针栓式液氧/煤油发动机燃烧数值仿真  

Numerical simulation of combustion for LOX/kerosene engine with pintle injector

作　　者：俞南嘉[1] 鲍启林 张洋[1] 戴健[1] YU Nanjia;BAO Qilin;ZHANG Yang;DAI Jian(School of Astronautics,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《火箭推进》2018年第4期23-29,共7页Journal of Rocket Propulsion

摘　　要：为了研究低温非自燃推进剂应用针栓式喷注器的流场分布规律,总结不同动量比对针栓式发动机燃烧流场的影响,采用数值仿真的方法研究针栓式液氧/煤油发动机的燃烧流场分布,仿真模型采用k-ε湍流模型、有限速率-涡耗散燃烧模型等。仿真结果表明:针栓式发动机在燃烧室内形成两个回流区,有利于燃烧室头部冷却;针栓式喷注器能够在燃烧室壁面形成液膜,提高了燃烧室壁面的热防护;随着动量比增加,燃烧高温区向燃烧室壁面靠近;动量比为1时,针栓式喷注器具有最佳的燃烧效率。In order to study the flow field distribution of the pintle injector with cryogenic and nonhypergolic propellant,the influence of different momentum ratios on the combustion flow field is summarized for the engine. In this paper,a numerical simulation method is used to investigate the distribution of the combustion flow field for LOX/kerosene engine with pintle injector. The simulation model adopts k-εturbulence model,finite rate/eddy-dissipation combustion model,etc. The simulated results show that the pintle engine can form two recirculation zones in the combustion chamber,which is beneficial to the cooling of the combustion chamber head. In addition,the pintle injector can form liquid film on the wall of combustion chamber,which improves the thermal protection of combustion chamber wall. As the momentum ratio increases,the high temperature area in combustor approaches to the wall of combustion chamber,and the pintle injector achieves the highest combustion efficiency when the momentum ratio is 1.

关 键 词：针栓式喷注器 数值仿真 仿真模型 燃烧效率 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]