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针对固液混合火箭发动机典型的边界层燃烧理论,用边界层的方法对固液混合火箭发动机燃烧进行了计算,计算采用二维轴对称的层流边界层方程,化学模型采用有限速率模型。计算考虑了不同氧化剂流率,不同吹入参数的多种情况,得到了固体混合发动机边界层的温度场分布,并利用计算结果,拟合了固体燃料的燃速公式,与相关文献的比较说明计算正确,结果符合燃烧机理和流动规律,为进一步研究固液混合火箭发动机的燃烧问题打下了基础。
Aiming at the typical boundary layer combustion theory of solid-liquid hybrid rocket motor, the combustion of solid-liquid hybrid rocket motor is calculated by boundary layer method. The two-dimensional axisymmetric laminar boundary layer equation is calculated, and the chemical model uses a finite rate model. The temperature distribution in the boundary layer of the solid hybrid engine was obtained by considering various conditions of different flow rates of oxidant and parameters of different blowing parameters. The calculation results were used to fit the formula of combustion rate of solid fuel, which was compared with the related literatures The calculation is correct, the result accords with combustion mechanism and flow law, which lays the foundation for further research on the combustion problem of solid-liquid hybrid rocket engine.