用湍流附面层方程计算喷管内的对流换热

THE CALCULATION OF CONVECTIVE HEAT EXCHANGE IN NOZZLE WITH TURBUIENT BOUNDER LAYER EQUATIONS

关键词:  火箭发动机喷管  紊流  边界层方程  对流传热

Key words:  Rocket nozzle  Turbulent flow  Boundary layer equation  Convection heat transfer

摘要:

在流场计算的基础上,运用Patankar-Spalding方法积分求解了湍流附面层控制方程组,从而得到了固体火箭发动机喷管内燃气与壁面之间的对流换热。其中在附面层靠近壁面的底层区使用了Gouette流分析,在壁面边界和自由流边界处引入了滑移值的概念,因此保证了计算结果的相对准确性。最后将本文的计算结果与巴兹公式的计算结果和实验结果进行了比较。

Abstract:

on the basis of flowfield calculation, the Coupled control equations of turbulent boundany layer can be solved by using Patankar-Spalding integral-melhod with six-point scheme to obtain the heat exchange between the hot gas and nozzle wall. Couette flow analysis is to applied to the near wall region, and the slip value conception is applied the wall boundary and free boundary.Thus the relative accuracy of the calculation results is ensured. At last, the calculation results of this paper arc compared with the experimental data and the calculation results of Bartz formula.