前缘钝化和化学非平衡效应对斜爆震发动机进气道特性的影响

为了探究前缘钝化、化学非平衡效应对斜爆震发动机进气道的工作性能及出口温度边界层分布的影响,采用热完全气体、化学非平衡气体两种模型对不同顶板、唇口前缘钝化半径下斜爆震发动机进气道进行数值模拟,结果表明：相比基准进气道,钝化后进气道上壁面温度边界层厚度较大,下壁面温度边界层厚度较小；在化学非平衡气体模型下,顶板前缘钝化半径(R1)>2mm时进气道的顶板附近和分离区内离解反应较为明显,唇口前缘钝化半径(R2)>2mm时进气道的唇罩、唇口板附近离解反应较为明显；当钝化半径≥4mm时,两种气体模型下进气道出口总压恢复系数和静温的相对变化量绝对值大于0.5%,有必要考虑化学非平衡气体效应对进气道出口性能的影响。

Influence of Leading Edge Blunt and Chemical Non-Equilibrium Effect on Characteristics of Inlet of Oblique Detonation Engine

In order to explore the influence of leading-edge blunt and chemical non-equilibrium effect on the working performance and the outlet temperature boundary layer distribution of the oblique detonation engine inlet, two models of thermally perfect gas and chemical non-equilibrium gas were used to simulate the inlet of oblique detonation engine with different top plate and lip leading edge blunt radius. The results show that compared with the basic inlet, the thickness of the temperature boundary layer on the upper wall of the blunted inlet is larger, and the thickness of the temperature boundary layer on the lower wall of it is smaller. Under the chemical non-equilibrium gas model, the dissociation reaction is more obvious near the top plate of the inlet and in the separation zone when R1>2mm, and the dissociation reaction is more obvious near the lip mask and lip plate of inlet when R2>2mm. When the blunt radius is not less than 4mm, the absolute value of the relative change of the total pressure recovery coefficient and the static temperature at exit of inlet under the two gas models is greater than 0.5%. It is necessary to consider the influence of the chemical non-equilibrium gas effect on performance at exit of inlet.