Multi-Wall Recycling / Rescaling Method for Inflow Turbulence Generation

Boles, John A.; Choi, Jung Il; Edwards, Jack R.; Baurle, Robert A.

doi:10.2514/6.2010-1099

Cited by 21 publications

(13 citation statements)

References 15 publications

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“…Multi-wall recycling/rescaling III.B.1. Extension of RR methods to multiple walls Following Boles et al, 13 we assume that the boundary layers evolving along each wall is independent and the rescaling is applied separately along each wall. Any turbulent quantity φ is then defined as φ = nwalls n=1 W n .φ n , where φ n is the quantity rescaled along the n th wall and injected at the inlet, and (W n ) is a weighting function based on the inverse squared wall distance (d) to ensure the coupling and is given by:…”

Section: Iiia Recycling/rescaling On a Single Wallmentioning

confidence: 99%

“…Regarding the mean flow at the recycling plane, we assume that the undisturbed flow exhibits a quadrant symmetry in the transverse plane, and a time and quadrant averaging procedure is used to force the mean flow to be symmetric (see also 13,3 ).…”

Section: Iiia Recycling/rescaling On a Single Wallmentioning

confidence: 99%

“…Wang et al 9 have used a similar approach based on a digital random filtering methods to generate turbulent fluctuations at the inflow for an oblique SWTBLI in the presence of side walls. Morgan et al 2 have carried out a LES simulation of a normal shock-train in a rectangular duct by extending the recycling/rescaling approach of Lund et al 10 to the compressible regime 11,12 and accounting for the development of the boundary layer in the presence of multiple walls by following the approach developed by Boles et al 13 We remark that synthetic turbulence techniques require the knowledge of Reynolds stress distributions and/or characteristics of the coherent structures that a priori are not known for near-corner flows.…”

Section: Introductionmentioning

confidence: 99%

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Turbulent inflow generation in square duct at supersonic Mach number

Roussel

Alizard

Grasso

2015

22nd AIAA Computational Fluid Dynamics Conference

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The present work focuses on the turbulent inflow generation in a rectangular duct by extending the recycling/rescaling technique to multiple walls, and investigates the sensitivity of the solution with respect to inflow conditions. LES simulations of the flow a in rectangular duct at M = 1.61 have been carried out for two different mean inflow conditions. The results show that at a distance of o(10) boundary layer thicknesses from the inlet, the flow relaxes to a state that is weakly affected by the boundary condition at the inlet. A LES simulation of shock-train boundary layer interaction occurring in the same rectangular duct geometry and at the same Mach number condition has also been carried out. The results have been compared with the reference experiment of Carroll & Dutton 1 and with the LES simulation of Morgan et al., 2, 3 and confirm the weak dependence of the solution upon the mean inflow initial condition. Nomenclature f = blending function for recycling/rescaling technique W = inner/outer boundary layer blending function for recycling/rescaling technique, and inverse squared wall distance weighting function δ = boundary layer thickness δ * = boundary layer displacement thickness θ = boundary layer momentum thickness u τ = friction velocity (.) w = value at the wall (.) + = non-dimensional quantity in wall unit (.) in = value at the inflow (.) rec = value at the recycling plane (.) vd = van-Driest-transformed quantitȳ (.) = time averaged value (.) = Favre averaged value (.) = fluctuation quantity

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Section: Iiia Recycling/rescaling On a Single Wallmentioning

confidence: 99%

Section: Iiia Recycling/rescaling On a Single Wallmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Turbulent inflow generation in square duct at supersonic Mach number

Roussel

Alizard

Grasso

2015

22nd AIAA Computational Fluid Dynamics Conference

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“…Neither of these observed effects were included in the present simulations. Also, while it is possible to force the generation of realistic turbulent structures within the inflow channel boundary layers using recycling / rescaling methods [15], it was found that the boundary layer was too thin and the mesh too coarse to sustain such structures. As such, no such forcing was applied for the LES/RANS simulations.…”

Section: Calculation Detailsmentioning

confidence: 99%

Large-Eddy/Reynolds-averaged Navier-Stokes Simulation of a Dual-Mode Scramjet Combustor

