摘要
以不可压ＮＳ方程为基础，在旋转相对坐标系中，采用贴体坐标和ＳＩＭＰＬＥ法，对给定结构的旋转固体火箭发动机燃烧室试车中气固两相湍流流动进行了数值模拟。不同时刻燃烧情况的计算结果表明：旋转对固体火箭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，前封头开口区域的气固两相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，旋转角速度极大，将会影响该区域的热防护，这也是导致固体火箭发动机地面旋转热试车前开口烧穿的重要原因之一。
Based on incompressible N S equations,spinning relative coordinate,body fitted grid system and SIMPLE method,internal gas particle turbulent flows in the combustion chamber of solid rocket motor under spinning static firing test condition are simulated numerically.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 gas particle vortex in the forward opening begins to get strong after the forward fins of grain are burned out.The distribution of tangential vortex possesses the features of Rankine,the nucleus radius in the forward opening is very small with very high nucleus spinning rate .The strong gas particle vortex seriously affects the thermal protection which would result in burn through of the forward opening of solid rocket motor under spinning static firing test.
出处
《固体火箭技术》
EI
CAS
CSCD
1999年第3期6-10,共5页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
旋转流
湍流
数值模拟
燃烧室
solid propellant rocket engine
rotating fluid
turbulent flow
numerical simulation
