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介绍了流体、固体传热耦合的一维分析方法,对带主动冷却系统的马赫数2.5超声速燃烧室进行了传热分析。该分析以实验测量的燃烧室壁面静压以及超临界煤油换热特性数据为基础,考虑了燃气的高温离解效应,燃烧特性以及碳氢燃料的高温热物理特性,对不同燃烧状态、冷却条件下的主动冷却过程进行了分析。结果表明有燃烧时壁面热流可高达1MW/m2以上,是无燃烧时的2～3倍。当煤油流量较小时(当量比为0.45),冷却后的壁面温度仍偏高,而且冷却壁内温度分布不均匀。随着煤油流量的增加,冷却效果明显提高,冷却壁内温度分布趋于均匀;并且煤油的出口温度也显著减小。
The one-dimensional analysis method of fluid-solid heat transfer coupling is introduced. The heat transfer analysis of Mach 2.5 supersonic combustion chamber with active cooling system is carried out. Based on the experimentally measured wall static pressure of the combustion chamber and the heat transfer characteristics of supercritical kerosene, the analysis takes into account the high-temperature dissociation effect, the combustion characteristics and the high-temperature thermophysical properties of the hydrocarbon fuels. Under different combustion conditions and cooling conditions The active cooling process was analyzed. The results show that when the combustion heat flow wall surface can be as high as 1MW / m2, is 2 to 3 times when no combustion. When the flow rate of kerosene is small (equivalent ratio is 0.45), the wall temperature after cooling is still high, and the temperature distribution in the cooling wall is not uniform. With the increase of kerosene flow rate, the cooling effect is obviously improved, the temperature distribution in the cooling wall tends to be uniform, and the outlet temperature of kerosene also decreases significantly.