激波诱导矢量喷管动态数值模拟  

Dynamic Numerical Simulation of Shock Vector Control Exhaust Nozzle

作　　者：马伟[1] 杜刚[1] 金捷[1] 廖华琳[2] 

机构地区：[1]北京航空航天大学能源与动力学院,北京100191 [2]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》2014年第5期30-37,共8页Gas Turbine Experiment and Research

摘　　要：对一二元收扩激波诱导矢量喷管进行了二维动态数值模拟,研究了不同落压比、不同次流加速时间下,喷管气动特性和流场结构随次流增加的变化规律。结果表明:喷管在过膨胀状态下,次流流量达到一定值时,其推力会有较强的振荡;在完全膨胀和欠膨胀状态下,振荡较小。其原因是,次流增加过程中,喷管出口附近有复杂波系存在和回流产生,而回流对提高推力和增加矢量角有益。2D dynamic numerical simulation of a shock vector controlled 2D-CD exhaust nozzle was con-ducted to investigate the effect of increasing secondary mass flow on the internal nozzle performance andflow field structure under different nozzle pressure ratios. Results indicate that when the secondary massreaches a certain value, the thrust of nozzle will undergo a strong oscillation when nozzle is under over-ex-panded condition. The oscillation will be much weaker when nozzle is under either fully expanded or un-der-expanded conditions. This phenomenon is attributed to a series of complex waves near the nozzle outletand the emergence of back flow. It is also concluded that back flow can enhance the performance of nozzleand enlarge the vector angle.

关 键 词：航空发动机 射流推力矢量喷管 激波诱导 动态 数值模拟 

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]