摘要
为了研究水环境下发动机喷管流动分离现象以及影响因素和规律,基于VOF多相流模型和SST k ω湍流模型,建立了水环境下固体火箭发动机喷流流场数值仿真模型,并进行了不同喷管扩张比和NPR(燃烧室总压与环境压强之比)下的喷流流场数值模拟。通过数值仿真分析获得了水环境下喷管内发生流动分离时推力、压力特征和流场非定常变化特征,水环境下喷管内流动分离具有强烈的非定常振荡特征,分离激波会在分离点与发动机喷管出口之间呈现推进 返回 推进周期性振荡的流动特征。同时,获得了喷管扩张比和NPR对流动分离特征的影响规律,相同水深环境下不同扩张比喷管对流动分离点位置影响较小;NPR越小,流动分离点的位置处喷管扩张比越小。
Based on the VOF multiphase model,SST k-ωturbulence model and dynamic-mesh method,a simulation model for the solid rocket motor ignition has been established to investigate the unsteady characteristics and the influencing laws of flow separation under water environment.The results show that flow separation is unsteady and the shock waves propulsion-return-propulsion oscillated periodically between the separation locations,corresponding to the smallest expanded ratio of the throat and exit of nozzle.The simulation result of characteristics of the jet flow of the motor in different expanded ratio and NPR were analyzed.It shows that at the same water depth,the expansion ratio of nozzles has little effect on the location of flow separation points.The smaller NPR is,the lower the nozzle expansion ratio is at the flow separation point.
作者
权晓波
王占莹
刘元清
孟元军
QUAN Xiaobo;WANG Zhanying;LIU Yuanqing;MENG Yuanjun(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2020年第1期8-15,共8页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
水环境
流动分离
数值仿真
solid rocket motor
water environment
flow separation
numerical simulation
