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为研究两级脉冲爆震发动机中激波聚焦起爆技术,研制了激波会聚起爆原理样机,建立了整套实验系统.利用三维激波会聚起爆原理样机,开展了导流角度、气流出口面积、尾喷管扩张角、凹面腔与射流入口间距离等对凹面腔内气动振荡频率和压力影响的冷态实验研究.结果表明:导流角增大,气动振荡频率增大;气流出口面积减小,气动振荡频率增大,凹面腔底部动态压力脉动幅值增大;喷管扩张角度增大,气动振荡频率数目增多;随着凹面腔与环形射流入口间的距离L增长,气动振荡频率降低,凹面腔底部动态压力脉动幅值降低.
In order to study the shock focusing initiation technology of two-stage pulse detonation engine, a prototype of shock convergence initiation principle was developed and a set of experimental system was established.Based on the three-dimensional shock convergence prototype prototype, the diversion angle, air outlet area, tail Nozzle expansion angle and the distance between the concave cavity and the entrance of the jet. The results show that: the air conduction angle increases and the frequency of pneumatic oscillation increases; the air outlet area decreases, The frequency of pneumatic oscillation increases and the amplitude of dynamic pressure pulsation increases at the bottom of concave cavity. The nozzle expansion angle increases and the number of pneumatic oscillation frequency increases. As the distance L between concave cavity and annular jet inlet increases, the frequency of pneumatic oscillation decreases, The dynamic pressure pulsation amplitude at the bottom of the chamber is reduced.