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为研究分级喷注超燃冲压发动机火焰稳定、燃烧状态及火焰传播特性,以双支板超燃燃烧室为基本构型,开展了当量比连续调节试验研究。模拟低飞行马赫数5.5工况,燃烧室入口马赫数为2,总温1436 K,试验表明:燃烧室单独上游喷注熄火当量比为0.19,该值不受下游燃烧的影响;单独下游喷注熄火当量比为0.46,上游火焰会削弱下游当量比变化对壁面压力的影响,并且会使下游熄火当量比值降低。通过调节上游当量比可实现燃烧状态的转换,转换过程存在迟滞。模拟高飞行马赫数6.5工况,燃烧室入口马赫数为3,总温1 899 K,试验表明:随着总温的增加,单独上游喷注可实现点火和稳焰,上游火焰发生抬举,燃烧室抗反压能力增强,可喷注更多燃料。
In order to study the flame stability, combustion state and flame propagation characteristics of scalpel injection scramjet, the experiment of equivalence ratio continuous adjustment was carried out based on the double-deck scram combustion chamber. Mach number of low flight Mach 5.5 was simulated, Mach number of inlet of combustion chamber was 2, and total temperature was 1436 K. The experiment showed that the equivalence ratio of flameout of single upstream injection of combustion chamber was 0.19, which was not affected by the downstream combustion; The equivalence ratio of flameout is 0.46. The upstream flame will weaken the influence of the downstream equivalence ratio on the wall pressure and will decrease the ratio of the downstream flameout equivalence. The conversion of the combustion state can be achieved by adjusting the upstream equivalence ratio, and there is a hysteresis in the conversion process. Simulated high flight Mach number 6.5, the Mach number of the inlet of the combustion chamber is 3, and the total temperature is 1899 K. The experiment shows that with the increase of the total temperature, the single upstream injection can achieve ignition and steady flame, and the upstream flame is raised and burned Room anti-anti-pressure capability, can inject more fuel.