Fulton

Edwards

Hassan

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Numerical simulations of reacting and non-reacting flows within a scramjet combustor configuration experimentally mapped at the University of Virginia's Scramjet Combustion Facility (operating with Configuration "A") are described in this paper. Reynolds-Averaged Navier-Stokes (RANS) and hybrid Large Eddy Simulation / Reynolds-Averaged Navier-Stokes (LES / RANS) methods are utilized, with the intent of comparing essentially 'blind' predictions with results from non-intrusive flow-field measurement methods including coherent anti-Stokes Raman spectroscopy (CARS), hydroxyl radical planar laser-induced fluorescence (OH-PLIF), stereoscopic particle image velocimetry (SPIV), wavelength modulation spectroscopy (WMS), and focusing Schlieren. NC State's REACTMB solver was used both for RANS and LES / RANS, along with a 9-species, 19reaction H 2-air kinetics mechanism by Jachimowski. Inviscid fluxes were evaluated using Edwards' LDFSS flux-splitting scheme, and the Menter BSL turbulence model was utilized in both full-domain RANS simulations and as the unsteady RANS portion of the LES / RANS closure. Simulations were executed and compared with experiment at two equivalence ratios, Ф = 0.17 and Ф = 0.34. Results show that the Ф = 0.17 flame is hotter near the injector while the Ф = 0.34 flame is displaced further downstream in the combustor, though it is still anchored to the injector. Reactant mixing was predicted to be much better at the lower equivalence ratio. The LES / RANS model appears to predict lower overall heat release compared to RANS (at least for Ф = 0.17), and its capability to capture the direct effects of larger turbulent eddies leads to much better predictions of reactant mixing and combustion in the flame stabilization region downstream of the fuel injector. Numerical results from the LES/RANS model also show very good agreement with OH-PLIF and SPIV measurements. An un-damped long-wave oscillation of the pre-combustion shock train, which caused convergence problems in some RANS simulations, was also captured in LES / RANS simulations, which were able to accommodate its effects accurately.

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“…The subgrid model used for the LES is an algebraic form from Lenormand, et al [26]: The inflow boundary layer for the LES/RANS simulations is sustained through a recycling / rescaling technique, applied to the fluctuating fields. [2,3] For the calculations performed in the complete 3D combustor, periodic flow cannot be assumed, and a more general recycling / rescaling procedure [27], valid for flows affected by multiple walls, is used. As of this writing, the chemical source terms are evaluated using filtered mean values.…”

Section: B Turbulence Modelmentioning

confidence: 99%

LES/RANS Simulation of a Supersonic Reacting Wall Jet

Edwards

Boles

Baurle

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This work presents results from large-eddy / Reynolds-averaged Navier-Stokes (LES/RANS) simulations of the well-known Burrows-Kurkov supersonic reacting wall-jet experiment. Generally good agreement with experimental mole fraction, stagnation temperature, and Pitot pressure profiles is obtained for non-reactive mixing of the hydrogen jet with a non-vitiated air stream. A lifted flame, stabilized between 10 and 22 cm downstream of the hydrogen jet, is formed for hydrogen injected into a vitiated air stream. Flame stabilization occurs closer to the hydrogen injection location when a threedimensional combustor geometry (with boundary layer development resolved on all walls) is considered. Volumetric expansion of the reactive shear layer is accompanied by the formation of large eddies which interact strongly with the reaction zone. Time averaged predictions of the reaction zone structure show an under-prediction of the peak water concentration and stagnation temperature, relative to experimental data and to results from a Reynolds-averaged Navier-Stokes calculation. If the experimental data can be considered as being accurate, this result indicates that the present LES/RANS method does not correctly capture the cascade of turbulence scales that should be resolvable on the present mesh. Instead, energy is concentrated in the very largest scales, which provide an overmixing effect that excessively cools and strains the flame. Predictions improve with the use of a low-dissipation version of the baseline piecewise parabolic advection scheme, which captures the formation of smaller-scale structures superimposed on larger structures of the order of the shear-layer width.ombustion processes occurring in high-speed propulsion devices can be strongly impacted by finite-rate chemistry and turbulence / chemistry interactions, as well as large-scale unsteady behavior caused by intermittent ignition events, shock / boundary layer interactions, and vortex dynamics. The state of the practice in high-speed engine component simulations [1] solves the Reynolds-Averaged Navier-Stokes (RANS) equations, expanded to include separate equations for species transport. Closure is usually accomplished through two-equation turbulence models in conjunction with Boussinesq and gradient-diffusion assumptions. Chemical reaction source terms are usually formulated using the law of mass action, and the effects of turbulence fluctuations on reaction rates are either completely ignored or modeled via eddy break up and/or assumed PDF methods. This standard model been used successfully in the design of scramjet-powered vehicles such as NASA's Hyper-X, the University of Queensland's HyShot program, and the U.S. Air Force's Scramjet Engine Demonstrator, but the ability of the model to handle highly transient physics of the types mentioned above is questionable at best. C Recent work [2][3][4][5] has focused on the development of a class of hybrid large-eddy simulation / Reynoldsaveraged Navier Stokes (LES/RANS) strategies specially designed for strongly-i...

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Multi-Wall Recycling / Rescaling Method for Inflow Turbulence Generation

Cited by 21 publications

References 15 publications

Turbulent inflow generation in square duct at supersonic Mach number

Turbulent inflow generation in square duct at supersonic Mach number

Large-Eddy/Reynolds-averaged Navier-Stokes Simulation of a Dual-Mode Scramjet Combustor

LES/RANS Simulation of a Supersonic Reacting Wall Jet

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