摘要
采用贴体坐标系和ＳＩＭＰＬＥ法，对固体发动机在旋转热试车条件下的燃烧室内流场进行了数值模拟。不同燃烧时刻的计算结果表明： 旋转对固体发动机燃烧室燃气流动结构的影响随着燃烧肉厚的退移而显著增强； 在发动机药柱的前翼燃烧消失后， 前封头开口区域的切向涡开始变得强烈； 切向涡的分布呈现Ｒａｎｋｉｎｅ 涡的特点， 在发动机前开口区域涡的固核半径极小， 旋转速度极大， 这将严重影响该区域的热防护， 应引起有关设计人员的高度重视。
Body fitted grid system and SIMPLE method were adopted to numerically simulate chamber internal flow field of solid propellant rocket motor under spinning static firing test condition.The calculated results of every different time show that the effects of spinning on internal flow field of chamber become remarkable along with the regress of burning propellant web. The tangential vortex in the forward opening begins get strong after the forward fins of grain burned out. The distribution of tangential vortex possesses the features of Rankine, but the radius of vortex nucleus in the forward opening is very small, spinning rate of vortex nucleus is very high,these will seriously affect the thermal protection
出处
《推进技术》
EI
CAS
CSCD
北大核心
1999年第6期23-27,共5页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
旋转
湍流
仿真
燃烧室
Solid propellant rocket engine,Spinning solid upper stage,Combustion product,Turbulence model,Numerical simulation
