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为了研究氢氧火箭发动机推力室喷注器多孔面板的发汗冷却特性,采用一维非热平衡能量方程模型对其进行了数值传热计算,计算模型考虑了冷却剂氢的变物性和多孔结构内固体与流体之间的对流换特征。分析总结了多孔结构固体导热率、孔隙率、颗粒特征直径和燃烧室热流密度等因素对多孔面板发汗冷却的影响。研究结果表明,选择较高导热率的多孔面板制造材料能够降低燃气侧面板温度和减小面板温度梯度;孔隙率一般在0.1～0.2为宜;随着颗粒特征直径增大冷却剂与多孔结构固体之间的换热能力明显下降,燃气侧面板温度呈先降低后升高的趋势。
In order to study the sweat cooling characteristics of porous rocket ejector perforated panels, a one-dimensional non-thermal equilibrium energy equation model was used to calculate the numerical heat transfer. The computational model considered the physical properties of the coolant hydrogen and the porous solid Convection with the fluid between the features. The influences of thermal conductivity, porosity, particle diameter, and heat flux of the combustion chamber on the sweat cooling of porous panels were analyzed and summarized. The results show that the selection of porous materials with higher thermal conductivity can reduce the temperature of the gas side panel and decrease the temperature gradient of the panel. The porosity is generally between 0.1 and 0.2. As the diameter of the particles increases, Between the heat transfer capacity decreased significantly, the temperature of the gas side panel first decreased and then increased.