AERODYNAMIC DESIGN OPTIMIZATION OF CASCADE AIRFOILS AND COMPRESSOR BLADE BASED ON GENETIC ALGORITHM
A direct numerical optimization method using genetic algorithms (GAs) has been developed. The algorithm with Pareto ranking and fitness sharing techniques was used for multiobjective design optimization of a two-dimensional compressor cascade airfoil to seek low total pressure loss coefficient and high static pressure ratio at the same time. Pareto solutions can provide not bad design plans for decision maker to select. The platform was also used for design optimization of the stacking line of an advanced transonic stage (ATS-2) stator to seek high adiabatic efficiency. The stage efficiency is increased by 0.502％ at optimal point and detail numerical study is presented in this paper. The flow fields of the cascade airfoils and the transonic stage were simulated with FINE/Turbo software package. The optimization results indicate that the present algorithm is provided with flexibility, reliability and robustness, and the optimization platform is effective and efficient in single/multi-objective aerodynamic design optimization.
compressor genetic algorithm optimization
JIN Dong-hai GUI Xing-min
School of Jet Propulsion, Beihang University Beijing, 100083 P.R.China
国际会议
昆明
英文
391-399
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）