两相脉冲爆轰发动机尾喷管的实验研究

Experimental Investigation on Nozzles of Two-Phase Pulse Detonation Engine

为了提高脉冲爆轰发动机的推进性能,实验研究了12种不同构型尾喷管对火箭式两相脉冲爆轰发动机爆轰特性和推进性能的影响,并对各类尾喷管的增推原因进行分析。结果表明满填充工况下各类喷管内的爆轰特性不尽相同,收敛喷管可得到最大压力峰值;在满填充工况下频率为10Hz时12种喷管构型中拉伐尔喷管的推力增益最大,塞式收敛扩张喷管其次;拉伐尔喷管的出口面积比对推力增益有较大影响,但收敛段-扩张段长度比对推力增益影响甚微。

Pulse detonation rocket engines( PDREs) with twelve different nozzles were studied experimentally to evaluate their detonation characteristics and propulsive performance in multi-cycle systems. The reason of the thrust variations of two-phase PDREs affected by different nozzles was analyzed. As the results,the detonation waves are quite different in the tested nozzles of PDREs,with the highest pressure peak appearing in the convergent nozzle when the engines are full filled with fuel. It is also found that the Laval nozzle offers the highest thrust augmentation among the tested nozzles,followed by the plug-in-convergent-divergent nozzle at the operation frequency of 10Hz. In addition,the exit-to-inlet area ratio of the Laval nozzle has significant influence on thrust augmentation,while the convergent-to-divergent length ratio has little influence.