两相流对固体火箭发动机塞式喷管性能的影响  

Effect of two-phase flow on performance of plug nozzle in solid rocket motor

作　　者：李泓瑾 李军伟[1] 谢侃[1] 李想 杨正 王宁飞[1] LI Hongjin;LI Junwei;XIE Kan;LI Xiang;YANG Zheng;WANG Ningfei(School of Astronautics,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：《航空学报》2023年第16期22-33,共12页Acta Aeronautica et Astronautica Sinica

摘　　要：针对固体火箭发动机中气固两相流对塞式喷管性能的影响,利用颗粒轨道模型法计算了环喉型塞式喷管两相流流场,辨识颗粒在流场中的运动轨迹,分析不同粒径颗粒对流场及推力性能的影响。结合传统钟形喷管,比较不同工况下塞式喷管与钟形喷管的推力性能,分析气固两相流对塞式喷管高度补偿特性的影响。结果表明:随着颗粒粒径的增大,颗粒会出现交错式的运动,增加了流场的复杂性;单个颗粒与该截断式塞锥只会发生一次碰撞,且粒径越大,碰撞位置越靠前;单一粒径颗粒带来的推力性能损失与颗粒粒径成正比,与工作压比成反比;真实工作条件下,相比于钟形喷管,气固两相流在设计工况对塞式喷管带来约3%更多的推力效率损失,推力效率最终趋于弱于钟型喷管2.7%,但塞式喷管在低压比工况仍具有可观的性能优势。To study the effect of gas-solid two-phase flow on performance of the plug nozzle in solid rocket motor,the two-phase flow field of annular plug nozzle was calculated by particle track model,the movement track of particles in flow field was identified,the influence of different particle sizes on flow field and thrust performance of nozzle was ana⁃lyzed.Combined with traditional bell nozzle,the thrust performance of plug nozzle and bell nozzle under different working conditions was compared,the influence of gas-solid two-phase flow on the height compensation characteris⁃tics of plug nozzle was analyzed.The results show that with the increase of particle size,the particles will appear stag⁃gered motion,which increases the complexity of the flow field.And there is only one collision between a single particle and the truncated plug,and the larger the particle size,the more advanced the collision position.The thrust perfor⁃mance loss caused by single particle size is proportional to particle size and inversely proportional to working pressure ratio.Under real working conditions,compared with bell nozzle,gas-solid two-phase flow brings about 3%more thrust efficiency loss to plug nozzle in the design condition,and thrust efficiency eventually tend to be weaker than the bell nozzle at 2.7%,but plug nozzle still has considerable performance advantage in low pressure ratio condition.

关 键 词：火箭喷管 环喉型塞式喷管 高度补偿 两相流 固体火箭发动机 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]