火箭发动机推力室粘性流场数值模拟及实验

Numerical Simulation and Experimental Study of Viscous Flow Field in Rocket Engine propulsion

用时间相关法的显式格式,结合k-ε方程湍流模型求解氢氧火箭发动机燃烧室中的粘性化学反应流动,化学反应采用9种组分,5个主要反应的有限速率的化学反应模型,得到了流动参数与组分的质量分数在燃烧室中的分布情况.其结果同理论分析的结果相一致,对火箭发动机燃烧室的压力和推力室的推力在启动段、关机段进行了计算机数值仿真,并与该火箭发动机热试车参数进行了比较,仿真的结果与火箭发动机热试车试验结果非常一致,验证了仿真模型的正确性和运用数值模拟方法取代部分实际热试车试验的可行性及可信性.

The reacting viscous flow field in 02/H2rocket motor combustor was computed by using time-dependent explicit scheme, and the two-equation k - ε turbulent model was also used in the procedure. The combustion process was modeled by 9-specice and 8-step finite-rate chemical model. The distribution of flow parameters and mass fractions of the products were presented in accordant with the theoretial analysis. The pressure of the rocket motor combustor and propulsion of the propeller chamber in the staring, stable crating and stopping sections are simulated and numerically analyzed under the condition with certain mixing ratio of the reactor. The result is in good accord with that of the practical testing. Accordingly, it is feasible and dependable for the numerical simulation method substitute patial test.