氢燃料冲压旋转爆震自由射流试验研究  

Free Jet Experimental Research of Hydrogen-Air Rotating Detonation Ramjet Engine

作　　者：郑榆山 王超 李宏斌 岳茂雄 乐嘉陵 刘彧 ZHENG Yu-shan;WANG Chao;LI Hong-bin;YUE Mao-xiong;LE Jia-ling;LIU Yu(Aerospace Technology Institute of CARDC,Mianyang 621000,China;Science and Technology on Scramjet Laboratory,CARDC,Mianyang 621000,China)

机构地区：[1]中国空气动力研究与发展中心空天技术研究所,四川绵阳621000 [2]中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室,四川绵阳621000

出　　处：《推进技术》2022年第12期342-351,共10页Journal of Propulsion Technology

基　　金：国家自然科学基金(11702316);中国空气动力研究与发展中心基础和前沿技术研究基金(PJD20190073)。

摘　　要：为探索旋转爆震燃烧在冲压发动机中的应用,基于氢燃料开展了Ma=3.1条件下不同当量比旋转爆震冲压发动机自由射流试验。燃烧室构型为圆环形,燃烧室内径54mm,外径90mm,隔离段内径64mm,外径80mm。燃料喷注采用30对喷孔双侧间隔喷注,喷孔直径0.4mm。高温高速空气由脉冲燃烧风洞提供并经发动机进气道捕获进入旋转爆震燃烧室,捕获空气流量约380g/s。试验中实现了冲压模态下旋转爆震波的稳定自持传播,燃烧室内形成同向单波模态,爆震波传播频率为6.34~6.73kHz,爆震传播速度为1434.07~1522.29m/s。试验结果表明,在Ma=3.1来流条件下,冲压模态旋转爆震燃烧具有可行性,同时随当量比提高,爆震波传播频率波动逐步扩大,爆震波传播稳定性有所下降。In order to explore the application of rotating detonation combustion in ramjet engine,H2/Air rotating detonation free jet experiment was carried out under Ma=3.1 inlet condition.Annular combustor was adopted and the inner and outer diameters were respectively 54mm and 90mm.Besides,the inner and outer diameters of the isolator were 64mm and 80mm.30 pairs of orifices with diameter of 0.4mm were used respectively in the inner and outer wall.High temperature and high speed airflow was provided by a pulsed combustion wind tunnel and captured by the engine inlet.The captured mass flow rate was about 0.38kg/s and the stable and self-sustained propagation of the rotating detonation wave in ramjet mode was realized in the experiment.Single-wave mode was formed in the combustor.The propagation frequency of the detonation wave ranged from 6.34~6.73 kHz and the speed was about 1434.07~1522.29m/s.Based on this study,the experiments verify the feasibility of rotating detonation ramjet engine under Ma3.1 inlet condition.With the increase of equivalent ratio,the frequency fluctuation of the detonation wave gradually expands and the propagation stability of the detonation wave decreases.

关 键 词：旋转爆震 冲压发动机 自由射流 起爆过程 试验研究 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]