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Turbomachinery blades are an integral part of air breathing propulsion systems, gas and steam turbines and other energy conversion devices. The blade design is a very important process since it defines component performance. A parametric approach for the blade geometry design has been implemented. A variety of three dimensional blade shapes can be created using only a few basic parameters and limited interaction with a CAD system. Using a general approach for creating the blade geometries makes the process easy and robust for creating 3D blade shapes for various turbomachinery components. The geometry of the blade is defined by a very basic set of geometric and aerodynamic parameters. Parameters such as flow angles, axial chord, thickness to chord ratio and streamline meridional coordinates are defined. The leading edge and trailing edge are defined by curves as part of the input. Using these parameters, a specified number of 2D airfoils are created and are radially stacked on the desired stacking axis. The sweep and lean perturbations of the blade are defined by splines as a function of a few control points. The design tool generates a specified number of 3D blade sections and each section consists of a defined number of coordinates in the cartesian coordinate system. These section