复燃对氢氧火箭发动机尾焰流场及辐射特性影响数值研究

Numerical Research on Influence Exerted by Afterburning on Flow Field and Radiation Characteristics of LH2/LOX Rocket Engine

为深入研究复燃对氢氧火箭发动机尾焰流场及辐射特性的影响,以氢氧发动机喉部截面参数为入口条件,采用耦合Realizable k-ε湍流模型的三维N-S方程,考虑尾焰复燃反应影响,利用PISO算法求解得到尾焰流场参数。在此基础上,通过气体辐射传输方程和大气透过率计算模型SLG对尾焰辐射特性进行计算,对比复燃反应对尾焰流场及其辐射特性的影响。结果表明,复燃反应对氢氧发动机尾焰流场计算影响较大,使温度场以及燃烧产物的质量分数大幅增加,从而导致尾焰的辐射特性增强,因而在氢氧发动机尾焰流场和辐射计算中,考虑复燃反应是极为必要的。

To have a deep understanding of the influence exerted by afterburning on the flow field and radiation characteristics of LH2/LOX rocket engine plume, parameters at the throat section of the engine are set as the inlet condition to consider the afterburning reaction. The N-S equation coupled with Realizable k-ε model is used as well. Plume flow field parameters are obtained through PISO algorithm. On this basis, plume radiation characteristics are calculated with gas radiation transmission equation and SLG model. The influence of afterburning reaction on the plume flow field and radiation characteristics are compared as well. The results indicate that the afterburning reaction exerts a significant effect on plume flow field calculation, making the mass fraction of combustion products go up greatly, which enhances plume＇s radiation characteristics. In conclusion, it is necessary to take account afterburning reaction in plume flow field and radiation calculations.