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

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