A NASA(National Aeronautics and Space Administration) transonic single stage turbine was taken as an example

describing how to use an aerodynamic numerical optimization platform to find the optimal solution.The platform had three parts:parameterization and fitting of blades

simulation of flow field and optimization strategy.Blades were parameterized based on non-uniform rational B-splines(NURBS) curve.Integrated optimizationstrategy which included DOE(design of experiments) method and genetic algorithm was used to find the global optimal solution.Results show that the performance is improved at the optimized work point.The platform provides a useful reference for analogous optimization of axial turbomachinery blades.