Numerical studies of flow patterns and fuel distribution of tandem-arranged multi jets in a hypersonic crossflow

In this paper, numerical simulations using Euler equations coupled detailed chemical reaction model are performed to reveal the influence of inhomogeneous distribution of inflow equivalence ratio (ER) on the morphology and characteristic of oblique detonation in hydrogen/oxygen/argon mixtures. The purpose of this study is to better understand the key parameters’ variation law of oblique detonation flow field under practical flight conditions so as to guide the design of oblique detonation chamber. Within the scope of our simulations, the results show that the oblique detonation wave (ODW) can still be standing under a large ER gradient. The thermodynamic state and characteristic sizes of the flow field reach the maximum value around ER = 0.8. First, the ODW angle and the post-wave temperature/pressure increase with the homogeneous inflow ER. Then, the inhomogeneity of inflow ER is introduced by assuming a lateral linear distribution covering the whole inflow boundary. When the ER increases along the inflow boundary with ER = 0 at the wedge tip, the overall morphology of the ODW presents a concave structure. Inversely, the ODW is convex with ER = 0 at the top outlet. The morphology and characteristic sizes of ODW are determined by the mixture composition in front of the corresponding wave surface. The transition mode of ODW is mainly determined by the ER of the incoming flow in front of the induction region.

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Injection angles on flow structures and mixing properties in a supersonic combustor at low Mach crossflow

Zhang,

Liang,

Wang

et al. 2024

Preprint

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The fuel-air mixing is of paramount importance in hypersonic air-breathing vehicles, and its performance is closely related to the fuel injection angle. This article presents an investigation into the influence of the injection angles on the flow and mixing processes in a supersonic combustor at low Mach supersonic inflow. Detailed flow characteristics are compared and analyzed, with a focus on instantaneous and average flows. Besides, several significant mixing parameters are thoroughly depicted. Results show that, in contrast to transverse injection, relatively strong fuel fluctuation is presented on the leeward side in comparison to the windward side in the near field for the inclined injection. Furthermore, the counter-rotating vortex pairs (CVP) are constricted by the inclination of the injection, giving rise to a decrease in jet-cavity interaction. Although inclined injection exhibits favorable performance in backpressure resistance at low Mach supersonic crossflow, it presents a greater challenge in terms of ignition, thus necessitating meticulous design considerations.

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Numerical studies of flow patterns and fuel distribution of tandem-arranged multi jets in a hypersonic crossflow

Cited by 3 publications

References 45 publications

Research on the mixing characteristics of a cavity based supersonic combustion chamber coupled with secondary recirculation jets

Research on the mixing characteristics of a cavity based supersonic combustion chamber coupled with secondary recirculation jets

Influence of inhomogeneous distribution of inflow equivalence ratio on oblique detonation morphology and characteristic

Injection angles on flow structures and mixing properties in a supersonic combustor at low Mach crossflow

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