来流总温对液态煤油旋转爆震影响的数值模拟  

Numerical Simulation of Influence of Inlet Total Temperature on Rotational Detonation in Liquid Kerosene

作　　者：王嘉瞳 李夏飞 秦琼瑶 金武 WANG Jiatong;LI Xiafei;QIN Qiongyao;JIN Wu(AECC Shenyang Engine Research Institute,Shenyang 110015,China;College of Energy and Power Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《南京航空航天大学学报》2024年第2期350-357,共8页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金(52276118)。

摘　　要：为了实现煤油/富氧空气旋转爆震燃烧室稳定工作并探索来流总温对流场及爆震燃烧特性的影响,设计了一种液态煤油/富氧空气旋转爆震燃烧室结构,采用欧拉⁃拉格朗日算法开展了旋转爆震燃烧室的冷热态数值模拟。结果表明,随着来流总温的提升,在温度及停留时间的共同作用下,燃油雾化掺混效果并非是来流总温越高越好,而是在1150 K下最优,燃油蒸发率达99.2%,掺混均匀度为50.3%。来流总温超过650 K的条件下均可以实现稳定的旋转爆震工作模式。来流总温的变化对于爆震波的传播模态有着显著的影响,来流总温越大,越有利于液态煤油/富氧空气旋转爆震燃烧室内多波模态的形成。随着爆震波波头数目的增加,单个波头的压力、波速及爆震波高度随之下降,而整体爆震波的稳定性得到了明显的提升。In order to realize the stable operation of the kerosene/oxygen-enriched air rotating detonation combustion,the influence of total inlet temperature on the flowfield and combustion characteristics was explored.In this paper,a liquid kerosene/oxygen-enriched air rotating detonation combustor is designed.The non-reacting and reacting flowfied is simulated with the Euler-Lagrange algorithm.Results show that with the increase of the total inlet temperature,the fuel atomization and mixing effect shows a parabolic trend.At 1150 K,the fuel evaporation rate is the highest(99.2%),and the blending uniformity is 50.3%.Under the condition that the total inlet temperature exceeds 650 K,a stable rotating detonation wave can be achieved.The total inlet temperature has a significant impact on the propagation mode of the detonation wave.The total inlet temperature is beneficial for the formation of the multi-wave mode of detonation.With the increase of the number of detonation wave,the pressure,wave velocity and detonation wave height of a single wave decrease,and the stability of the overall detonation wave is significantly improved.

关 键 词：煤油 旋转爆震燃烧室 雾化掺混 爆震波稳定性 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]