抽吸气对高负荷跨声双级风扇裕度影响的数值研究  

Numerical Research of the Effects of Blade Thickness Parameter on Compressor Rotor Blade Flutter

作　　者：陆庆飞[1] LU Qing-fei （China Gas Turbine Establishment, Chengdu 610500, China）

机构地区：[1]中国燃气涡轮研究院,四川成都610500

出　　处：《燃气涡轮试验与研究》2012年第2期18-20,42,共4页Gas Turbine Experiment and Research

摘　　要：采用计算流体力学与结构动力学相结合的方法，数值模拟了大负荷弯掠扭组合叶片非定常粘性流场；通过对叶片表面非定常气动力及其所做非定常气动功的计算分析，采用能量法对叶片颤振与否进行预估判断。在气动设计满足设计要求的基础上，小范围调整大负荷弯掠扭组合叶片的最大厚度分布和最大厚度相对位置分布，并分别进行颤振预估计算。结果表明，最大厚度分布和最大厚度相对位置分布对颤振影响明显。在最大厚度相对位置分布相同的情况下，均匀减薄叶片，会使一阶动频减小，积累功率增大，颤振发生的可能性增大。研究结果对叶轮机颤振机理研究具有一定的参考意义。The numerical simulation of unsteady viscous flow filed of heavy load bent, swept and twisted blades has been made by using the method of the coupling of CFD and CSD. According to the calculation and analysis of the unsteady aerodynamic force and the resulting work, it is estimated whether the blade flut- ter occurs by adopting the energy method. When aerodynamic design fulfilling the demands, the distribution of the blade maximum thickness and the relative location is adjusted in little range and the flutter computa- tion is executed. The calculated results showed the significant effects of the blade maximum thickness and the relative location on flutter. The blade thickness reduction made the first-order frequency decrease and accumulated power increase in the case of the same location of the maximum thickness. Consequently, the possibility of blade flutter increased. The result of present investigation will be referential for the turboma- chinery flutter mechanism.

关 键 词：大负荷弯掠扭组合叶片 最大厚度分布 最大厚度相对位置分布 颤振 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程;航空宇航科学技术]