摘要
本文基于RANS方法对马赫数6飞行条件下的乙烯燃料圆截面超燃冲压发动机燃烧流场开展了数值研究,计算中采用了压力相关的火焰面/进度变量模型,得到的数值结果与试验吻合,并据此分析了0.18和0.06当量比工况的火焰结构和燃烧特征。计算表明,0.18当量比工况释热强度高,在流场中形成了热壅塞,并且预混燃烧和扩散燃烧共同主导了整体的释热。而0.06当量比工况流道中心仍是超声速状态,扩散火焰主导了整体的释热。2个工况中,射流背风区和轴对称凹腔都是重要的反应区,其中射流背风区释热强度高,而凹腔起到了增强混合和提高燃烧效率的重要作用。
A numerical study on the combustion flow field of an ethylene-fueled circular-section scramjet engine under Mach number 6 flight condition is conducted based on the RANS method.A pressure-related flamelet/progress variable model is used in the calculations,and the numerical results obtained are in good agreement with the experiments.Accordingly,the flame structure and combustion characteristics were analyzed for the high and low equivalence ratio cases.Calculations show that the high equivalence ratio case has a high level of heat release,forming a thermal congestion in the flow field,and that the premixed combustion and diffusion combustion together dominate the overall heat release.In the low equivalence ratio case,the center of the flow channel is still supersonic,and the diffusion flame dominates the overall heat release.In both cases,the jet leeward zone and the axisymmetric cavity are important reaction zones,where the former has a high heat release intensity,while the latter plays an important role in enhancing mixing and improving combustion efficiency.
作者
于江飞
汤涛
闫博
汪洪波
杨揖心
熊大鹏
孙明波
Jiangfei YU;Tao TANG;Bo YAN;Hongbo WANG;Yixin YANG;Dapeng XIONG;Mingbo SUN(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2024年第14期215-228,共14页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(11925207,92252206,12102471,12002376)
