流量突变条件下煤油流动与对流传热特性实验

对流量突变条件下RP-3航空煤油的圆管流动与传热过程进行了实验研究。燃料流动与传热实验是在超临界压力为3MPa、燃料温度为300～650K、雷诺数为3000～60000范围内进行的。实验同步测量了圆管煤油温度、壁温、油压的沿程分布，并应用基于动量与能量守恒的非定常控制体分析方法，获得了航空煤油壁面摩阻系数与传热努塞尔数的分布。实验结果表明:当煤油温度未超过临界值（约650K）、处于过压液态时，该实验条件下的入口流量的突增或者突减过程对摩阻系数与努塞尔数的影响很小。 

Experiment on flow and heat transfer of aviation kerosene with time variation of inlet mass flow rate

Characteristics of turbulent flow and heat transfer of compressed liquid kerosene were studied experimentally with sudden changes of the inlet mass flow rate. Flow and heat transfer experiments were conducted at a fuel temperature range of 300-650K, a Reynolds number range of 3000-60000 and a supercritical pressure of 3MPa. The fuel temperature, pressure and mass flow rate, and tube outside wall temperature were measured. Fuel skin friction coefficient and Nusselt number were calculated through unsteady control volume analysis based on momentum and energy conservations. The present results show that the time change of mass flow rate has very little effect on the skin friction coefficient and Nusselt number for compressed liquid kerosene tube flow when the temperature of kerosene doesnt exceed critical value 650K.