跨声速风扇叶片的静态气动弹性问题

使用时域的流固耦合数值计算方法,研究了跨声速风扇叶片在气动力和离心力共同作用下的静态气动弹性问题,分析了叶片在不同工况下的变形规律及叶片变形对整体气动性能的影响.NASA rotor 67的静态气动弹性计算说明气动力对叶片最大变形的贡献达13.07%, 而且叶片变形明显地改变了通道激波的位置和强度.宽弦空心跨声速风扇叶片的静态气动弹性计算说明叶片变形对总体气动效率的影响为0.15%~ 0.5%,其中气动力对变形贡献在叶片尖部的前缘可达41%,考虑气动力引起的变形使得该风扇的流量增大,气动特性线整体向右偏移.计算结果说明:气动力的非线性对跨声速风扇叶片静态变形问题有显著的影响,工程实践中从设计叶型到制造叶型的反扭过程应该采用流固耦合方法以得到更准确的叶型. 

Static aeroelastic problems of transonic fan blades

A time domain fluid-solid interaction numerical calculation method was applied to study the static aeroelastic problems of transonic fan blades under aerodynamic and centrifugal forces. The blade deformation rules and its effects on aerodynamic performance were analyzed under various working conditions. Static aeroelastic simulation of the NASA rotor 67 indicates that the aerodynamic contribution to the maximum blade deformation accounts for 13.07% of the total deformation, and the passage shockwave position and strength are altered due to the blade deformation. The static aeroelastic simulation of a wide-chord hollow transonic fan blades reveals that the effects of blade deformation on the aerodynamic efficiency is 0.15%-0.5%. The aerodynamic contribution to total deformation at leading edge is up to 41% and the aerodynamic characteristic map of this fan is shifted rightwards with the increasing mass flow rate. The overall results show that the nonlinearity of aerodynamic force has significant effects on the static aeroelastic property of transonic fan blades, and the blade un-running design in industrial practice should adopt a fluid-solid interaction method to attain more accurate blade shapes.