柔性喷管SRM三维两相内流场数值模拟
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摘要
针对柔性喷管固体火箭发动机的复杂多相流数值计算问题,基于Euler-Lagrange方法,应用k-ωSST湍流模型和颗粒轨道模型,建立了气固两相三维内流场计算模型。分析了发动机内部压强和温度场、燃气和粒子速度场、固相粒子沉积浓度和颗粒运动轨迹;重点分析了喷管无摆动和摆动5°状态下的发动机内流场变化特性。研究表明:2种工况下的燃烧室平均压强、温度场及喷管出口速度变化幅度较小,但对喷管柔性连接缝内的流场速度影响较大,固相粒子最大沉积率产生于发动机后封头的绝热层内壁;喷管无摆动时,柔性连接缝内的粒子沉积率较低,随着喷管摆动幅度增加,粒子沉积浓度大幅度升高。
According to the problems of complicated multi-phase flow fields of the flexible-nozzle solid rocket motor( SRM),the 3 D two-phase numerical model was established based on the method of EulerLagrange.The k-ω SST( shear-stress-transport) turbulence model and the particle orbital model( PTM)were used for simulation.The pressure and temperature fields,gas and particle velocity fields,particle deposition concentration and trajectory were analyzed. The SRM internal-flow-field variation-characteristics under the conditions of nozzle without swing and swinging 5° were compared. The results show that the change of average pressure and temperature of the combustion chamber,the velocity at the exit of nozzle is very little,but the velocity of flexible joint is different. The maximum deposition rate of the particles appears on the inner wall of the insulating layer in the SRM rear head.In the case of no swing,the particle deposition rate is less in the flexible joint,and as the nozzle swings increases,the deposition concentration of particle increases obviously.
According to the problems of complicated multi-phase flow fields of the flexible-nozzle solid rocket motor( SRM),the 3 D two-phase numerical model was established based on the method of EulerLagrange.The k-ω SST( shear-stress-transport) turbulence model and the particle orbital model( PTM)were used for simulation.The pressure and temperature fields,gas and particle velocity fields,particle deposition concentration and trajectory were analyzed. The SRM internal-flow-field variation-characteristics under the conditions of nozzle without swing and swinging 5° were compared. The results show that the change of average pressure and temperature of the combustion chamber,the velocity at the exit of nozzle is very little,but the velocity of flexible joint is different. The maximum deposition rate of the particles appears on the inner wall of the insulating layer in the SRM rear head.In the case of no swing,the particle deposition rate is less in the flexible joint,and as the nozzle swings increases,the deposition concentration of particle increases obviously.
引文
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[3]牛青林,傅德彬,李霞.不同飞行状态下固体火箭发动机尾喷焰数值研究[J].航空动力学报,2015,30(7):1 745-1 751.NIU Qing-lin,FU De-bin,LI Xia.Numerical study on the plumes of solid rocket motor under various flight conditions[J].Journal of Aerospace Power,2015,30(7):1 745-1 751.(in Chinese)
[4]DUNLAP R,BLACKNER A M,WAUGH R C,et al.Internal flow field studies in a simulated cylindrical port rocket chamber[J].Journal of Propulsion and Power,1990,6(6):690-704.
[5]李映坤,韩珺礼,陈雄,等.基于SST湍流模型的模拟SRM内流场数值仿真[J].固体火箭技术,2014,37(5):616-621.LI Ying-kung,HAN Jun-li,CHEN Xiong,et al.Numerical simulation of model SRM inner flow field based on SST turbulence model[J].Journal of Solid Rocket Technology,2014,37(5):616-621.(in Chinese)
[6]张磊,王浩,阮文俊,等.超声速燃气射流流场特性的三维数值模拟[J].弹道学报,2015,27(2):80-84.ZHANG Lei,WANG Hao,RUAN Wen-jun,et al.Three-dimensional numerical simulation flow characteristics of supersonic gas jet[J].Journal of Ballistics,2015,27(2):80-84.(in Chinese)
[7]李峥,向红军,张小英.复合推进剂固体火箭发动机喷流流场数值模拟[J].固体火箭技术,2014,37(1):37-42.LI Zheng,XIANG Hong-jun,ZHANG Xiao-ying.Numerical simulation of composite solid propellant rocket motor exhaust plume[J].Journal of Solid Rocket Technology,2014,37(1)37-42.(in Chinese)
[8]金秉宁,刘佩进,杜小坤,等.复合推进剂中铝粉粒度对分布燃烧响应和粒子阻尼特性影响[J].推进技术,2014,35(12):1 701-1 706.JIN Bing-ning,LIU Pei-jin,DU Xiao-kun,et al.Propellant on distributed combustion response and particle damping[J].Journal of Propulsion Technology,2014,35(12):1 701-1 706.(in Chinese)
[9]杨育文,邓康清,余小波,等,高含铝推进剂低压固体火箭发动机尾流场复燃数值模拟与实验研究[J].推进技术,2017,38(3):680-686.YANG Yu-wen,DENG Kang-qing,YU Xiao-bo,et al.Numerical simulation and experimental investigation on plume afterburning of low-pressure solid rocket motor with highly aluminized propellant[J].Journal of Propulsion Technology,2017,38(3):680-686.(in Chinese)
[10]MINE Y.Analysis and design optimization of solid rocket motors in viscous flows[J].Computers&Fluids,2013,75:22-34.
[11]傅德彬.数值仿真及其在航天发射技术中的应用[M].北京:国防工业出版社,2011.