中文摘要：

以采用再生冷却的液氧煤油火箭发动机的相关参数为依据,考虑温度和压力对冷却剂物性的影响、冷却通道内液态冷却剂流动的压力损失和冷却剂在两相区与单相区的传热差别,利用Fortran编程软件调用Nist Refprop数据库的流体物性,对以水为第三流体的第三流体冷却循环进行传热计算,得出冷却通道入口压力在2～SMPa内各个压力下水的流量范围,并且入口压力越高,水流量越小,而在各入口压力和冷却剂流量下火箭发动机壁温和热流密度不仅在喷管喉部出现峰值,在两相区内也会出现峰值.通过对涡轮泵和冷凝器的质量分析以及循环的效率分析,得出循环在最高效率时,冷却通道入口压力最小,冷却剂流量最大;循环的总质量和冷凝器的质量最小时,冷却通道入口压力最大,冷却剂流量最小;第三流体泵的质量最小时,冷却通道入口压力和冷却剂流量最小.

英文摘要：

Considering the influence of temperature and pressure on coolant physical properties,flow pressure loss of liquid coolant in cooling channel and heat transfer difference of coolant between single phase region and two phase region,heat transfer calculations of third fluid cooled cycle which took water as third fluid was conducted with Fortran to call the coolant physical properties in Nist Refprop database based on the relative parameters of liquid oxygen kerosene rocket engine with regenerative cooling.Water flow ranges at different pressures were obtained when the inlet pressure of cooling channel changed from 2MPa to 8MPa.The larger the pressure,the smaller the water flow.Wall temperatures and thermal fluxs of rocket engine at different coolant flows and inlet pressures showed peak values both in the nozzle throat and the two phase region.Quality analysis of turbo pump and condenser and cycle efficiency analysis indicated that the highest cycle efficiency appeared at the smallest inlet pressure and largest coolant flow,the smallest quality of cycle and condenser appeared at the largest inlet pressure and smallest coolant flow,and the smallest quality of third fluid pump appeared at the smallest inlet pressure and coolant flow.