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为了研究航天煤油的富燃燃烧特性,设计了一个气氧/煤油富燃燃气发生器,并进行了室压范围1~4MPa、混合比范围0.25~0.52的燃烧试验,获得了混合比和室压对特征速度、燃气温度及燃烧效率的影响规律。试验结果表明,采用火花塞点火方式可以实现该燃气发生器在高度富燃条件下的可靠点火;在本文研究范围内,试验测得的特征速度和燃气温度明显低于化学平衡理论预测值,燃烧效率介于63.9%~88.3%之间。混合比是特征速度、燃气温度及燃烧效率的最大影响因素,室压的影响远小于混合比。燃烧效率与实际燃气温度与理论燃气温度比值的平方根成正比。
In order to study the rich combustion characteristics of aerospace kerosene, a gas-oxygen / kerosene fuel-rich gas generator was designed and the combustion test was carried out in the pressure range of 1 ~ 4MPa and the mixing ratio of 0.25 ~ 0.52. The mixing ratio and pressure Characteristics of speed, gas temperature and combustion efficiency of the law. The experimental results show that the spark ignition can be used to achieve reliable ignition of the gas generator under highly fuel-rich conditions. Within the scope of this study, the measured characteristic velocities and gas temperatures were significantly lower than those predicted by chemical equilibrium. The combustion efficiency Between 63.9% ~ 88.3%. The mixing ratio is the most influential factor of characteristic velocity, gas temperature and combustion efficiency. The influence of chamber pressure is far less than the mixture ratio. Burning efficiency is proportional to the square root of the ratio of actual gas temperature to theoretical gas temperature.