复合喷管结构流固耦合仿真分析及试验研究  

Coupled Numerical Simulation on Flow Field and Thermo-structure and Experiment Research of Composite Nozzle

作　　者：吴秋 姬铮 任全彬[2,3] 陈林泉 张明[2,3] WU Qiu;JI Zheng;REN Quanbin;CHEN Linquan;ZHANG Ming(Northwestern Polytechnical University,Xi’an 710072,China;The 41st Institute of the Fourth Academy of CASC,Xi’an 710025,China;National Key Lab of Combustion,Flow and Thermo-structure,Xi’an 710025,China)

机构地区：[1]西北工业大学,西安710072 [2]中国航天科技集团公司第四研究院第41研究所,西安710025 [3]固体火箭发动机燃烧、热结构与内流场国防科技重点实验室,西安710025

出　　处：《弹箭与制导学报》2020年第2期117-120,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了获得高低燃温组合推进剂下喷管结构温度及喉衬烧蚀率变化,开展了组合推进剂下复合喷管结构的流固耦合分析及试验研究,仿真计算及试验结果表明,低燃温推进剂燃气能有效降低流场向喷管结构的热量传递,降低喷管结构温度。并且低燃温推进剂能有效降低高温燃气对喉衬的烧蚀,与纯高燃温推进剂发动机烧蚀率相比,使用组合推进剂时喉衬烧蚀率下降15.8%。In order to obtain the varieties of nozzle temperature and throat erosion by using pure-high temperature propellants and high-low temperature combined propellants.Coupled numerical simulation on flow field and Thermo-structure of composite nozzle and experiments were implemented.The simulation and experiments results indicated the low temperature propellants can bring down the nozzle structure temperature effectively.The low temperature propellants can also reduce the throat erosion effectively by hot-gas.The ablation rate using combined propellants decline 15.8%compared with pure-high temperature propellants.

关 键 词：高低燃温组合推进剂 流固耦合 外壁面温度 烧蚀率 

分 类 号：TP751.1[自动化与计算机技术—检测技术与自动化装置] V430[自动化与计算机技术—控制科学与工程]