载荷分布对可控扩散叶型性能的影响  

Effects of Load Distribution on Controlled Diffusion Airfoils Aerodynamic Performance

作　　者：李梦雪 周正贵[1] LI Meng-xue;ZHOU Zheng-gui(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,南京210016

出　　处：《科学技术与工程》2020年第30期12618-12629,共12页Science Technology and Engineering

基　　金：国家科技重大专项(2017-II-0001-0013)。

摘　　要：叶型吸力面和压力面等熵马赫数分布符合控制扩散规律,则其设计点损失小、低损失攻角范围大。为了研究可控扩散叶型载荷分布对叶栅气动性能的影响,建立了可控扩散叶型自动优化设计方法;并对叶栅进口马赫数为0.7的静子和转子叶型进行多个载荷分布设计,分析载荷分布规律对叶栅性能的影响。结果表明:对于静子及转子叶型,载荷前移(至0.1倍相对轴向弦长位置)可抑制吸力面附面层发展,降低设计进气角损失、增大低损失攻角范围;吸力面峰值马赫数增大,吸力面靠前缘凸起程度越大,小攻角损失增加、最低损失对应进气角增大。研究表明载荷分布影响气流加速及扩压梯度大小,进而影响激波产生和附面层发展,导致全攻角范围内性能变化。The distribution of isentropic Mach number of the airfoil’s suction side and pressure side accord with the control diffusion criteria,in which the design point loss is low and the operating range is wide.To study the influence of the load distribution on the aerodynamic performance of the cascades,an automatic optimization design method for controlled diffusion airfoils was established,several load distribution designs were carried out for the stator and rotor airfoils with the inlet Mach number of 0.7,and the influence of the load distribution law on the performance of the cascades was analyzed.The results show that for the stator and rotor airfoils,the front-loading(forward to 0.1 times of the relative axial chord length)is helpful to inhibit boundary layer development,reduce the design point loss,and increase the operating range;the peak Mach number of suction side increases,the camber near the leading edge of airfoil suction side increases,loss under small incidence increases,and the inlet flow angle corresponds to the minimum loss increases.The study also shows that the load distribution affects airflow’s acceleration and adverse pressure gradient,which in turn affects the generation of shock waves and the development of boundary layer,resulting in performance changes within the full angle of attack.

关 键 词：可控扩散叶型 优化设计 载荷分布 气动设计 数值模拟 

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]