摘要
为了解塞式喷管发动机在不同压比下工作时的再生冷却换热特性,对一试验用塞式喷管发动机建立三维计算模型,采用数值模拟的方法,得到了不同压比下再生冷却塞锥壁面以及内部截面的压强、热流密度和温度的分布曲线和云图.计算过程中采用一阶迎风格式离散控制方程.计算结果表明塞式喷管发动机在较低压比的工况下工作时,塞锥受热状况较为恶劣,塞锥壁面出现压强和温度的峰值,该截面内部的温度和温度梯度达到最大.
To understand different heat transfer characteristics of regenerative cooling in plug nozzle in different operation conditions, computational model of three dimension plug nozzle was established and numerical simulation was employed. Pressure, heat flux and temperature contour in different operation conditions were obtained. Governing equations were discretized with one order upstream scheme. The results show： at lower pressure ratio, heat transfer condition on the plug surface is the worst, peak values of pressure and temperature appear along the wall of plug nozzle, temperature and temperature gradient along the section of wall reach the highest.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2007年第4期632-638,共7页
Journal of Aerospace Power
基金
国家"863"基金资助项目(863-2-1-3-1)
关键词
航空
航天推进系统
液体推进剂火箭发动机
塞式喷管
再生冷却
数值模拟
aerospace propulsion system
liquid propellant rocket engines
plug-nozzle
regenerative cooling
numerical simulation
