Combustion dynamics of high Mach number scramjet under different inflow thermal nonequilibrium conditions

Ao, Yu; Wu, Kun; Lu, Hongbo; Feng, Jing; Fan, Xuejun

doi:10.1016/j.actaastro.2023.04.020

Cited by 10 publications

(2 citation statements)

References 34 publications

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“…The diameter of each nozzle is mm, and they are perpendicular to the wall surface. A1 and A2 are located on the uppe Hydrogen-fueled scramjet engines, due to their high specific impulse characteristics, have broad application prospects in hypersonic vehicles; hence, researchers have conducted numerous simulations of hydrogen fuel combustion [23][24][25][26][27][28][29][30]. Wang et al [23] conducted research on the combustion performance of a hydrogen-fueled scramjet engine, revealing a positive feedback relationship between the lift shear layer in the recirculation zone and enhanced combustion, which demonstrates the strong robustness of the shear layer/recirculation stable combination mode.…”

Section: Computational Domain and Relevant Parametersmentioning

confidence: 99%

“…The results showed that the presence of nonequilibrium at lower vibrational temperatures inhibits combustion, and nonequilibrium effects play an essential role in the internal structure of the flame. Ao et al [27] investigated the impact of different degrees of thermodynamic nonequilibrium on supersonic hydrogen/air combustion. The results showed that when the inlet vibration temperature was 688.38 K and 1088.42 K, the combustion efficiency was 76% and 84%, respectively.…”

Section: Computational Domain and Relevant Parametersmentioning

confidence: 99%

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Parametric Study of Flow and Combustion Characteristic in a Cavitied Scramjet with Multi-Position Injection

Xi,

Liu,

Shao

et al. 2024

Fire

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This study focuses on the three-dimensional flow and combustion characteristics of a cavitied scramjet engine with multi-position injection. A single-equation large eddy simulation (LES) turbulence model is employed, with a detailed reaction mechanism for hydrogen combustion, as described by Jachimowski. The combustion characteristics of hydrogen in the scramjet combustion chamber are analyzed. Based on the combustion chamber model, the influence of different equivalence ratios, injection timing, injection positions, and injection pressures on the flame formation and propagation process are compared. The results indicate that within a certain range, an increase in the equivalence ratio enhances the combustion intensity and chamber pressure. In the case of multi-position injection, the order of injection from different nozzles has little effect on the final flame stabilization mode and pressure distribution. The opposite-side distribution of nozzles can effectively improve the fuel efficiency and the internal pressure. Furthermore, when the nozzles are closely placed in the opposite-side distribution, the combustion efficiency increases, although this leads to a higher total pressure loss. In scenarios where the fuel injection duration is short, an increase in the injection pressure at the upstream nozzles of the cavity results in a higher local equivalence ratio, as well as reduced fuel mixing and ignition time.

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