火箭推进2011，Vol.37Issue(6)：20-25,6.
湍流、喷雾模型对氢氧火箭发动机燃烧仿真的影响
Effects of turbulent and spray models on combustion process simultion of LOX/GH2 rocket engine
摘要
Abstract
Based on the improved PISO algorithm, the numerical simulation for the combustion instability of a LOX/GH2 rocket engine was conducted by changing the turbulent and spay models of κ-ε equations. The compared results of the theoretical analysis and numerical simulation show that in the two-dimensional situation, both droplet collision model and TAB droplet breakup model are not suitable for the numerical simulation of LOX/GH2 combustion instability; the pressure oscillation in the combustion chamber can be simulated by combining the TVB droplet breakup model with the turbulent models of κ-ε equations, but the oscillation frequency can not be simulated; if the turbulent models of Realizable κ-ε equations are adopted without consideration of the droplet spray models, both the pressure oscillation in the combustion chamber and the distribution of the oscillation frequency can be simulated.关键词
氢氧火箭发动机/不稳定燃烧/数值仿真Key words
LOX/GH2 rocket engine/combustion instability/numerical simulation分类
航空航天引用本文复制引用
程钰锋,聂万胜,丰松江..湍流、喷雾模型对氢氧火箭发动机燃烧仿真的影响[J].火箭推进,2011,37(6):20-25,6.基金项目
国家自然科学基金 （）
