喷管对连续旋转爆轰发动机性能影响数值研究  

Numerical investigation on the effect of nozzle on the performanceof continuous rotating detonation engine

作　　者：邱玉杰 李苏杭 刘仁体 范云锋 陈建平 QIU Yujie;LI Suhang;LIU Renti;FAN Yunfeng;CHEN Jianping(Shanghai Electro-Mechanical Engineering Institute,Shanghai 201109,China)

机构地区：[1]上海机电工程研究所,上海201109

出　　处：《固体火箭技术》2020年第4期414-422,共9页Journal of Solid Rocket Technology

摘　　要：为研究尾喷管构型对连续旋转爆轰发动机性能的影响,采用内径40 mm,外径60 mm,长度50 mm的环形燃烧室,空气为氧化剂,氢气为燃料,对安装等直喷管、收敛喷管、扩张喷管和拉瓦尔喷管的连续旋转爆轰发动机的内外流场进行数值模拟。获得了不同尾喷管条件下爆轰波的传播特性和流场结构,分析了喷管构型对发动机内外流场结构和推进性能的影响。计算结果表明,不同尾喷管条件下,燃烧室内均能形成稳定传播的爆轰波;与等直喷管相比,收敛喷管和拉瓦尔喷管对燃烧室内的爆轰波的压力和传播速度具有明显提升作用,但波头高度则明显降低,安装扩张喷管条件爆轰波压力和传播速度略微有所降低,波头高度却增加。收敛喷管和拉瓦尔喷管对发动机尾部火焰具有一定的约束作用;在给定的发动机模型下,收敛喷管对发动机的推力性能提升最为显著,其推力和比冲分别为259.4 N和120.3 s,扩张喷管则降低了发动机的推力性能。To investigate the effect of the nozzle configuration on the performance of continuous rotating detonation engine,the internal and external flow fields of continuous rotating detonation engine equipped with straight nozzle,convergent nozzle,expansion nozzle and Laval nozzle were numerically simulated by using an annular combustor with an inner diameter of 40 mm,an outer diameter of 60 mm,a length of 50 mm,and air as oxidant and hydrogen as fuel.The propagation characteristics and flow field structure of detonation wave under different nozzle conditions were obtained.The influence of nozzle configuration on the flow field structure and propulsion performance was analyzed.The calculation results show that the detonation wave propagates steadily in the combustion chamber under different nozzle conditions;compared with the straight nozzle,the convergent nozzle and the Laval nozzle can obviously increase the pressure and propagation velocity of detonation wave in the combustion chamber,but the wave head height decreases obviously;under the expansion nozzle condition,the detonation pressure and propagation velocity are slightly reduced,but the height of the wave head is increased.Converging nozzle and Laval nozzle have a certain restraining effect on the rear tail flame of the engine;under the given engine model,the thrust performance of convergent nozzle is improved most significantly,and its thrust and specific impulse are 259.4 N and 120.3 s respectively.The expansion nozzle reduces the thrust performance of the engine.

关 键 词：连续旋转爆轰发动机 喷管 三维数值模拟 内外流场 推进性能 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]