流动参数对固液发动机燃料退移速率的影响  

Influence of inlet velocity and fuel geometry on regression rate of solid fuel in hybrid rocket motor

作　　者：孙得川[1] 王博[1] 夏广庆[1] 

机构地区：[1]大连理工大学航空航天学院,工业装备结构分析国家重点实验室,大连116024

出　　处：《固体火箭技术》2013年第4期496-499,510,共5页Journal of Solid Rocket Technology

基　　金：中央高校基本科研业务费专项资金资助项目

摘　　要：建立了固液混合火箭发动机流场与固体燃料之间热流固耦合计算的数值模型,通过模型指出建立燃料表面温度与退移速率之间的函数关系是耦合计算的唯一途径。针对二维平面燃烧情况,计算了入口氧化剂平均速度、几何斜面角度,以及燃面曲率对退移速率的影响。通过计算可知,提高氧化剂流速可提高退移速率;燃面与氧化剂的夹角只影响局部流动,对退移速率影响不大;沿着流向的燃面曲率影响较大,是提高退移速率的有效途径。The thermo-fluid-solid coupling model was established to simulate the heat transfer between combustion flowfield and solid fuel in hybrid rocket motor. Based on the model, the relationship of regression rate and fuel surface temperature was found to be the only way to calculate the regression rate accurately. For two-dimensional combustion, average velocity of oxidant, angle of fuel surface, and curvature of fuel surface were varied to study the influence on regression rate. The results show that increasing the velocity of oxidant can increase the regression rate. The angle of fuel surface has little effect on the regression rate and it can only affect the local domain near the head of the angle. The curvature of fuel surface along flow direction is an important parameter that can improve the regression rate effectively.

关 键 词：固液混合发动机 热流固耦合 退移速率 影响参数 

分 类 号：V436[航空宇航科学与技术—航空宇航推进理论与工程]