Turbine nozzle airfoil and/or trailing edge profile

A static nozzle section for a turbine, the static nozzle section comprising:

• a set of static nozzles, the set of static nozzles including at least one nozzle 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
• at least one endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge,
• wherein at least one of a suction side or a pressure side of the airfoil has a shape having a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I, 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,
• wherein the shape having the nominal profile in accordance with the at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 10% and 90% of the height of the airfoil.

A turbine nozzle 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
• at least one endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge,
• wherein at least one of a suction side or a pressure side of the airfoil has a trailing edge shape having a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE II, 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 trailing edge profile sections at each distance Z along at least a portion of the airfoil, the trailing edge profile sections at the Z distances being joined smoothly with one another to form the nominal profile of the trailing edge shape,
• wherein the shape having the nominal profile in accordance with the at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 10% and 90% of the height of the airfoil.