固体发动机燃烧室离散相颗粒相变对喉衬烧蚀的影响_高波.pdfVIP

32 4 Journal of Solid Rocket Technology Vo.l 32 No. 4 2009 (, 7 0025) : 针对喉衬烧蚀试验中高燃温推进剂对喉衬烧蚀较普通推进剂偏小的现象, 采用 Eu ler-Lagrangian方法, 对燃烧室 内离散 颗粒的传热和 变过程进行数值分析, 对烧蚀偏小现象给出了理论解释分析结果表明, 在发动机燃烧室内的高 温环境( 4 000 K) 下, 约有离散项总质量 40% 左右的颗粒发生 变成为气体, 大部分离散 颗粒从喷管逃逸; 离散项颗粒的 变, 一方面会减弱对喉衬的烧蚀, 另一方面会造成燃烧室内温度等参数分布的不均匀 : 固体火箭发动机; 喉衬; 烧蚀; 两 流; 离散 颗粒; 变; 数值模拟 : V435 : A : 006-2793( 2009) 04-0379-04 Influence of phase change of dispersed-phase particle in SRM cham ber on throat in sert erosion GAO Bo ( The Fourth Academ y of CASC, X ian 7 0025, China) A bstrac t: For analyzing less erosion loss phenom ena of throat insert in an erosion test m otor w ith the h igh energy propellant compared w ith that of norm alHTPB propellant, the heat transfer and phase change of d ispersed-phase particles in the chamberw ere smi u lated by m eans of Eu ler-Lagrangian m ethod, and a theoretical explanation was given. The resu lts show that about 40% of the d ispersed-phase particles at high tem perature ( 4 000 K) evaporate, and most of particles are exhausted from the nozzle; The phase change of d ispersed-phase particles can m ake not only the erosion of throat insert reduced, bu t param eters of the cham ber such as tem perature non-uniform ly distributed. K ey w ords: solid rocket m otor; throat insert; eros ion; tw o-phase flow; d ispersed-phase particle; phase change; num erical smi u lation 1 , , , 4 000 K, , , 2 3 ( , 8. 5% ) , , p-t, , , , , , , , 0.