Abstract:

The full three dimension flow field solver based on ReynoldsAveraged NavierStokes (RANS) equations and the numerical optimization program based on multi-objective genetic algorithm are applied to the optimal design of NASA Rotor37. A flow field solver code is developed based on three dimensional NS equations and validated by comparing computation results with experiment data. An optimization program with the ability of global optimization is developed, which combines multi-objective genetic algorithms with response surface models. This optimization method is applied to the aerodynamic redesign of NASA Rotor37 with camber line and thickness distribution, in which the objectives are to maximize the total pressure ratio and the adiabatic efficiency. Optimization results show that the total pressure ratio is improved by 0.6% and adiabatic efficiency is improved by 0.7%, which validates the multi-objective optimal design method.

Key words: propulsion system of aviation and aerospace, transonic compressor rotor, multi-objective optimization design, camber line, thickness distribution, response surface