不同燃烧室结构下的碳/空气两相旋转爆轰发动机数值研究  

Numerical study of carbon/air two-phase rotating detonation engines with different combustor configurations

作　　者：祝文超 宋玉 王宇辉 王健平[2] 张国庆[3] ZHU Wenchao;SONG Yu;WANG Yuhui;WANG Jianping;ZHANG Guoqing(College of Mechanical and Electrical Engineering,Beijing University of Chemical Technology,Beijing 100029,China;College of Engineering,Peking University,Beijing 100871,China;School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]北京化工大学机电工程学院,北京100029 [2]北京大学工学院,北京100871 [3]北京理工大学宇航学院,北京100081

出　　处：《推进技术》2024年第11期108-118,共11页Journal of Propulsion Technology

基　　金：中央高校基本科研业务费专项资金(buctrc201913)。

摘　　要：气固两相旋转爆轰发动机的研究有望提高固体冲压发动机的推进性能。由于实验的局限性,燃烧室内的颗粒分布和流场结构等在很大程度都是未知的。本文以常温条件的碳/空气作为推进剂,对不同当量比下的环形和空心燃烧室进行了三维数值模拟研究。气相化学反应模型采用层流有限速率模型,碳燃烧采用多表面反应模型,颗粒直径为1μm。结果表明:空心燃烧室内未完全燃烧的颗粒数量增加,接触面发生褶皱且波后无低温条带;在环形燃烧室中,爆轰波与燃烧室壁面的相互碰撞产生新的爆轰波,而空心燃烧室的新爆轰波是由燃烧室下游激波对撞后形成的高压区产生的。相比于环形燃烧室,空心燃烧室内爆轰波的压力偏低,颗粒的燃烧效率降低,相同燃料与空气流量条件下发动机的推力下降且更加不稳定。Solid-gas two-phase rotating detonation engines have been widely studied,which may be ex⁃pected to improve the propulsive performance of solid ramjets,but experimental limitations have prevented the full information of the particle distribution and flow field from being revealed.This paper conducts a three-dimen⁃sional numerical study on annular and hollow combustors at different equivalence ratios,using carbon/air as the propellant at room temperatures.The laminar finite rate reaction model and the multiple surface reaction model are used for the gaseous chemical reaction and the carbon combustion,respectively.The particle diameter is 1μm.The results show that the number of incompletely burned particles is larger in the hollow combustor,the contact surface is uneven and there is a lack of the low temperature strip behind detonation waves.The annular combustor forms new detonation waves by colliding of detonation waves with the combustor wall,whereas the hol⁃low combustor forms new detonation waves through the high-pressure area generated by shockwave collisions downstream of the combustor.Compared with the annular combustor,the hollow combustor has lower detonation pressure of detonation wave and combustion efficiency of the particles.In the same fuel and air mass flow rate con⁃ditions,the engine thrust is lower and more unstable in the hollow combustor.

关 键 词：旋转爆轰发动机 空心燃烧室 环形燃烧室 数值模拟 爆轰波 

分 类 号：V231.22[航空宇航科学与技术—航空宇航推进理论与工程]