摘要
采用数值优化方法对跨声速压气机转子NASA rotor37进行了多目标的数值三维气动优化设计,并对设计前后的几何形状、总体性能及流场的变化进行了详细的分析对比。结果表明,利用多目标遗传算法或者多目标模拟退火算法进行多目标的气动优化设计所得出的分布是基本一致的。各性能参数及流场结构的变化还是主要来源于前缘激波结构的变化。
Numerical optimization design was carried out on the multi-objective optimization design of the rotor of transonic compressor NASA rotor37. And then, the changes of geometry, overall performance and flow field were analyzed and compared in detail. The result shows that flow field distribution of aerodynamic multi-objective optimization design is same by using multi-objective genetic algorithm and simulated annealing algorithm. Leading edge shock wave structure is the main factor leads to the change of performance parameters and flow field structure.
出处
《汽轮机技术》
北大核心
2009年第6期448-450,共3页
Turbine Technology
关键词
跨声速
多目标优化
遗传算法
模拟退火法
transonic
multi-objective optimization
genetic algorithm
simulated annealing algorithm
