摘要
考虑冷却剂入口模型及气壁镀镍,对液体火箭发动机推力室再生冷却通道和冷却剂进行三维流动与传热耦合计算.采用经验公式计算燃气侧对流及辐射换热,冷却剂为甲烷,考虑其物性随温度和压力的变化.所得结果表明:冷却剂入口二次流及突扩流场的叠加,使局部压力损失变大,影响进口下游较大区域流动传热状况;气壁镀镍能提高气壁的耐高温性,降低气壁锆铜的温度.
Three-dimensional numerical simulation was carried out for coupled flow and heat transfer of regenerative cooling channel and coolant in consideration of the cooling channel inflow and hot-gas wall nickelage.The empirical method was used to simulate hot-gas convective and radiative heat transfer;the coolant was methane,whose thermophysical properties varied with both temperature and pressure.The results show that,the secondary flow plus sudden expansion flow field at inflow could lead to increase of local pressure lose and affect the flow and heat transfer situation at a large downstream region;nickelage on hot-gas wall can improve its capacity to endure high temperature and reduce the copper-alloy temperature.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第12期2834-2838,共5页
Journal of Aerospace Power
关键词
再生冷却
冷却剂入口
镀镍
流动
换热
数值模拟
regenerative cooling
channel inflow
nickelage
fluid flow
heat transfer
numerical simulation
