大密流比高亚音叶型优化设计  

Optimization Design of High Subsonic Profiles with Large Axial Velocity Density Ratio

作　　者：孔祥雪 周正贵[1] KONG Xiangxue;ZHOU Zhenggui(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2021年第2期36-39,共4页Machine Building & Automation

基　　金：国家科技重大专项(2017-Ⅱ-0001-0013)。

摘　　要：二维叶型是构成轴流压气机三维叶片的基本元素。密流比是影响由回转面二维型所构成叶栅气动性能的重要参数。采用基于遗传算法的优化平台,进行大密流比高亚音叶型优化设计;研究目标函数设置方法并考察大密流比情况下载荷分布规律。研究表明:以设计工况点参数为目标进行单工况优化不仅可有效提高设计工况性能,也可以有效提高非设计工况性能;对于大密流比高亚音静子/转子叶型,载荷沿弦向分布较均匀,不呈前加载特性;对于大安装角转子叶型,压力面局部凸起与吸力面尾缘配合,形成收缩流道,可抑制吸力面尾缘流动分离。The two-dimensional profile is the basic element of the three-dimensional blade of the axial flow compressor.Axial velocity density ratio is an important parameter that affects the aerodynamic performance of the cascade formed by a two-dimensional profile of the revolution surface.The optimization platform based on genetic algorithm was used to optimize the design of high subsonic blade profiles with large axial velocity density ratio.The method of setting the weighting factor in objective function was studied and the load distribution law in the case of large axial velocity density ratio was investigated.The research shows that the optimization of single condition with the parameters of the design condition as the target can effectively improve the performances of the design and off-design conditions.For high subsonic stator/rotor blades with large axial velocity density ratio,the load distribution is more uniform along the chord direction and does not show the front loading characteristic.For the rotor blade profile with large stagger angle,the pressure surface local bulge coordinates with the trailing edge of the suction surface to form a contraction channel,which can suppress the flow separation of the trailing edge of the suction surface.

关 键 词：压气机 轴向密流比 可控扩散叶型 优化设计 载荷分布 

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]