摘要
针对双脉冲发动机第一脉冲燃烧室内绝热层出现局部烧蚀加重现象,对203 mm和120 mm的2种双脉冲发动机内流场特性进行了仿真,分析了面积突扩在其燃烧室内形成的燃气漩涡流动及相关两相流特性,并通过经验公式计算了燃烧室对流换热分布。通过对比计算结果与实验现象,发现壁面烧蚀加重区域与燃气漩涡区位置基本重合;燃气漩涡区内的对流换热系数明显高于燃烧室其他部位,特别是再附着点附近,是造成该区域烧蚀加重的主要因素。此外在推进剂含金属添加剂时,少量较小尺寸的凝相粒子会被卷入燃气回流区,向上游壁面运动,并可能产生沉积。
Aimed at the local ablation enhancement problem in the 1st pulse combustion chamber of a dual-pulse motor,numerical simulation of the two-phase inner flow in two dual-pulse motors with 203 mm and 120 mm in caliber respectively was conducted.The vortex movement of gas in the combustion chamber and its two-phase characteristics were analyzed,which were induced by the chamber area sudden expansion.The heat convection intension on the chamber wall was computed by an expirical formula.By comparing the calculation results with the experinental data,it was revealed that the convection enhancement zone was consistent with the local ablation spot well.The chamber wall heat convection in the gas vortex region,especially near the reattachment point,was much higher than in the other chamber wall regions,which caused the local ablation enhancement.In addition,when the propulsion grain had metal involved,a portion of metal-oxide particles in smaller size were carried into the vortex zone and moved to the upstream chamber wall.Those particles may deposit on the chamber wall.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第4期453-456,共4页
Journal of Solid Rocket Technology
关键词
双脉冲固体发动机
燃烧室
内流场
烧蚀
dual-pulse solid rocket motor
combustion chamber
internal flow field
ablation
作者简介
刘亚冰（1983-），男，博士生，研究领域为航空宇航推进论与工程。E-mail：lyb718@163．com
