进气角度和初始粒径对发射筒内流动特性的影响  

Impact of injection angle and initial particles diameter on interior flow characteristic of silo

作　　者：白俊华[1] 胡馨博[1] 

机构地区：[1]西北工业大学,西安710072

出　　处：《固体火箭技术》2013年第2期165-169,共5页Journal of Solid Rocket Technology

基　　金：国家自然科学基金资助项目(50976095)

摘　　要：根据导弹发射的实际工作过程,建立了燃气-蒸汽式发射动力系统的计算模型,利用CFD技术对燃气遇冷却水掺混后的入筒工作过程进行了数值模拟,针对输气管进气角度、冷却器一次雾化粒径等发射系统内流场特性的影响因素进行了分析研究,并对不同输气管角度下的喷管受力情况进行了分析总结。结果表明,不同时刻下发射筒内气体流动流形变化较大;随着输气管角度的减小,发射筒内流动的混乱度增加;在所计算工况中,输气管进气角度与发射筒轴线的夹角为70°时喷管壁面受到的最大压力差最小,随着时间的增加,喷管最大压力差呈减小趋势;较小的初始雾化粒径有利于减少冷却水在筒内的滞留量,降低发射筒的工作温度,使发射过程中燃气能量更为可控。Based on the working course of gas-steam launch system, the computational model was built, and the numerical simulations were conducted for the mixture of gas and cooling water into silo. Some factors, including gas injection angle and initial particle diameter were analyzed. The stress on the nozzle at different gas injection angle was summarized. The results indicate that the flow shape varies greatly at different times;and the trouble increases with the injection angle decreasing;the nozzle suffers the least max. pressure when the injection angle is 70° to the axis of the silo;and the max. pressure of nozzle reduces by the time increasing; the smaller initial diameter can reduce the rest time of particles in the silo,improve the vaporizing rate of the cooling water and de- crease the temperature of the silo, making the gas energy controllable.

关 键 词：燃气-蒸汽式发射动力系统 输气管进气角度 初始粒径 流动特性 喷管受力 

分 类 号：V553[航空宇航科学与技术—人机与环境工程]