摘要
高超声速流动往往伴随着热化学非平衡效应,而热化学非平衡效应会对高超声速推进系统内的流动、燃烧带来一系列影响。采用双温度热化学非平衡模型以及热力学平衡模型,对飞行条件为马赫数10、高度29 km的煤油燃料超燃冲压发动机进行数值模拟,研究了热非平衡效应对发动机流动、燃烧及性能的影响。结果表明:热非平衡效应可以通过改变斜激波角度进而影响发动机内的流场结构和掺混效率。尽管热非平衡态下燃烧室前部的平衡温度较高,可以促进凹腔上游的燃烧,但对于凹腔后部的燃烧,热非平衡效应降低了热释放率峰值及燃烧效率。喷管中的振动非平衡效应可影响推力。总的来说,热非平衡效应降低了马赫数10煤油燃料发动机的性能。
Hypersonic flow is generally accompanied by the thermochemical non-equilibrium effect,which brings a series of effects on the flow and combustion in hypersonic propulsion systems.This paper gives a numerical investigation of the effects of thermal nonequilibrium on flow,combustion and engine performance by simulating the kerosenefueled scramjet at the free-stream conditions of Mach number 10 and 29 km.The thermochemical nonequilibrium and thermal equilibrium models are employed in this study.The results show that the thermal non-equilibrium effect can change the flow field structure and mixing efficiency in the engine by increasing the angle of oblique shock wave.The equilibrium temperature at the front of the combustion chamber is higher in the thermal non-equilibrium state,which can promote the combustion upstream of the cavity.However,the effect of thermal non-equilibrium reduces the peak heat release rate and combustion efficiency downstream of the cavity.The vibrational non-equilibrium in the nozzle can affect the thrust.In general,thermal non-equilibrium effects can reduce the performance of kerosene-fueled scramjet atMachnumber10.
作者
吴忧
陈兵
杨庆春
徐旭
WU You;CHEN Bing;YANG Qingchun;XU Xu(School of Astronautics,Beihang University,Beijing 102206,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2024年第11期259-271,共13页
Acta Aeronautica et Astronautica Sinica
基金
高超声速冲压发动机技术重点实验室支持项目(WDZC6142703202201)。
