论文部分内容阅读
提出液体火箭发动机层板推力室再生冷却通道传热过程的数理模型。采用通用形式控制方程处理冷却剂紊流换热和通道材料导热的共轭传热问题 ,计算采用LVEL紊流模型 ,并考虑冷却剂 (氢 )的热物性参数随温度和压力的变化及层板材料热物性随温度的变化。结果表明 ,采用大高宽比、小气壁厚度的通道设计 ,可显著提高再生冷却能力 ,降低室壁温度和温差。采用对流换热系数和热物性为常数的简化处理会引起很大误差。
A mathematical model of the heat transfer process of regenerative cooling passage in thrust chamber of liquid rocket engine laminates is proposed. The general form control equation is used to deal with the heat transfer problem of the turbulent flow of the coolant and the thermal conductivity of the channel material. The LVEL turbulence model is used to calculate the thermal physical parameter of the coolant (hydrogen) with the change of temperature and pressure, Material thermal properties with temperature changes. The results show that the channel design with large aspect ratio and small wall thickness can significantly improve the regenerative cooling capacity and reduce the wall temperature and temperature difference. A simplified process using convective heat transfer coefficients and thermophysical constants can cause significant errors.