摘要
采用基于雷诺平均N-S方程的全三维流场模拟程序和基于多目标遗传算法的数值优化程序,对跨音压气机转子NASA Rotor37进行了优化设计。对所开发的三维N-S方程求解程序进行了实验验证,完善了多目标遗传算法与响应面方法相结合的具有全局寻优能力的优化程序,以总压比和绝热效率最大为设计目标,应用该优化方法对NASA Rotor37进行考虑中弧线和厚度分布的多目标气动优化设计。结果表明:在满足流量约束的条件下,绝热效率提高了0.7%,总压比提高了0.66%,并且优化设计时间大幅减小。
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.
出处
《吉林大学学报（工学版）》
EI
CAS
CSCD
北大核心
2010年第1期299-304,共6页
Journal of Jilin University:Engineering and Technology Edition
基金
'973'国家重点基础研究发展计划项目(2007CB210104)
关键词
航空
航天推进系统
跨音压气机转子
多目标优化设计
中弧线
厚度分布
响应面
propulsion system of aviation and aerospace
transonic compressor rotor
multi-objective optimization design
camber line
thickness distribution
response surface
