激波聚焦诱导气液两相爆震燃烧的数值模拟  

Numerical simulation on gas-liquid two-phase detonation combustion induced by shock wave focusing

作　　者：杨青[1] 李志强[1] 邸亚超[1] 许欢[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》2014年第8期1802-1809,共8页Journal of Aerospace Power

摘　　要：对以激波聚焦和增加障碍物方式诱导煤油-空气气液两相爆震燃烧的过程进行了数值模拟.采用欧拉-拉格朗日方法建立了脉冲爆震发动机(PDE)中气液两相流的喷射、雾化、掺混过程.研究发现环形爆震波在爆震管凹腔内经过反射、汇聚后能够引燃可燃混合物.而在障碍物处,激波的反射和再反射聚焦能够形成高温高压点(2700K,25MPa),产生局部爆炸,有助于形成稳定的脉冲爆震燃烧(波面速度为1900m/s,温度为2 950K),有效地缩短由缓燃向爆震转变(DDT)距离至0.45m.Numerical simulation on gas-liquid two-phase detonation combustion of kero- sene-air was conducted induced by shock wave focusing and setting obstacles. The numerical model of gas-liquid two-phase flow was established for the fuel injection, atomization and mixing of pulse detonation engine （PDE） by an Eulerian-Lagrangian formulation. Computa- tional results show that the reflection and focusing of the ring shock wave can ignite the combustible mixture inside the capacity of detonation tube. Rereflection and focusing of the reflecting shock wave could form higher temperature and pressure points （2 700 K, 25 MPa） near the obstacles, which can lead to local explosion, further generate stable pulse detonation combustion （velocity of 1900m/s, temperature of 2950K） and shorten the length of def lagration to detonation transition （DDT） to 0.45 m effectively.

关 键 词：激波聚焦 爆震燃烧 气液两相 脉冲爆震发动机 由缓燃向爆震转变 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]