引射模态总压比对气动壅塞影响

为了获得高亚音速飞行条件下引射模态射流壅塞情况、提高引射模态火箭射流引射抽吸能力和发动机性能,本文利用全流道一体化数值模拟方法,针对Ma=0.8飞行状态,研究了在无二次燃烧组织的条件下,主次流总压比对引射空气流量、Fabri壅塞的影响规律,结果表明：在低总压比条件下,提高主次流总压比,可提高火箭射流的引射抽吸能力,引射空气流量增大；随着总压比的进一步提高,欠膨胀的火箭射流超声速势核区会挤压引射空气流道,冲压燃烧室反压前传导致引射空气流量降低；主次流总压比高于350,火箭射流会将引射空气流道堵塞,产生Fabri壅塞,引射空气流量降低为零。

Effects of Total Pressure Ratio on Fabri Choking in ejector mode

In order to improve the ejection capacity and engine performance, the effects of total pressure ratio of primary and secondary flows on Fabri choking and ejection capacity were studied on Ma=0.8 subsonic flight status by means of the whole flow-path CFD simulation. The results show that the primary rocket jet ejection capacity could increase with the total pressure ratio of primary and secondary flows, in the low total pressure ratio range. The higher pressure primary rocket jet would expand in the ramjet combustor and squirt the secondary ejection air flow path, therefore reduced the ejection capacity and the ejection air mass flow rate. The primary rocket jet would block the secondary ejection air flow path, therefore the secondary ejection air mass flow reduced to 0, when its total pressure ratio was higher than 350.