Optimization of endwall contouring in axial compressor S-shaped ducts  

作　　者：Jin Donghai Liu Xiwu Zhao Weiguang Gui Xingmin 

机构地区：[1]School of Energy and Power Engineering, Beihang University [2]AVIC Aviation Powerplant Research Institute

出　　处：《Chinese Journal of Aeronautics》2015年第4期1076-1086,共11页中国航空学报（英文版）

基　　金：supported by the National Natural Science Foundation of China (Nos.51006005, 51236001);the National Basic Research Program of China (No.2012CB720201);the Fundamen tal Research Funds for the Central Universities of China

摘　　要：This paper presents a numerical investigation of the potential aerodynamic benefits of using endwall contouring in a fairly aggressive duct with six struts based on the platform for endwall design optimization.The platform is constructed by integrating adaptive genetic algorithm（AGA）, design of experiments（DOE）, response surface methodology（RSM） based on the artificial neural network（ANN）, and a 3D Navier–Stokes solver.The visual analysis method based on DOE is used to define the design space and analyze the impact of the design parameters on the target function（response）.Optimization of the axisymmetric and the non-axisymmetric endwall contouring in an S-shaped duct is performed and evaluated to minimize the total pressure loss.The optimal ducts are found to reduce the hub corner separation and suppress the migration of the low momentum fluid.The non-axisymmetric endwall contouring is shown to remove the separation completely and reduce the net duct loss by 32.7%.This paper presents a numerical investigation of the potential aerodynamic benefits of using endwall contouring in a fairly aggressive duct with six struts based on the platform for endwall design optimization.The platform is constructed by integrating adaptive genetic algorithm（AGA）, design of experiments（DOE）, response surface methodology（RSM） based on the artificial neural network（ANN）, and a 3D Navier–Stokes solver.The visual analysis method based on DOE is used to define the design space and analyze the impact of the design parameters on the target function（response）.Optimization of the axisymmetric and the non-axisymmetric endwall contouring in an S-shaped duct is performed and evaluated to minimize the total pressure loss.The optimal ducts are found to reduce the hub corner separation and suppress the migration of the low momentum fluid.The non-axisymmetric endwall contouring is shown to remove the separation completely and reduce the net duct loss by 32.7%.

关 键 词：Adaptive genetic algorithm（AGA） Artificial neural network（ANN） Corner separation Design of experiments（DOE） Endwall contouring OPTIMIZATION Response surfacemethodology （RSM） S-shaped duct 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]