全流量补燃循环液氧甲烷发动机推力调节方案研究  

Study on the Control Scheme of Full-Flow Staged CombustionCycle Liquid Oxygen/Liquid Methane Engine

作　　者：邢理想 苏展 张航 武晓欣 张卫红[1] XING Lixiang;SU Zhan;ZHANG Hang;WU Xiaoxin;ZHANG Weihong(Northwestern Polytechnical University,Xi’an 710100,China;Xi’an Aerospace Propulsion Institute,Xi’an 710100,China)

机构地区：[1]西北工业大学,西安710100 [2]西安航天动力研究所,西安710100

出　　处：《宇航总体技术》2023年第4期33-40,共8页Astronautical Systems Engineering Technology

基　　金：国家部委重点实验室基金(6142704210102)。

摘　　要：无毒、无污染的大推力可重复使用液氧甲烷发动机成为研究热潮,以200 t级全流量补燃循环液氧甲烷发动机为研究对象,结合真实气体效应下涡轮绝热功模型和低温冷却套模型,对比分析了发动机多种调节元件设置方案,结果表明富氧发生器、富燃发生器副路调节元件分别设置为调节器和节流阀时,发动机推力和混合比耦合程度相对较低,利于单一工况参数的调节。在此系统方案基础上,通过仿真对比分析,选择出了最佳推力调节方案。The non-toxic,non-polluting large thrust reusable liquid oxygen methane engine has become a hot research topic.In this paper,a 200-ton full flow combustion cycle liquid oxygen methane engine is taken as the research object,combined with the real gas effect of the turbine adiabatic work model and the low temperature cooling jacket model,the setting scheme of various regulating elements of the engine is compared and analyzed.The results show that the oxygen-enriched generator,The coupling degree of engine thrust and mixing ratio is relatively low when the sub-circuit adjusting element of fuel-rich generator is respectively set as regulator and throttle valve,which is beneficial to the adjustment of single working condition parameters.On the basis of this system scheme,through simulation and comparison analysis,the optimal thrust adjustment scheme is selected.

关 键 词：全流量补燃循环 液氧甲烷 推力调节 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]