共用尾喷管多管脉冲爆震发动机数值模拟研究  

Numerical investigation of multi-tube pulse detonation engine with common nozzle

作　　者：李建中[1] 王家骅[1] 王春[2] 张德良[2] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]中国科学院力学研究所高温气动重点试验室,北京100080

出　　处：《空气动力学学报》2008年第1期96-100,共5页Acta Aerodynamica Sinica

基　　金：南京航空航天大学科研创新基金资助(Y0802-021)

摘　　要：采用基元反应模型和显式迎风TVD差分格式数值模拟方法,研究共用尾喷管多管脉冲爆震发动机(PulseDetonation Engine,简称PDE)各爆震管之间相互影响。采用点隐算法解决化学反应引起的刚性问题,模拟了共用尾喷管内的流场,以及爆震波退化为激波遇到尾喷管收敛斜面反射及反射波向爆震管上游传播的过程。研究结果为多管PDE的共用尾喷管设计提供了理论基础。The flow-field interaction among detonation tubes sharing a common nozzle in a multi-tube pulse detonation was investigated and explicit TVD scheme was adopted to solve two-dimensional Euler equations implemented with detailed chemical reaction kinetics of hydrogen/air mixture. Point Implicit method was applied to treat the stiff problem arising from computation of chemical reaction flow. The flow-field of common nozzle was simulated numerically. When detonation wave went out the tube, the detonation wave declined and turned into shock wave. The shock wave reflection over common nozzle surface and the reflected shock wave traversing back up the other tube were simulated numerically. The numerical simulation result is of importance to supply theory and practice for optimizing common nozzle of multi - tube pulse detonation engine.

关 键 词：脉冲爆震发动机 数值模拟 共用尾喷管 基元反应模型 

分 类 号：V235.22[航空宇航科学与技术—航空宇航推进理论与工程]