摘要
针对氢氧火箭发动机地面水平试车时尾流燃气对地面热防护的影响,分别采用二维轴对称模型和三维模型对发动机尾流流场进行了数值模拟。计算中,采用氢氧单步燃烧反应模型考虑尾流燃气与空气的燃烧,湍流模型选用了标准k-ε模型。仿真结果表明:三维模型中,燃气逐渐向地面流动,地面燃气温度高于二维轴对称模型中的燃气温度;发动机工况变化时,三维模型和二维轴对称模型中的地面燃气温度变化趋势相反,采用三维模型计算具有更好的可信度。
Aiming-at the influence of wake flow gas of the oxyhydrogen rocket engine on the ground protective devices in the horizontal ground test, the numerical simulation of engine wake flow field was conducted with 2-dimenstional axis symmetrical model and 3-dimensional model. In the calculation, the single step H-O combustion reaction model was used for the reactions between the wake flow gas and air, and the standard k-e turbulence model was selected. The simulation results show that when the 3-dimensional model was adopted, the fired gas flows to the ground where the gas temperature was higher than that of 2-dimenstional axis symmetrical model; as the working condition of the engine was changed, the variable trend of the gas temperature on the ground as for the 2-dimen- sional axis symmetrical model was opposite to that as for 3-dimension model. Therefore, the reliability of 3-dimentional is higher than 2-dimensional axis symmetrical model.
出处
《火箭推进》
CAS
2012年第6期29-34,共6页
Journal of Rocket Propulsion
基金
国家863项目(2008AA702303)
关键词
液体火箭发动机
地面水平试验
燃烧反应模型
燃气温度
热流密度
liquid rocket engine
horizontal ground test
combustion reaction model
gas temperature
heat-flow density
