Studies of shock/turbulent shear layer interaction using Large-Eddy Simulation

Génin, Franklin; Menon, Suresh

doi:10.1016/j.compfluid.2009.12.008

Cited by 137 publications

(50 citation statements)

References 48 publications

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“…A 4 th order Runge-Kutta scheme is used to solve the solid phase governing equations. Detailed validation of this simulation strategy and numerical approach for shock-turbulence interaction [10], blast waves [1,5] and detonations [11] has been reported elsewhere.…”

Section: Methodsmentioning

confidence: 99%

Simulations of heterogeneous detonations and post-detonation turbulent mixing and afterburning

Gottiparthi¹,

Menon²

2012

AIP Conference Proceedings

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Abstract. We conduct three-dimensional numerical simulations of the propagation of blast waves resulting from detonation of a nitromethane charge of radius 5.9 cm loaded with aluminum particles and analyze the afterburn process as well as the generation of multiple scales of mixing in the post detonation flow field. In the current study, the particle combustion is observed to be dependent on particle dispersal and mixing of gases in the flow where particle dispersal spreads aluminum within the flow and mixing provides the necessary oxidizer. Thus, 5 μm aluminum particles are burnt more effectively in comparison to 10 μm particles for a fixed initial mass of particles. Also, for a fixed initial particle size, increase in the initial mass of aluminum particles resulted in greater mixing.

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Section: Methodsmentioning

confidence: 99%

Simulations of heterogeneous detonations and post-detonation turbulent mixing and afterburning

Gottiparthi¹,

Menon²

2012

AIP Conference Proceedings

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“…The penetration depth of fuel stream is confirmed to be lower and the unburnt fuel stream spreads longer in the downstream for the elliptic combustor cases than the round cases. The weaker shock waves intersect with the unburnt fuel stream, which is helpful for local fuel mixing through strengthening vortex generation [96,97]. The coherent fire plume interfaces in the expander section show obvious two-layer flow structures, i.e.…”

Section: A Comparison Of Aerodynamic Fieldsmentioning

confidence: 99%

A comparative study of elliptical and round scramjet combustors by Improved Delayed Detached Eddy Simulation

Yao

Yuan

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

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To explore the combustion performance of non-rectangular type supersonic combustors, the flow and combustion characteristics in round and round-to-elliptic shape-transition (RdEST) supersonic combustors under the same configurations of flight Mach number and fuel equivalence ratio were compared based on modeling results. The fuel equivalence ratio is maintained the same as 0.8, while two inlet Mach numbers of 2.5 and 3.0 both corresponding to a real flight Mach number of 6.5 are tested. To alleviate the strict requirements on wall-normal and -parallel grid spacing, Improved Delayed Detached Eddy Simulation (IDDES) is employed in this study to enable an automatic choice of RANS or LES mode depending on the local boundary layer thickness and turbulent viscosity. To reduce the computational cost of stiff kerosene oxidation chemistry, a total of four versions of skeletal mechanisms (respectively 48s/197r, 39s/153r, 28s/92r and current 19s/54r) have been developed based on the detailed 2815s/8217r Dagaut mechanism by using a highly efficient and reliable directed relation graph with error propagation and sensitivity analysis (DRGEPSA) method together with manual path analysis. Although the mechanism size has been significantly reduced, key kinetic properties such as adiabatic flame temperature, heat release rate, ignition delay and laminar flame speed all agree well with the original detailed mechanism. The static pressure along streamwise direction is compared with the measurement to validate the modeling results. Two key aspects are well predicted, i.e. the pressure ratio and the initial pressure rise location, indicating that the flame anchoring location and the distribution of wave structures inside the combustor are close to the actual situation. Then the aerodynamic fields are analyzed for the round and elliptic combustors to compare their flow, mixing and combustion related flow structures. The three-dimensional wave structures inside the elliptic combustor are firstly shown to reveal the influence of nonaxisymmetric cross-section on the shock train and Mach field. Especially the time evolution of the flame region is analyzed, and dominant flame modes are extracted by the aid of proper orthogonal decomposition (POD) method.

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“…The values at the cell interfaces are computed using MUSCL reconstruction with Monotonized Central limiter. Both the Eulerian dispersed phase and the gas-phase governing equations are integrated using a predictor-corrector time integration approach [19]. The overall scheme is second order accurate in space and time.…”

Section: Governing Equations and Numerical Approachmentioning

confidence: 99%

“…In the current two-phase model, the gas-phase is always computed using an Eulerian approach by solving the threedimensional Navier-Stokes equations for compressible, unsteady, reactive, multiphase flows [5,12,19]. For the particle phase, we employ both the EL [12,13,20] and the EE [10,17,18] methods.…”

Section: Governing Equations and Numerical Approachmentioning

confidence: 99%

“…The numerical scheme used here is the well validated MUSCL reconstruction with Monotonized Central limiter [22,19], Harten-Lax-van Leer Riemann solver with contact (HLLC) to compute the gas-phase fluxes. Specifically, HLLC is used here since this Riemann solver provides contact surface required to evaluate the interface velocity [22].…”

Section: Governing Equations and Numerical Approachmentioning

confidence: 99%

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Turbulent mixing and afterburn in post-detonation flow with dense particle clouds

Gottiparthi¹,

Menon²

2017

AIP Conference Proceedings

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Abstract. Augmentation of the impact of an explosive is routinely achieved by packing metal particles in the explosive charge. When detonated, the particles in the charge are ejected and dispersed. The ejecta influences the post-detonation combustion processes that bolster the blast wave and determines the total impact of the explosive. While the classical Eulerian-Lagrangian (EL) methods can accurately handle the post-detonation mixing zone in the dilute regime, the Eulerian-Eulerian (EE) method is preferred for the initial dense clustering. Here, we summarize the results obtained using both EL and EE methods as well as demonstrate a new hybrid EE-EL approach. The EL method, which is also developed to handle both dense and dilute flows using the discrete equation method, is used initially to study the dispersion of a relatively dense particle shell by blast waves. The results show distinct clustering of particles that later leads to the formation of jet-like structures as seen in experiments. Then, the hybrid EE-EL method is used to study the dispersion of dense clouds from explosives packed with aluminum (reactive) or steel (inert) particles. A transitioning criterion is used to smoothly transfer the initially dense Eulerian mass to Lagrangian particles when dilute. Results are presented to demonstrate that the approach is computationally efficient and accurate for certain ranges of particle sizes and loading. It is shown that mixing between the ambient and post-detonation products can be enhanced when particles are present in the flow. Furthermore, the afterburn of aluminum particles increases in the average gas-phase temperature by 100 K -200 K when compared to a case with non-reacting particles. More studies are still needed to establish a robust strategy for wider applications.

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Studies of shock/turbulent shear layer interaction using Large-Eddy Simulation

Cited by 137 publications

References 48 publications

Simulations of heterogeneous detonations and post-detonation turbulent mixing and afterburning

Simulations of heterogeneous detonations and post-detonation turbulent mixing and afterburning

A comparative study of elliptical and round scramjet combustors by Improved Delayed Detached Eddy Simulation

Turbulent mixing and afterburn in post-detonation flow with dense particle clouds

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