等离子体激励对串列叶栅流动分离抑制效果的数值仿真  

Numerical Simulation of Plasma Excitation on the Effect of Tandem Cascade Flow Separation Suppression

作　　者：陈景波 丁均梁 张海灯 郭基联[3] CHEN Jing-bo;DING Jun-liang;ZHANG Hai-deng;GUO Ji-lian(No. 1 Middle School of Lanxi City,Zhejiang Province,Lanxi Zhejiang 321100,China;Air Force Engineering University Plasma Dynamic Laboratory,Xi'an 710038,China;Air Force Engineering University Aviation Engineering Institute,Xi'an 710038,China)

机构地区：[1]浙江省兰溪市第一中学,浙江兰溪321100 [2]空军工程大学等离子动力学重点实验室,西安710038 [3]空军工程大学航空工程学院,西安710038

出　　处：《航空发动机》2019年第1期22-27,共6页Aeroengine

摘　　要：为了探究不同等离子体激励布局对串列叶栅角区流动分离抑制的效果,采用数值仿真方法,在流动分离前施加激励,对不同布局激励前后流场的流场结构和总压损失沿流向分布进行对比,分析了等离子体激励布局对串列叶栅角区流动分离的影响,以及激励对串列叶栅气流掺混的影响。结果表明:在来流马赫数为0.5、攻角为4°时,ACU2布局激励对流动分离有较好的抑制作用,总压损失系数减小10.74%;ACU2-ACU5组合激励对抑制后排叶片的角区分离有较好效果,总压损失系数降低25.09%。The effect of different plasma excitation layouts on the suppression of flow separation in the tandem cascade angular region was investigated by numerical simulation method.The excitation was brought to bear before flow separation.The structure of flow field and the distribution of total pressure loss along the direction of flow before and after different excitation layouts were compared.The effect of plasma excitation on flow separation in the tandem cascade angle region and the effect of excitation on tandem cascade flow mixing were analyzed.The results show that when the inlet Mach number is 0.5 and the attack angle is 4°,the ACU2 layout excitation has a better effect on the flow separation,and the total pressure loss coefficient is reduced by 10.74%.The combined excitation of ACU2-ACU5 has a better effect on restraining the angle region separation of the rear row blade,and the coefficient of total pressure loss is reduced by 25.09%.

关 键 词：等离子体流动控制 组合激励 串列叶栅 流动分离 数值模拟 总压损失系数 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]