固体火箭超燃冲压发动机燃气喷射燃烧数值仿真研究  

Numerical research on gas injection combustion of solid rocket scramjet

作　　者：陈永志 石保禄 赵马杰 李鹏昌 冯滢 CHEN Yongzhi;SHI Baolu;ZHAO Majie;LI Pengchang;FENG Ying(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《航空动力学报》2024年第11期465-474,共10页Journal of Aerospace Power

摘　　要：针对固体火箭超燃冲压发动机燃烧室内燃料滞留时间短、与空气来流掺混困难,火焰稳定性差,颗粒燃烧效率低等问题。基于欧拉-拉格朗日方法建立了两相流动燃烧数值模拟方法,利用最小自由能法及能量、质量守恒定律进行一次燃气简化。基于某型带凹腔火焰稳定装置的固体火箭超燃冲压发动机模型,探究了不同燃气喷射角度、不同燃气喷射位置对发动机温升效率、总压恢复系数、凹腔性能、颗粒燃烧效率等参数的影响。结果表明该数值模拟方法具有较高的计算精度。研究发现增大燃气喷射角度可以提升燃料穿透深度,增加颗粒燃烧效率,但会造成总压损失升高;改变燃气喷射位置发现影响颗粒燃烧效率的原因不仅有颗粒的滞留时间,还包括颗粒所在区域的温度分布。Considering some problems in the combustion chamber of solid rocket ramjet,such as short fuel residence time,difficult mixing with air flow,poor flame stability,and low particle combustion efficiency,based on the Eulerian Lagrange method,a two-phase flow combustion simulation model was established and the primary gas was simplified by using the minimum free energy method and the law of conservation of energy and mass.Based on a solid rocket scramjet model with a cavity flame stabilizer,the influences of different gas injection angles and positions on temperature rise efficiency,total pressure recovery coefficient,cavity performance and particle combustion efficiency were explored.The results showed high calculation accuracy of this method.It was found that increasing the gas injection angle could improve the fuel penetration depth and increase the particle combustion efficiency,but the total pressure loss would increase;the change of gas injection location affected the combustion efficiency of particles not only because of the particle retention time,but also because of the temperature distribution in the region with the particles.

关 键 词：固体火箭超燃冲压发动机 气固两相流动燃烧 一次燃气 超声速流动 燃烧组织方案 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]