RBCC发动机不同模态下推阻力特性仿真  

Simulation on thrust/drag property in different modes of RBCC engine

作　　者：杨建文 刘计武 张蒙正 南向军 YANG Jianwen;LIU Jiwu;ZHANG Mengzheng;NAN Xiangjun(Key Laboratory of Science and Technology on Liquid Rocket Engine,Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)

机构地区：[1]西安航天动力研究所液体火箭发动机技术重点试验室,陕西西安710100

出　　处：《火箭推进》2022年第6期52-58,共7页Journal of Rocket Propulsion

基　　金：国家重点实验室联合基金(U1967203)。

摘　　要：以某RBCC组合发动机试验件为研究对象,对发动机的流动与燃烧过程开展了三维数值模拟,发动机顶壁面中心线上的静压分布计算结果与试验数据吻合较好,验证了仿真分析的合理性以及计算结果的准确性。结果表明:同一来流条件下,发动机正常工作时,不同模态下,进气道的空气捕获流量和产生的阻力相同;冷态工作时,虽然尾喷管会产生一定的推力,但由于进气道和燃烧室会产生很大的阻力,导致发动机整体产生的是阻力;火箭模态下,火箭会产生引射作用,同时火箭燃气与引射空气发生二次化学反应,发动机产生的推力与纯火箭相比,有一定的推力增益,推力增益约12.7%;冲压模态下,在余气系数大于1的情况下,随着煤油流量的增加,煤油与空气的混合比越靠近当量混合比,发动机产生的推力也会随着增大。Combustion flow of a RBCC test model was simulated through the three-dimensional numerical methods.Good agreements between computation and experimental results were obtained for wall static pressure distribution, validating that the numerical scheme employed is reliable.Results show that, to the same flow conditions, when the engine works properly, the air mass flux and the drag of the inlet are the same under different model.For the cold flow model, although the nozzle produced some thrust, but the inlet and combustor produced much more drag, so the engine will produce drag.For the rocket model, rocket will have ejector effect, and the ejector air will combustion again with the rocket gas, the engine thrust will be larger than the rocket thrust, and have 12.7% thrust gain.For the ramjet model, when the residual gas coefficient decreased, the engine thrust will increase.

关 键 词：火箭基组合循环 工作模态 推力 阻力 仿真研究 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]