轴流压气机尾流撞击效应机理的数值模拟  

Numerical simulation of wake impacting effect of axial flow compressor

作　　者：侯安平[1] 熊劲松[1] 周盛[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《北京航空航天大学学报》2005年第9期944-948,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金资助项目(10072008)

摘　　要：通过精确给定转子进口边界条件,以模拟上游静子尾迹对转子流场的影响,这样利用单排的计算结果模拟转/静干涉引起的非定常流动对流场气动参数的影响,因为相邻叶片排的叶片数不同,从而避免传统方法中常用的叶片数约化存在的难以正确模拟非定常激励频率的问题,对计算时间和计算能力的要求也可减少.针对一个低速转子的数值模拟结果显示,如果能合理地组织来流尾迹的扫过频率和尾迹亏损的幅度,对转子气动性能的改善是很显著的,从而为风扇/压气机中控制和利用非定常流动提供了一个可行的方向.By giving accurate inlet boundary condition of rotor to simulate the interaction between rotor and stator, the result of 3D unsteady numerical simulation to a row of rotor＇s flow field can reflect the effect induced by upstream unsteady wakes. Because the number of rotor＇s blades and stator＇s blades is difference, traditional numerical simulation usually can＇t accurately simulate the frequency of upstream unsteady excitation to downstream flow field. This difficulty can be solved by using this method. At the same time, the requirement of computational time and computational capability can be received. The result of numerical simulation to a low velocity axial flow compressor rotor shows that the aerodynamic performance of the rotor can be improved greatly if the deflected amplitude and frequency of upstream wakes were arranged reasonable. Therefore one kind of reasonable methods was presented to control and use unsteady flow in axial flow fan ＆ compressor.

关 键 词：非定常流动 数值模拟 轴流式压缩机 转/静干涉 尾流撞击效应 

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]