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在高马赫数飞行下,超燃冲压发动机的燃料冷却量大于燃料燃烧量。为了降低燃料的冷却量以及实现燃料冷却量和燃烧量的匹配,采用分析法对超燃冲压发动机壁面燃料冷却工质在超临界压力下进行做功潜力分析。发动机壁面冷却燃料的特性决定其热量大小。根据发动机壁面温度分布、热流密度分布计算热量,建立稳定流动燃料工质的平衡方程。结果表明:在壁面最高温度为1200 K时,传入壁面的热量为562.4 k W,其中理论热量为541.3 k W;冷却燃料工质流量增加,最大输出功减小;燃料工质出口温度增加,输出功减小;燃料工质出口压力增加,输出功基本不变。
At high Mach numbers, the scramjet’s fuel cooling is greater than the amount of fuel it burns. In order to reduce the amount of fuel cooling and achieve the matching of fuel cooling and combustion, analytical method was used to analyze the work potential of the fuel cooling fluid in the scramjet engine under supercritical pressure. Engine wall cooling fuel properties determine the size of its heat. According to the engine wall temperature distribution, heat flux density calculation of heat, the establishment of a stable flow of fuel refrigerant balance equation. The results show that when the maximum wall temperature is 1200 K, the heat input into the wall is 562.4 k W, of which the theoretical heat is 541.3 k W; the flow rate of cooling fuel increases and the maximum output power decreases; the outlet temperature of fuel medium increases, The output is reduced; the outlet pressure of the fuel medium increases, the output power basically unchanged.