推力室多孔面板氢发汗冷却传热分析

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。

Numerical analysis of H2 transpiration cooling for thrust chamber porous plate

In order to investigate the transpiration cooling characteristics of H/O rocket engine thrust chamber injector porous plate, the one-dimensional local thermal non-equilibrium numerical model was adopted to conduct the heat transfer computation and analysis. The hydrogen coolant ther- too-physical properties varied with both temperature and pressure, and heat transfer between the porous media and coolant were considered for the computation model. The influence of porous media thermal conductivity, porosity, sphere diameter and heat flow density on porous plate transpiration cooling were analyzed. The investigation demonstrates that optimization of porous plate material with high thermal conductivity can reduce the gas side plate temperature and temperature gradient of porous plate. The porosity should be 0.1-0.2. The heat transfer capacity between the porous media and coolant is obviously reduced with the increase of sphere diameter, but the temperature of the gas side plate decreases at first and then increases.