Multidisciplinary Design Optimization of Axial Compressor with Double Step Optimization

Abstract

In this paper, multidisciplinary optimization for transonic low pressure compressor has been done. The rotating speed of compressor is 22,000 rpm and the rotor stage is composed of 24 blades. The optimization process is done twice to gain the accurate solution. In order to save computational cost, the first optimization process was conducted by using the Approximation model. The second optimization process was performed full numerical computation for accuracy of the optimization result. Framework is constructed using sensitivity analysis, D-optimal DOE and artificial neural network method. To obtain global optimum, genetic algorithm is used. After the optimization process, the aerodynamic efficiency is raised by 3.69% and the structural safety factor is raised by 234.4%. Nomenclature C x= Blade chord length of x th section β 1x = Inlet angle of x th section β 2x = Exit angle of x th section η = Efficiency of the compressor σ = Stress σ Y = Maximum yield stress SF = Safety factor of the compressor