碳 氢 燃 料 超 燃 冲 压 发 动 机 热 非 平 衡 效 应

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 kerosene-fueled 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 at Mach number 10.