A multi-objective technique for designing single stage compressors is described. The blade geometry is defined as a function of known parametric equations, and the coefficient multipliers are viewed as design variables. A design of experiment approach is used to reduce the large combinations of design variables into a smaller subset. A response surface method is used to approximate the performance (total pressure rise, and adiabatic efficiency) as a function of design variables, and an optimum configuration is determined. This method has been applied to a rotor-stator combination similar to NASA Stage 35 with encouraging results.
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