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为了验证亚燃冲压燃烧室在高空负压条件下稳定工作的能力,设计了带蒸发式值班火焰稳定器与直射式喷油装置的亚燃冲压模型燃烧室,对该模型燃烧室进行了冷态流阻试验、贫油熄火边界试验以及不同截面燃烧效率试验研究。研究结果表明,试验件的冷态流阻系数略大于1,冷态总压恢复系数0.98以上;蒸发式火焰稳定器贫油熄火边界较宽;两截面燃烧效率最低相差6%,最高相差19%,在高空负压条件下,增加燃烧段长度能显著提高燃烧效率。
In order to verify the stability of sub-combustion chamber under the condition of high-altitude negative pressure, a sub-combustion model combustion chamber with evaporating on-duty flame stabilizer and direct injection device was designed. The combustion chamber of this model was cooled Flow resistance test, lean oil flameout boundary test and combustion experiment of different cross sections. The results show that the coefficient of cold flow resistance of the test piece is slightly larger than 1, and the total pressure recovery coefficient of the cold state is 0.98. The evaporative flame stabilizer has a wide range of lean flame extinction, the minimum difference of combustion efficiency between the two cross sections is 6% and the maximum difference is 19% , Under the conditions of negative pressure at high altitude, increasing the length of the combustion section can significantly improve the combustion efficiency.