环形燃烧室中自燃推进剂的非稳态旋转爆震现象  

Unsteady rotating detonation phenomenon of hypergolic propellant in annular combustor

作　　者：严宇 王致程 胡洪波 洪流 杨宝娥 YAN Yu;WANG Zhicheng;HU Hongbo;HONG Liu;YANG Baoe(Science and Technology on Liquid Rocket Engine Laboratory,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实验室,陕西西安710100

出　　处：《火箭推进》2023年第6期55-62,81,共9页Journal of Rocket Propulsion

基　　金：国家自然科学基金(51506157,11602186);陕西省自然科学基础研究计划(2022JQ-490);重点实验室基金(HTKJ2022KL011002)。

摘　　要：为研究环形燃烧室中自燃推进剂旋转爆震波的传播特性,以一甲基肼和四氧化二氮为推进剂,在圆环形燃烧室中组织旋转爆震燃烧。燃烧室外径和内径分别为60 mm和30 mm,采用了24对撞击式喷嘴,四氧化二氮的喷孔直径为0.4 mm,一甲基肼的喷孔直径为0.3 mm,通过高频脉动压力传感器记录了旋转爆震波的传播过程。研究结果表明:自燃推进剂的旋转爆震燃烧过程具有高度非稳态特性,不仅各个旋转周期之间存在明显差异,而且同一个传播周期内旋转爆震波的强度也是动态变化的;对于自燃推进剂的旋转爆震燃烧的产生及维持过程来说,外界激励不起决定性作用,燃烧室几何构型、流量和混合比对旋转爆震燃烧的影响更大。To investigate the propagation characteristics of rotating detonation waves utilizing hypergolic propellant,the rotating detonation was organized in an annular combustor using methylhydrazine as the fuel and nitrogen tetroxide as the oxidizer,respectively.In the combustor with inner diameter 30 mm and outer diameter 60 mm,twenty-four pairs of impinging injection elements were used with oxidizer orifice 0.4 mm and fuel orifice 0.3 mm.Pressure sensors with low sampling rate and high frequency dynamic pressure sensors were used to record the supply and combustion pressures.The results show that the rotating detonation combustion of hypergolic propellant is highly unstable.The detonation wave strength is not only varying from cycle to cycle,but also changing very fast within one cycle.For the generation and maintenance process of rotational detonation combustion with hypergolic propellant,the external stimulation is not a significant factor,and the combustor geometry,mass flow rate and mixture ratio play more important role at rotating detonation.

关 键 词：旋转爆震 自燃推进剂 环形燃烧室 实验 非稳态 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]