The Study Of Aerodynamic Design Optimization Method For The Blade Of Turbomachinery

The aerodynamic design optimization method of turbomachinery is studied in this paper. The method used for aerodynamic design optimization of axial turbo-machinery is developed, including blade parameterization method, FLUENT solver, orthogonal design method, gradient-based analysis method and response surface method.Based on the work of our research group, a new method which presents the blade thickness distribution with a cubic and a quartic polynomial is used for improving the blade parameterization method. The variable range of blade profile is increased without increasing the number of design variable, and almost all blade profiles in engineering can be reconstructed by this method. The parameterization method of stacking line is introduced in this paper to obtain curved blade and provide design variables for its optimization. Otherwise, two kinds of design of experiment method are analyzed and compared. The response surface method based on the orthogonal design method is introduced and applied in the aerodynamic design optimization of turbomachinery. The model of response surface method is evaluated by the variance analysis.A VKI gas turbine cascade and a turbine stator are optimized to assess this method. The results show that the thermal loss coefficient of the two cases is respectively decreased about 0.6 and 1.04 percentage point. In additional, according to the result of parameterization and CFD analysis of stacking line, the lean blade is used to improve the flow near the blade hub.The method can be used to control the blade profile and analyze the effect of design variable on the design objective. The satisfactory results show that this method can be used as a good tool of aerodynamic design optimization of blade.