摘要
通过理论结合数值仿真的方法考虑背压对液体火箭发动机用液体离心喷嘴喷雾锥的影响。在理论模型的基础上,使用旋转轴对称模型对离心喷嘴内外流场求解耦合VOF方程的N-S方程组的数值模拟表明:背压增加,喷雾锥内外压差使喷雾锥向内收缩。基于流场参数分析,建立内外压差的经验公式,得到了与实验吻合的考虑背压影响的喷雾锥模型。
The effects of backpressure on spraying cone of liquid swirl injector using in liquid rocket engine were studied by combining theory with numerical simulation.Based on theoretical analysis,numerical simulations were carried out by using a swirl axi-symmetric model to solve N-S equations coupled with VOF equation for interior and exterior flow field of a swirl injector.It shows that the increasing pressure differentce between internal and external surface of spraying cone caused contraction.An empirical equation of pressure differentce was obtained with analysis for numerical results.A theoretical model of spray pattern was established and showed good agreement with existing experimental data.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2010年第5期539-543,共5页
Journal of Propulsion Technology
基金
国家建设高水平大学公派留学项目提供的资金支持
关键词
液体离心喷嘴
背压
喷雾锥形状
喷雾锥角
理论模型
Liquid swirl injector
Backpressure
Spray pattern
Spray angle
Theoretical model
