关键词: 传热;液氧;液体推进剂火箭发动机;传热系数;计算

Abstract: Heat transfer performance of liquid oxygen under conditions of critical temperature and supercritical pressure has been studied experimentally by means of electrical heating. The adaptability of criterion equations commonly used at home for calculating the heat transfer performance of L.O.was also examined. The study results show as follows.1. The subcritical,non-isothermal,turbulent heat transfer equation is not suitable for supercritical situation, except for wall temperature TW<200K. and L.O. temperature T1<140K.2. The considerable error would happen when universal heat transfer equation for critical temperature region (relation by Schmzmann, M.) is used for ca-lculating the heat transfer coefficient of L.O.in the vicinity of critical tempera-ture and gas oxygen at low temperature. The calculation conducted with the new criterion relation presented in this paper Nuf = 0.0266Ref0.8Prm0.8(Tw/T1 )-1 is conformed with ihe experimental data very well.3. The popular equation for gas heat exchange can be used for hight-tem-perature gas oxygen under condition of supercritical pressure.

Key words: Heat transfer;Liquid oxygen;Liquid propellant rocket engine;Heat transfer coeff icient;Computation