Numerical simulation of the gas-liquid interaction of a liquid jet in supersonic crossflow

Li, Peibo; Wang, Zhenguo; Sun, Mingbo; Wang, Hongbo

doi:10.1016/j.actaastro.2016.12.025

Cited by 67 publications

(22 citation statements)

References 55 publications

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“…Betelin et al [17] developed a two-phase simulation system under Euler-Lagrange framework combined with the evaporation and combustion models in addition to the breakup model. And Li [18] captured the liquid trailing phenomenon in supersonic crossflows with Euler-Lagrange system. Although Euler-Lagrange system provides a practical way to simulate the two-phase flows in a large space scale with limited computational resources, the detailed behaviors cannot be captured in the nearfield region where primary breakup happens.…”

Section: Introductionmentioning

confidence: 99%

Simulation of liquid jet primary breakup in a supersonic crossflow under Adaptive Mesh Refinement framework

Liu

Wang

Sun

et al. 2019

Aerospace Science and Technology

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Compressible two-phase flows were simulated based on the five-equation model under the Adaptive Mesh Refinement (AMR) framework to balance the requirements between space resolution and computational cost. And the simulation system was established in an open source software AMROC (Adaptive Mesh Refinement Object-oriented C++). A combination of Godunov method and wave propagation method was introduced to integrate numerical methods with the AMR algorithm. High speed and high liquid-gas density ratio are two main challenges in the simulation of liquid jet in a supersonic crossflow. To enhance the robustness of the simulation system, a MOON-type positivity preserving method was adopted in the development of the codes. Based on the system mentioned above, a liquid jet in a Mach 1.5 supersonic crossflow was simulated as the standard case to study the primary

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Section: Introductionmentioning

confidence: 99%

Simulation of liquid jet primary breakup in a supersonic crossflow under Adaptive Mesh Refinement framework

Liu

Wang

Sun

et al. 2019

Aerospace Science and Technology

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“…Obviously, it is different from the atomization process of the jet in the transverse gas flow. Furthermore, the magnitudes and distribution of tangential, radial, and axial velocities, which directly affected the effect of jet atomization and separation performance, are also different in the jet‐swirling coupled field . However, due to the complexity of the jet‐swirling coupled flow field and the limitations of the experimental conditions, it is difficult to study the distribution of the internal flow field systematically …”

Section: Introductionmentioning

confidence: 99%

Investigation of gas–liquid two‐phase flow field behavior based on computational fluid dynamics in a water‐sparged aerocyclone

Qiu

Quan

2018

Asia-Pacific J Chem Eng

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The water-sparged aerocyclone (WSA) is a new type of high efficient gas-liquid mass transfer equipment. The focus of this paper is to investigate the gas-liquid interaction, the distribution pattern of the flow field, and the distribution characteristics of turbulent kinetic energy in the coupled space of WSA. The Reynolds stress model and the multiphase flow model of volume of fluid were employed to simulate the distribution of three-dimensional flow field in WSA, simultaneously. In present work, the numerical simulation results match well with the measured pressure drop data. The simulation results show that the symmetry of the velocity distribution of the coupled field is weakened, and the decay rate of turbulent kinetic energy is raised with the increase of gas inlet velocity. The maximum value of the axial velocity occurs a phenomenon of metastasis from the vicinity of the wall to the center of the exhaust pipe along the radial distribution. The radial velocity reaches a maximum near the center of the coupling field. The tangential velocity distribution has peak areas near the WSA wall and near the central exhaust pipe, respectively. The research results can provide the basis for the optimal design and industrial scale-up of WSA. KEYWORDS computational fluid dynamics (CFD), flow field behaviors, gas-liquid, turbulent kinetic energy (TKE), water-sparged aerocyclone (WSA)

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“…Nowadays, there are some classical methods for drag reduction, including non-smooth surface drag reduction method, [1][2][3][4][5] super-hydrophobic surface drag reduction method, 6,7 smooth wall drag reduction method, 8 electromagnetic vibration drag reduction method, 9,10 high polymer additive method 11 and jet drag reduction method. 12,13 The jet drag reduction method is mainly applied in the field of supersonic and hypersonic. Transverse jet technology has been applied widely into engineering applications, such as dispersing contaminant, cooling combustion chamber of turbine, gasdriven control of aircraft 14 and so on.…”

Section: Introductionmentioning

confidence: 99%

Research on drag reduction performance of turbulent boundary layer on bionic jet surface

Zhao

Liu

2016

Proceedings of the Institution of Mechanical Engineers, Part M:

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Based on the fact that jet formed in outer gill of sharks can reduce the wall friction during the breath process, a bionic jet surface model was established. The numerical simulations were carried out using shear stress transport k2v model, and the simulation results accorded with that of experiments. First, in the case of fixed flow-velocity ratio, the drag reduction performance would be better with the smaller jet's angle, and the impact that the angle has on the drag reduction would be greater with the increase in jet hole's aperture. Second, in the case of fixed jet's angle, the drag reduction had a nearly linear relationship with flow-velocity ratio. Namely, the drag reduction would be better as the flow-velocity ratio increased, and the larger the jet hole's aperture, the better the drag reduction. In addition, compared with the case of smoothing surface, the flow structure in turbulent boundary layer was changed by jet, increasing the thickness of viscous bottom layer and decreasing the gradient of normal velocity perpendicular to wall. Finally, the drag reduction mechanism was proposed based on the increased velocity effect of turbulent core, isolation effect of wall and the increased turbulent damping effect.

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Numerical simulation of the gas-liquid interaction of a liquid jet in supersonic crossflow

Cited by 67 publications

References 55 publications

Simulation of liquid jet primary breakup in a supersonic crossflow under Adaptive Mesh Refinement framework

Simulation of liquid jet primary breakup in a supersonic crossflow under Adaptive Mesh Refinement framework

Investigation of gas–liquid two‐phase flow field behavior based on computational fluid dynamics in a water‐sparged aerocyclone

Research on drag reduction performance of turbulent boundary layer on bionic jet surface

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