高坤,楚武利,董万峰
GAO Kun,CHU Wu-li,DONG Wan-feng(Northwestern Polytechnical University

• 1:西北工业大学
• 2:西北工业大学
• 3:西北工业大学 陕西西安710072
• 4:陕西西安710072

摘要(Abstract)：

基于商业软件NUMECA的叶轮机械全三维优化设计平台Design3D,采用三维N-S方程流场计算、网格自动生成、三维叶片参数化造型与遗传算法寻优相结合的方法,对一跨音速轴流压气机叶轮进行了三维叶片型线优化设计。优化目标是在流量、总压比不减小的情况下,降低总压损失,以提高其整体效率。优化叶片与原叶片相比,总压损失显著降低,等熵效率提高了1.285%,同时总压比和流量也都得到了提高。通过流场分析,可以看出优化叶片性能的提高主要是源于中上部叶展区域的总压损失的减小,而总压损失的减小则主要归功于分离区的减小和激波的削弱。
With the help of commercial software NUMECA/Design3D,the optimization design of a three dimensional blade profile was carried out for a transonic compressor blade.And it is based on the method consists of three dimensiona Navier-Stokes flow computation,mesh generation automatically,three dimensional blade section parameterization and genetic algorithm.The optimization objective is minmum the overall pressure loss,as wall as keeping the mass flow rate and overall pressure rate not decreasing.Comparing with the baseline design,the optimized solution decreased the total pressure loss greatly,as a result of increasing the isentropic efficiency by 1.285%.At the same time, the mass flow rate and overall pressure rate has improved.Our numerical results show that the gain in aerodynamic performance of resulted designs is largely attributed to the reduction in losses due to shocks and flow separations.

关键词(KeyWords)： 轴流压气机;跨音速;三维;数值优化
axial compressor;transonic;three dimensional;numerical optimization

Abstract:

Keywords:

基金项目(Foundation):

作者(Author): 高坤,楚武利,董万峰
GAO Kun,CHU Wu-li,DONG Wan-feng(Northwestern Polytechnical University

参考文献(References)：

• [1]Oyama A,Liou M S,Obayashi S.Transonic Axial-FlowBlade Shape Optimization Using Evolutionary Al-gorithm and Three-Dimensional Navier-Stokes Solver[J].Journal of Propulsion and Power,2004,20:612-619.
• [2]Lian Y,Liou M S.Multiobjective Optimization UsingCoupled Response Surface Model and Evolutionary Al-gorithm[C].Accepted for publication at AIAA Jour-nal.AIAA Paper 2004-4323.
• [3]Lian Y,Liou M S.Multi-objective Optimization of aTransonic Compressor Blade using Evolutionary Algo-rithm[C].AIAA paper 2005-1816.
• [4]Benini E.Three-Dimensional Multi-Objective DesignOptimization of a Transonic Compressor Rotor[J].Journal of Propulsion and Power,2004,20:559-565.
• [5]Mengistu T,Ghaly W.Single and Multipoint ShapeOptimization of Gas Turbine Blade Cascades[C].AIAA Paper,2004-4446.
• [6]伊卫林,黄鸿雁,韩万金.基于数值优化方法的跨声速压气机掠动叶设计[J].推进技术,2006,27(1):33-36.
• [7]高学林,袁新.叶轮机械全三维粘性气动优化设计系统[J].中国电机工程学报,2006,26(4):88-92.
• [8]周正贵,高亚声速压气机叶片优化设计[J].推进技术,2004,25(1):58-61.
• [9]suder K L Experimental and computational investiga-tion of the tip clearance flow in a transonic axial com-pressor rotor[J].Jounral of Turbomachinery,1996,118(1):218-229.
• [10]Denton J.D.Lessons from Rotor 37.In:3rd Interna-tional Symposium on Aerothermodynamics of InternalFlows[C].Beijing,1996.3-14.
• [11]Smagorinisky J.General circulation expriments withthe primitive equations I:The basic exprement[J].Moth Weather Rev,1963,91(3):99-164.
• [12]Myers R H,Montgomery D C.Response surfacemethodology:Process and product optimization usingdesigned experiments[M].Wiley,NewYork,1995.1-78,351-401.