Abstract: The physical model and mathematical control equations of heat transfer for parallel four thrust chambers with all-radiation cooling were presented Heat transfer characteristics connecting with this arrangment were analyzed The result shows that the circumferential temperature change caused by the radiation between chambers is mostly decided by the dimensionless distance L/D and the single engine wall temperature T 0 The location that maximal circumferential temperature appears varies from the direction angle Ψ =0° at throat to Ψ =±45° at nozzle exit and accordingly the temperature distribution varies from single peak to two peaks In addition,the analysis of the system with only one pair of operating thrust chambers was performed The simulation test on the ground validated the numerical analysis

Key words: Liquid propellant rocket engines;Rocket engine cluster;Thermal radiation;Temperature distribution;Numerical analysis

摘要： 提出了四台对角布置全辐射冷却推力室外向辐射传热的物理模型和数学方程 ,分析此布置形式推力室的热特点。计算表明 ,因推力室之间辐射传热而引起的周向温度畸变 ,主要取决于推力室间的相对间距L/D和单机壁温水平T0 ;周向温度峰值出现位置从喉部的Ψ =0°附近渐变到喷口的Ψ =± 45°处 ,周向壁温分布亦相应地从单峰形态渐变成双峰形态。对仅有两对角推力室工作、另一对推力室不工作时的温度分布特点也作了分析。地面模拟实验证明数值分析结果是正确的

关键词: 液体推进剂火箭发动机;并联火箭发动机;热幅射;温度分布;数值分析