一种改进的压气机叶尖泄漏流堵塞预估模型及数值验证  

Modified blockage model of tip leakage flow and its validation

作　　者：程朝青[1] 崔健[1] 李志平[1] 龚一方[1] 李秋实[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191

出　　处：《航空动力学报》2011年第5期1104-1110,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(10902008;50906001)

摘　　要：基于压气机叶尖间隙内的流动为Couette流动的实际情况,改进了适用于低速压气机的麻省理工学院Khalid叶尖泄漏堵塞预估模型;同时考虑叶尖泄漏流经过激波后堵塞迅速增加,发展了适用于跨声速压气机的叶尖泄漏流堵塞预估模型.对某低速轴流压气机单转子、跨声压气机单转子进行全三维黏性数值模拟,将计算得到的叶尖泄漏堵塞量与模型预测得到的堵塞量进行对比,结果表明此模型较Khalid模型能够更加准确地预测低速压气机的堵塞,同时能够用于预测跨声压气机叶尖泄漏流堵塞.Based on the common cognition of the tip clearance flow,which has a significant influence on compressor performance and MIT（Massachusetts Institute of Technology） Khalid tip leakage model,a blockage model of tip leakage flow in the condition of low-speed and transonic was deduced in this paper.With analysis of the real flow case in tip clearance and diffusion passage,the aerodynamic design parameters,such as loading,cord length,etc,on the rotor tip and the influence of shock wave on tip leakage loss were analyzed in this model.The three-dimensional numerical simulation results show that this model can track the behaviors of jam resulted from compressor tip clearance flow.

关 键 词：压气机 叶尖间隙 泄漏流 泄漏涡 堵塞 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]