缩比推力室甲烷传热试验研究

Experimental study on methane heat transfer test system

为了研究火箭发动机推力室冷却通道内的甲烷传热和流阻特性,研制了缩比推力室甲烷传热试验系统,并以推力室挤压热试验的形式进行了5次超临界甲烷传热试验和2次亚临界甲烷传热试验研究.超临界甲烷传热试验燃烧室压力为5.5～7.5 MPa,燃烧室氢氧混合比约为6.8,甲烷温度为128～230 K,甲烷冷却剂流量为5～7 kg/s,甲烷冷却剂入口压力为8.3～11.7 MPa.亚临界甲烷传热试验的室压约为4 MPa,氢氧混合比2.8,甲烷温度为：128～189 K,甲烷冷却剂流量约为2.9 kg/s,甲烷入口压力为3～3.5 MPa.通过试验研究获得了液态甲烷在推力室冷却通道内超临界压力状态和亚临界压力状态下的传热和流阻特性.

A methane heat transfer test system was built to investigate the methane heat transfer and flow resistance characters in the coolant channel of thrust chamber in liquid rocket engine. Five supercritical hot fire tests and two subcritical hot fire tests for methane heat transfer study were per- formed in trust chamber extrusion heat test. The conditions of supercritical methane heat transfer tests are combustion chamber pressure of 5.5-7.5 MPa, O/H mixture ratio of about 6.8, methane tempera- ture of 128-230 K, methane coolant mass flow of 5-7 kg/s, methane coolant inlet pressure of 8.3-11.7 MPa. The conditions of subcritical methane heat transfer tests are combustion chamber pres- sure of about 4 MPa, O/H mixture ratio of about 2.8, methane temperature of 128M89 K, methane coolant mass flow of about 2.9 kg/s, coolant inlet pressure of 3-3.5 MPa. The heat transfer and flow resistance characters of liquid methane in trust chamber cooling channels were obtained in supercriti- cal and subcritical pressure states by experimental study.