基于遗传算法与响应面模型的压气机叶片气动优化设计  

Aerodynamic design optimization of compressor blade using genetic algorithms and response surface model

作　　者：伊卫林[1] 黄鸿雁[1] 韩万金[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《推进技术》2006年第6期510-514,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金项目(50236020);高校博士点基金项目(20030213022)

摘　　要：对所开发的三维N-S方程求解程序进行了实验验证,开发了集成改进拉丁超立方体试验设计,流场求解程序,二次多项式响应面近似模型,改进遗传算法于一体的具有全局寻优能力的气动设计体系。以绝热效率最大为目标,应用该优化方法对跨声压气机动叶进行弯掠两个自由度的气动优化设计。优化后叶片绝热效率有较大程度的提高,并且具有良好的变工况性能。结果表明了所开发流场求解程序及优化设计方法的良好性能。A flow field solver code was developed based on three dimensional Navier-Stokes equations and validated by comparing the computational results with experimental data. A new global optimization strategy was described for computationally expensive aerodynamic design optimization problems, combined with improved-hypereube-sampling algorithm, a secondorder polynomial response surface models （RSM） , improved genetic algorithm （GA） and 3-D Navier-Stokes solver. This optimization method was applied to aerodynamic redesign of transonic compressor rotor with sweep and curve. The optimized rotor can evidently enhance the adiabatic efficiency and has fine off-design performance. The results showed that both the solver code and the optimization method have fine capability.

关 键 词：压气机 数值仿真 试验设计 遗传算法 优化设计 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]