Turbine rotor blade airfoil profile

A turbine rotor blade stage for a turbine section of a turbomachine, the turbine rotor blade stage comprising:

• a set of turbine rotor blades, the set of turbine rotor blades including at least one turbine rotor blade having:
• an airfoil having:
• a suction side, a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side;
• and
• an endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, the endwall defining an origin at a pressure side, aftmost point;
• wherein the airfoil has a shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I and originating at the origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define airfoil profile sections at each distance Z along at least a portion of the airfoil, the airfoil profile sections at the Z distances being joined smoothly with one another to form the nominal profile.

A turbine section comprising a plurality of turbine stages each having a plurality of turbine rotor blades, each of the plurality of turbine rotor blades in a respective turbine stage comprising:

• an airfoil having:
• a suction side, a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side;
• and
• an endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, the endwall defining an origin at a pressure side, aftmost point;
• wherein the airfoil has a shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I and originating at the origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance, and wherein X and Y values connected by smooth continuing arcs define airfoil profile sections at each distance Z along at least a portion of the airfoil, the airfoil profile sections at the Z distances being joined smoothly with one another to form the nominal profile.