Three-dimensional aerodynamic optimization design method using simulated annealing and response surface model

This paper presents an optimization design system suitable for computationally expensive three-dimensional aerodynamic design problems. The improved Latin hypercube design of experiment was used to select sample points which were then analyzed by a three-dimensional Navier-Stokes solver developed by authors to construct database. The approximation model was established by the quadratic response surface method. Then the model was optimized by using effective simulated annealing algorithm to obtain the optimum design. To demonstrate its performance, the optimization redesign was performed on NASA rotor 67 transonic fan rotor blades with three-dimensional leading-edge stacking line. As a result of the optimization, the pressure ratio was successfully increased by 1.8%, as well as to limit little mass flow and adiabatic change. Then a detailed study of flow structure was presented and the results have proven that this design optimization method can help turbomachinery designers to design higher-performance machines with shorter design cycle and lower design costs.