Numerical investigation of shock-SF6 bubble interaction with different mach numbers

Zhu, Yuejin; Yang, Zhiwei; Pan, Zhenhua; Zhang, Penggang; Pan, Jianfeng

doi:10.1016/j.compfluid.2018.10.009

Cited by 20 publications

(9 citation statements)

References 23 publications

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“…For the time advancement, a third-order Runge-Kutta algorithm is used. The present numerical method has been utilized successfully in previous studies [16][17][18].…”

Section: A Numerical Methodsmentioning

confidence: 99%

Flame evolution in shock-accelerated flow under different reactive gas mixture gradients

et al. 2019

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The interaction between a planar shock wave and a spherical flame is studied numerically for an ethyleneoxygen-nitrogen gas mixture. Influences of different initial reactive gas mixture gradients on the shock-flame interaction are investigated by using high-resolution computational simulations. The results show that the different reactive gas mixture gradients can greatly affect the flame evolution in shock accelerated flow. A detonation only emerges in the homogenous reactive gas mixture case, but a distinct shock bifurcation can be found in the inhomogeneous cases where the leftward reflected shock wave propagates in a reverse flow with a high transverse velocity gradient in the inhomogeneous cases. Also, the flame volume and heat release rate increase when the distribution of the reactive gas mixture is uniform or with a positive gradient in this paper, but decrease when the distribution of the reactive gas mixture is with a negative gradient, however, the ratio of unburned to burned regions in the flame zone shows just the opposite trends. Furthermore, the factors affecting the vorticity generation are also analyzed. It is found that the compression term has a relatively stronger influence on the vorticity generation in all the three cases except the period before the reflected shock wave impinges on the distorted flame in the homogeneous case, wherein the baroclinic effect dominates the vorticity generation in the flame zone.

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“…For the time advancement, a third-order Runge-Kutta algorithm is used. The present numerical method has been utilized successfully in previous studies [16][17][18].…”

Section: A Numerical Methodsmentioning

confidence: 99%

Flame evolution in shock-accelerated flow under different reactive gas mixture gradients

et al. 2019

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“…The values are set to k = 2.34 × 10 −2 J m −1 K −1 s −1 , µ = 1.86 × 10 −5 kg m −1 s −1 , and D = 1.73 × 10 −5 m −2 s −1 , respectively. 21 To avoid unphysical oscillations for the computational results, a global Lax-Friedrich's flux splitting combined with a ninth-order weighted essentially nonoscillatory (WENO) scheme 23 third-order Runge-Kutta method is used to integrate the equations in time marching.…”

Section: A Numerical Methodsmentioning

confidence: 99%

“…The uniform mesh size 0.1 mm is adopted in the present study, which is sufficient to ensure the computational accuracy and minimize the computation cost simultaneously. 20,21…”

Section: B Computational Setupmentioning

confidence: 99%

“…The results showed that the shock focusing pattern was governed by the Atwood number, Mach number, and the bubble shape simultaneously. The authors [19][20][21] also numerically investigated the deformation and instability of He and SF 6 bubbles, and the formation and evolution of vortex rings, shock wave, and the influences of initial parameters (such as the incident shock wave strengths) were analyzed in detail. Recently, the interaction between a planar shock wave and square and triangular bubbles containing SF 6 , He, argon (Ar), or carbon dioxide (CO 2 ) was numerically studied by Igra and Igra.…”

Section: Introductionmentioning

confidence: 99%

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Numerical investigation of planar shock wave impinging on spherical gas bubble with different densities

Zhu,

Yang,

Luo

et al. 2019

Physics of Fluids

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The interaction between a planar shock wave and a spherical gas bubble containing sulfur hexafluoride, Refrigerant-22, neon, or helium is studied numerically. Influences of the Atwood number (At) on the evolution of the shock wave and gas bubble are clarified by using highresolution computational simulations. The results show that the difference in the physical properties between the ambient air and the gas bubble has a significant influence on the evolution of wave pattern and bubble deformation. For the fast/slow configuration (At > 0) in the present study (At = 0.67 and 0.51), the incident shock focuses near the interior right interface to form an outward jet. Besides, the mixedness, average vorticity, and the absolute value of circulation all increase as the Atwood number increases. By contrast, for the slow/fast configuration (At < 0) with At = −0.19 and −0.76, the rotational directions of the vorticities formed at the same position are reversed compared with those in the fast/slow configuration, which induces an inward air jet to impact on the gas bubble from the outside. In addition, the mixedness, average vorticity, and the absolute value of circulation all increase as the Atwood number decreases. Nevertheless, regardless of At > 0 or At < 0, the effective volume of the gas bubble basically decreases when the Atwood number decreases. Hence, on the whole, the Atwood number has a nonmonotonic influence on the evolution of effective volume of gas bubble, mixedness, average vorticity, and circulation simultaneously.

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“…Through steady and unsteady simulations of the centrifugal fan based on computational fluid dynamics (CFD), the internal flow field of the centrifugal fan has attracted a large number of researchers [32][33][34][35][36][37][38][39][40][41][42]. The discrete format at steady calculations is SIMPLE; SIMPLE is also adopted at the unsteady simulations, and the second-order format is carried out in the steady and unsteady simulations.…”

Section: Numerical Verificationmentioning

confidence: 99%

Unsteady Characteristics of Forward Multi-Wing Centrifugal Fan at Low Flow Rate

Lun

Ye²,

Lin³

et al. 2019

Processes

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The unsteady flow characteristics of a forward multi-wing centrifugal fan under a low flow rate are studied using the computational fluid dynamics (CFD) method. This paper emphasizes the eddy current distribution in terms of the Q criterion method, as well as pressure fluctuation, frequency spectrum, and kinetic energy spectrum analysis of internal monitoring points in a forward multi-wing centrifugal fan. The numerical results show that abnormal eddies mainly appear at the volute outlet and near the volute tongue, boundary layer separation occurs near the suction surface of the blade, and shedding eddies appear at the trailing edge of the blade with the time evolution. The unsteady flow characteristics of a forward multi-wing centrifugal fan at a small flow rate provide significant physical insight into understanding the internal flow law.

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Numerical investigation of shock-SF6 bubble interaction with different mach numbers

Cited by 20 publications

References 23 publications

Flame evolution in shock-accelerated flow under different reactive gas mixture gradients

Flame evolution in shock-accelerated flow under different reactive gas mixture gradients

Numerical investigation of planar shock wave impinging on spherical gas bubble with different densities

Unsteady Characteristics of Forward Multi-Wing Centrifugal Fan at Low Flow Rate

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