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在隔离段入口Ma=3(模拟飞行马赫数6.5)条件下,采用乙烯燃料的超燃冲压发动机点火十分困难。为解决该难题,采用了空气节流作为辅助点火措施。基于脉冲燃烧风洞直连式试验平台进行了空气节流点火试验,通过壁面压力测量,获得了节流点火的火焰发展历程。以点火时间为指标,对节流流量、乙烯当量比、节流时间等参数进行了定量分析,节流流量的调节范围为0%~45%,乙烯当量比调节范围为0.6~1.2,节流时间调节范围为190~350ms。分析了三个节流参数各自的作用机理,通过数据拟合,绘制了节流流量与点火时间、乙烯当量比与点火时间的关系曲线,揭示了节流时间与点火时间的关系。
At the entry of the isolation section, Ma = 3 (Flight Simulator 6.5), ignition of a scramjet with ethylene fuel was very difficult. In order to solve this problem, air throttling is used as an auxiliary ignition measure. The air throttling ignition test was carried out based on the pulsed combustion wind tunnel direct-connect test platform. Through the measurement of the wall pressure, the development history of the throttled ignition flame was obtained. The parameters of throttle flow rate, ethylene equivalent ratio, throttle time and so on were quantitatively analyzed with the ignition time as an indicator, the adjustment range of throttle flow was 0% ~ 45%, and the ethylene equivalent ratio adjustment range was 0.6 ~ 1.2. Time adjustment range of 190 ~ 350ms. The mechanism of each of the three throttling parameters is analyzed. The relationship between throttling flow rate, ignition time, ethylene equivalent ratio and ignition time is plotted by data fitting, and the relationship between throttling time and ignition time is revealed.