In order to reveal the multiphase flow field structure and fuel droplets distribution under rotating detonation ramjet engine fueled by liquid kerosene, non-premixed simulations coupled with an Euler-Lagrangian approach is adopted. Supersonic air is used as oxidizer and the total pressure and total temperature at the entrance of isolation are set as 1.2 MPa and 1100 K, respectively, with a Mach number of 1.9. It is shown that a single-wave is formed and typical rotating detonation wave structures are established under two different orifice spacing conditions, namely 2 mm and 6mm. A "rich oil and poor oxygen band" is formed and attributed to the inconsistent supply of fuel and air after the passage of the detonation wave. When the orifices spacing is increased from 2 mm to 6 mm, both obvious strips after the detonation wave and “n-type” deflagration structures near the contact surface are observed. Besides, the detonation wave front becomes discontinuous, as well as from the deflagration heat release distribution. Despite of the effect of the circumferential propagation of detonation wave, kerosene droplets still propagate mainly along the downstream direction. However, Kerosene droplets distribution shows obvious difference along the detonation wave propagation direction.

中文翻译：

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煤油燃料旋转爆轰冲压发动机流场结构及液滴分布的数值研究


为了揭示液态煤油燃料旋转爆震冲压喷气发动机下的多相流场结构和燃料液滴分布，采用非预混耦合的欧拉-拉格朗日方法。使用超音速空气作为氧化剂，隔离入口处的总压力和总温度分别设置为 1.2 MPa 和 1100 K，马赫数为 1.9。结果表明，在 2 mm 和 6 mm 两种不同的孔间距条件下，形成了单波并建立了典型的旋转爆轰波结构。形成“富油差氧带”，并将其归因于爆炸波通过后燃料和空气供应不一致。当孔口间距从 2 mm 增加到 6 mm 时，可以观察到爆震波后明显的条带和接触面附近的“n 型”爆燃结构。此外，爆轰波前变得不连续，爆燃热释放分布也是如此。尽管受到爆轰波圆周传播的影响，但煤油液滴仍然主要沿下游方向传播。然而，煤油液滴沿爆轰波传播方向的分布表现出明显的差异。