A parallel adaptive method for simulating shock-induced combustion with detailed chemical kinetics in complex domains

Deiterding, Ralf

doi:10.1016/j.compstruc.2008.11.007

Cited by 125 publications

(81 citation statements)

References 47 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…A straight channel in Fig.1(a) is used in Section 3 while expanding channels in Fig.1(b) are studied in Section 4. The level-set technique [29] with ghost fluid approach [16] is employed for the expanding upper boundary in Fig.1(b). Reflecting boundary with slip wall conditions are used on the upper and lower wall, and the inflow of the hot jet is embedded within the lower domain boundary.…”

Section: Computational Setupmentioning

confidence: 99%

Adaptive simulations of viscous detonations initiated by a hot jet using a high-order hybrid WENO–CD scheme

Cai

Deiterding

Liang

et al. 2017

Proceedings of the Combustion Institute

Self Cite

View full text Add to dashboard Cite

Abstract:In the present work a sixth-order hybrid WENO-Centered Difference (CD) scheme with an adaptive mesh refinement method is employed to investigate gaseous detonation by injecting a hot jet into a hydrogen-oxygen combustible mixture flowing at supersonic speed. Two-dimensional reactive NavierStokes (NS) equations with one-step two-species chemistry model are solved numerically. The comparison between viscous and inviscid detonation structures shows that due to the absence of both the physical viscosity in Euler equations and minimization of numerical dissipation in the hybrid WENO-CD scheme, very small-scale vortices can be observed behind the detonation front. The diffusion effect in the NS equations suppresses the small-scale vortices, but it has negligible influence on the large-scale vortices generated by Richtmyer-Meshkov (RM) instability and those along the highly unstable shear layers induced by Kelvin-Helmholtz (KH) instability. When studying the same setup in an expanding channel and beyond the point of detonation initiation, it is found that because of the diffusion effect of detached shear layers, any unburned jet flow is consumed quickly and then additional energy is released periodically. Because of the formation of multiple secondary triple points and subsequent shear layers after the shutdown of the hot jet, a highly turbulent flow is produced behind the detonation front. Rather than the commonly known RM instability, the large-scale vortices involved in the highly unstable shear layers dominate the formation of the turbulent flow and the rapid turbulent mixing between the unburned jet flow and burned product. It is found that the size of unburned jets and vortices due to KH instability is growing for larger expansion angles. The further generated turbulent flow resulting from larger sized vortices, significantly enhances the mixing rate behind the Mach stem, leading to rapid consumption of the unburned reactants. Therefore, detonations propagate faster in channels with larger expansion angle and higher expansion ratio.

show abstract

Section: Computational Setupmentioning

confidence: 99%

Adaptive simulations of viscous detonations initiated by a hot jet using a high-order hybrid WENO–CD scheme

Cai

Deiterding

Liang

et al. 2017

Proceedings of the Combustion Institute

Self Cite

View full text Add to dashboard Cite

show abstract

“…The last step involves the interpolation and mirroring of ρ, u, and p across the sphere boundary and the modification of the normal velocity in the immersed boundary cells to (2v · n − u · n)n, with n = ∇ϕ/|∇ϕ|, cf. Deiterding (2009). The benefit of this immersed-boundary, aka 'ghost fluid' method (Fedkiw et al 1999) is the natural incorporation of moving bodies.…”

Section: Computational Modellingmentioning

confidence: 99%

“…Numerical approach As in Laurence & Deiterding (2011), we employ the Cartesian fluid solver framework AMROC (Deiterding 2005b;Deiterding et al 2005Deiterding et al , 2007Deiterding 2009Deiterding , 2011aZiegler et al 2011) to simulate numerically the fluid-structure interaction of the free-flying spherical bodies. The equations solved to model the inviscid compressible fluid are the Euler equations in conservation-law form…”

Section: Computational Modellingmentioning

confidence: 99%

Dynamical separation of spherical bodies in supersonic flow

2012

View full text Add to dashboard Cite

An experimental and computational investigation of the unsteady separation behaviour of two spheres in Mach-4 flow is carried out. The spherical bodies, initially contiguous, are released with negligible relative velocity and thereafter fly freely according to the aerodynamic forces experienced. In experiments performed in a supersonic Ludwieg tube, nylon spheres are initially suspended in the test section by weak threads which are detached by the arrival of the flow. The subsequent sphere motions and unsteady flow structures are recorded using high-speed (13 kHz) focused shadowgraphy. The qualitative separation behaviour and the final lateral velocity of the smaller sphere are found to vary strongly with both the radius ratio and the initial alignment angle of the two spheres. More disparate radii and initial configurations in which the smaller sphere centre lies downstream of the larger sphere centre each increases the tendency for the smaller sphere to be entrained within the flow region bounded by the bow shock of the larger body, rather than expelled from this region. At a critical angle for a given radius ratio (or a critical radius ratio for a given angle), transition from entrainment to expulsion occurs; at this critical value, the final lateral velocity is close to maximum due to the same 'surfing' effect noted by Laurence & Deiterding (J. Fluid Mech., vol. 676, 2011, pp. 396-431) at hypersonic Mach numbers. A visualization-based tracking algorithm is used to provide quantitative comparisons between the experiments and high-resolution inviscid numerical simulations, with generally favourable agreement.

show abstract

“…Mirrored values are constructed by calculating spatially interpolated values in the point � = + 2 from neighboring interior cells. We employ a dimension-wise linear interpolation for this operation, but it has to be emphasized that directly near the boundary the number of interpolants needs to be decreased to ensure the monotonicity of the numerical solution (Deiterding, 2009). This property is essential in simulating hyperbolic problems with discontinuities.…”

Section: Embedding Of Moving Boundaries Into Cartesian Schemesmentioning

confidence: 99%

Shock-driven fluid-structure interaction for civil design

Wood¹,

Deiterding²

2011

Self Cite

View full text Add to dashboard Cite

The multiphysics fluid-structure interaction simulation of shock-loaded structures requires the dynamic coupling of a shock-capturing flow solver to a solid mechanics solver for large deformations. The Virtual Test Facility combines a Cartesian embedded boundary approach with dynamic mesh adaptation in a generic software framework of flow solvers using hydrodynamic finite volume upwind schemes that are coupled to various explicit finite element solid dynamics solvers (Deiterding et al., 2006). This paper gives a brief overview of the computational approach and presents first simulations that utilize the general purpose solid dynamics code DYNA3D for complex 3D structures of interest in civil engineering. Results from simulations of a reinforced column, highway bridge, multistory building, and nuclear reactor building are presented.

show abstract

A parallel adaptive method for simulating shock-induced combustion with detailed chemical kinetics in complex domains

Cited by 125 publications

References 47 publications

Adaptive simulations of viscous detonations initiated by a hot jet using a high-order hybrid WENO–CD scheme

Adaptive simulations of viscous detonations initiated by a hot jet using a high-order hybrid WENO–CD scheme

Dynamical separation of spherical bodies in supersonic flow

Shock-driven fluid-structure interaction for civil design

Contact Info

Product

Resources

About