Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape having has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, Table VIII, Table IX, Table X, Table XI, or Table XII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

Abstract: The present disclosure is directed to a method for scaling an airfoil for placement in a turbomachine. The method disclosed herein includes radially scaling a master airfoil to form a scaled airfoil. The method may also include tuning the scaled airfoil. For example, tuning the scaled airfoil may include axially scaling. The scaled airfoil generally has similar characteristics to the master airfoil.

Abstract: A method of engineering a turbomachine airfoil may include providing a master airfoil configuration having a preset outer and inner radius relative to an axis of rotation thereof. The master airfoil configuration may be radially scaled to a custom-sized turbomachine airfoil having an outer radius different than the preset outer radius of the master airfoil configuration, and/or an inner radius different than the preset inner radius of the master airfoil configuration. Tuning a frequency of the custom-sized turbomachine airfoil by changing a parameter of at least one of a part span shroud and a tip shroud may then be performed. Axial scaling may also be performed. The custom-sized turbomachine airfoil may be employed in the turbomachine without performing wheel box testing, and may exhibit substantially similar operational characteristics as the master airfoil configuration.