某固体火箭发动机喷管传热烧蚀数值模拟  

Numerical Simulation on Heat Transfer and Ablation for the Nozzle of a Solid Rocket Motor

作　　者：白涛涛[1] 孙振华[1,2] BAI Taotao;SUN Zhenhua(China Airborn Missile Academy,Luoyang 471009,Henan,China;Aviation Key Laboratory of Science and Technology on Airborne Guided Weapons,Luoyang 471009,Henan,China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]航空制导武器航空科技重点实验室,河南洛阳471009

出　　处：《弹箭与制导学报》2022年第4期119-124,共6页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：针对某固体火箭发动机喷管,采用商用CFD软件二次开发功能编写传热烧蚀计算程序,建立喷管扩张段传热烧蚀计算方法,开展了喷管流-固-热耦合数值计算研究,得到了不同时刻喷管扩张段密度、比热容、导热系数及静温变化情况,预估了喷管扩张段体积烧蚀、表面烧蚀及外壁温度随时间变化规律,并与试验结果进行了对比分析。结果表明:碳/酚醛扩张段上的表面烧蚀主要集中在靠近喉衬的左半区,并且主要由发动机一级高压工作段引起;扩张段体积烧蚀质量损失率在发动机初始工作时最大,随后逐渐减小。Aim at the nozzle of SRM,the heat transfer and ablation are programmed using the secondary development function of commercial CFD software,the calculation method of heat transfer and ablation for nozzle divergent is developed,and the fluid-solid-thermal coupling numerical calculation of nozzle is carried out,the density,specific heat capacity,thermal conductivity and temperature of nozzle divergent under different times are obtained,the variation of volume ablation,surface ablation and outside wall temperature with time for nozzle divergent are estimated,and comparisons are made between simulation and test results.It shows that:the surface ablation of divergent is centred on the left half that is close to throat,which is generated by the high pressure working section of SRM;the mass loss rate of volume ablation for nozzle divergent is the largest in the initial stage of working process for SRM,and then it gradually decreases.

关 键 词：固体发动机 喷管 传热 烧蚀 碳/酚醛 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]