;
• and
• the plurality of cooling holes located in the rotor blade according to a set of Cartesian coordinates of Table 1, and the set of Cartesian coordinates of Table 1 describing distances from a point of origin on the airfoil to the plurality of cooling holes.

A turbine engine, comprising:

• a flowpath, a compressor section, a combustor section and a turbine section;
• the flowpath extending through the compressor section, the combustor section and the turbine section from an inlet into the flowpath to an exhaust from the flowpath;
• the turbine section comprising a turbine rotor with a plurality of turbine blades arranged circumferentially about an axis in an array, and a first of the plurality of turbine blades including an airfoil and a plurality of cooling holes;
• the airfoil located in the flowpath, the airfoil including a leading edge, a trailing edge, a suction side and a pressure side, and the suction side and the pressure side extending longitudinally between and meeting at the leading edge and the trailing edge;
• and
• the plurality of cooling holes located in the airfoil according to a set of Cartesian coordinates of Table 1, and the set of Cartesian coordinates of Table 1 describing distances from a point of origin on the airfoil to the plurality of cooling holes.