摘要
采用贴体坐标和ＳＩＭＰＬＥ法，对某一大型固体发动机在旋转条件下的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内流场结构的影响随着燃烧肉厚的退移而显著增强；前封头开口区域存在着强烈的切向涡，将严重影响该区域的热防护。
Body fitted grid system and SIMPLE method are adopted to numerically simulate chamber internal flowfield of a large solid motor under spinning condition. The calculated results at various time show that the effect of rotation on internal flowfield of chamber becomes remarkable along with the regression of burning propellant web; there exits a strong tangential vortex in forward openning, which will have serious effect on thermal protection.
出处
《固体火箭技术》
EI
CAS
CSCD
1999年第2期8-11,27,共5页
Journal of Solid Rocket Technology
关键词
火箭发动机
旋转流场
流场模拟
燃烧室
solid propellant rocket engine
gyration
flow field
flow field simulation
