摘要
针对脉冲爆震发动机地面启动问题,采用非稳态二维轴对称数值模拟的方法对多循环火箭式脉冲爆震发动机引射模态,即爆震管加直管引射器的引射过程进行了研究。同时通过爆震引射的实验获得引射比作为比较参数。引射比的计算结果与实验数据基本吻合。提出了爆震非稳态引射的3个阶段和相应的3种作用机制即:激波的压缩加速;射流卷吸;惯性和压差作用,并为下一步主爆震管燃油喷注位置提供了设计依据。
Numerical investigation was conducted in which ejecting mode of a multi-cycle pulsed detonation rocket engine with a simple cylindrical ejector was simulated using unsteady axisymmetric N-S Eqs. Experiments were carried out to measure the ejection ratio,which was used as the comparative parameter. The result of simulation is in good agreement with that of experiment. Ejecting process was divided into three phases corresponding to three different working mechanisms： （1） air compression and acceleration by shockwave; （2） shearing and dragging of the plume; （3） action of inertia and pressure gradients. The simulation result can also be used as a reference for the design of fuel injection.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2005年第4期645-650,共6页
Journal of Aerospace Power
基金
国家自然科学基金资助(50336030)
关键词
航空
航天推进系统
脉冲爆震发动机
非稳态引射
数值模拟
多循环
aerospace propulsion system
pulse detonation engine
unsteady ejection
numerical simulation
multi-cycle
