Abstract: The effort of spray characteristic on rocket engine combustion stability for hypergolic propellant (MMH/NTO) was studied A physical model for spray droplet diameter effecting evaporation rate was developed Fuel vaporization determined the decomposition rates of bipropellant gas phase of MMH And the time lag of evaporation and decomposition was utilized to analyze the combustion instability Application of Computational Fluid Dynamics(CFD) techniques to stability testing,pressure pulse gun methodology was modeled numerically Spray characteristic as driving mechanism for combustion instability was studied The sensitivity to fluctuations was also determined The limiting map of combustion stability was given

Key words: Liquid propellent rocket engine;Liquid inject;Drop;Evaporation;Cmbustion stability;Numerical simulating

摘要： 用数值方法研究了一甲基肼 /四氧化二氮自燃推进剂 (MMH/ NTO)喷雾液滴直径对火箭发动机燃烧稳定性的影响。从喷雾特性对蒸发速率的影响规律出发 ,发展了喷雾液滴大小影响蒸发速率的物理模型。以蒸发作为燃烧速率控制过程 ,由 MMH的分解蒸发速率来控制。用蒸发和分解的时滞分析了燃烧不稳定性 ,应用 CFD技术发展了评定燃烧稳定性的脉冲枪模型 ,得到了对燃烧振荡的敏感分析 ,并给出了燃烧稳定性的极限图

关键词: 液体推进剂火箭发动机;液体喷射;液滴;蒸发;燃烧稳定性;数值仿真