Turbine rotor blade airfoil profile
Various embodiments of the disclosure include turbine rotor blades and systems employing such blades. Various embodiments include a turbine rotor blade having: an airfoil having an airfoil 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 an origin at a pressure side, aftmost point of an endwall coupled to the airfoil. 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. The X and Y values are connected by smooth continuing arcs to 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.
1 . A turbine rotor blade 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.
2 . The turbine rotor blade of claim 1 , wherein the turbine rotor blade includes a first stage blade.
3 . The turbine rotor blade of claim 1 , further comprising a fillet connecting a surface of the endwall to a surface of the airfoil.
4 . The turbine rotor blade of claim 1 , wherein the shape having the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 10% and 92% of the height of the airfoil.
5 . 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.
6 . The turbine rotor blade stage of claim 5 , further comprising a fillet connecting a surface of the endwall to a surface of the airfoil.
7 . The turbine rotor blade stage of claim 5 , wherein the turbine rotor blade stage is a first stage blade section.
8 . The turbine rotor blade stage of claim 5 , wherein the shape having the nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 10% and 92% of the height of the airfoil.
9 . 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.
10 . The turbine section of claim 9 , further comprising a fillet connecting a surface of the endwall to a surface of the airfoil.
11 . The turbine section of claim 9 , wherein the respective turbine stage is a first turbine stage, and the plurality of turbine rotor blades includes first stage rotor blades.
12 . The turbine section of claim 9 , wherein the shape having the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in TABLE I includes the airfoil profile sections defined within 10% and 92% of the height of the airfoil.
13 . The turbine section of claim 9 , wherein the leading edge includes a cooling channel extending through the airfoil that results in a decrease of local temperatures while maintaining aerodynamic performance and minimizing decreases in efficiency of the turbine section.