Numerical Investigation of a Supersonic Cavity Flameholder

Peterson, David M.; Hassan, Ezeldin A.; Tuttle, Steven G.; Hagenmaier, Mark A.; Carter, Campbell D.

doi:10.2514/6.2014-1158

Cited by 24 publications

(15 citation statements)

References 27 publications

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“…domain width that encompasses two full injection ports. This domain matches that used in previous improved delayed detached-eddy simulation studies [12,13] for this configuration. As mentioned previously, Peterson et al [12] included a comparison of results using this domain width with those obtained using the full facility width with side-wall effects.…”

Section: Computational Grid Descriptionsupporting

confidence: 53%

“…This allowed the consideration of only a fraction of the facility width, providing for a more efficient means to analyze the flowpath while retaining the salient flow features. This simplification has been justified to some extent through the research efforts of Peterson et al [12], where it was demonstrated that the inclusion of side walls had only a small effect on the computed cavity flow structure in the vicinity of the spanwise center plane. The smallest spanwise width allowed by the symmetry present in the geometry is a 0.25 in.…”

Section: Computational Grid Descriptionmentioning

confidence: 99%

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Hybrid Reynolds-Averaged/Large-Eddy Simulation of a Scramjet Cavity Flameholder

Baurle

2017

AIAA Journal

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.J055339Steady-state and scale-resolving simulations have been performed for flow in and around a model scramjet combustor flameholder. Experimental data available for this configuration include velocity statistics obtained from particle image velocimetry as well as a limited number of scalar measurements using laser-induced breakdown spectroscopy. Several turbulence models were used for the steady-state Reynolds-averaged simulations, which included both linear and nonlinear eddy viscosity models. The scale-resolving simulations used a hybrid Reynoldsaveraged/large-eddy simulation strategy that is designed to be a large-eddy simulation everywhere except in the inner portion (log layer and below) of the boundary layer. Hence, this formulation can be regarded as a wall-modeled largeeddy simulation. This effort was undertaken to not only assess the performance of the hybrid Reynolds-averaged/ large-eddy simulation modeling approach in a flowfield of interest to the scramjet research community but also to begin to understand how this capability can best be used to augment standard Reynolds-averaged simulations. The numerical errors were quantified for the steady-state simulations and at least qualitatively assessed for the scaleresolving simulations before making any claims of predictive accuracy relative to the measurements. The steady-state Reynolds-averaged results displayed a high degree of variability when comparing the flameholder fuel distributions obtained from each turbulence model. This prompted the consideration of applying the higher-fidelity scale-resolving simulations as a surrogate "truth" model to calibrate the Reynolds-averaged closures in a nonreacting setting before their use for the combusting simulations. In general, the Reynolds-averaged velocity profile predictions at the lowest fueling level matched the particle imaging measurements almost as well as was observed for the nonreacting condition. However, the velocity field predictions proved to be more sensitive to the flameholder fueling rate than was indicated in the measurements.

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Section: Computational Grid Descriptionsupporting

confidence: 53%

Section: Computational Grid Descriptionmentioning

confidence: 99%

Hybrid Reynolds-Averaged/Large-Eddy Simulation of a Scramjet Cavity Flameholder

Baurle

2017

AIAA Journal

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“…The WMLES formulation is the Improved Delayed Detached Eddy Simulation (IDDES) method, 26 in which a blending function for the length scale in the Spalart-Allmaras turbulence model is used to smoothly transition from RANS in near-wall boundary layers to low dissipation LES mode in regions of separated flow away from walls. The implementation in US3D has been used to study many compressible reacting flows using WMLES 19,20,21,22 and most notably in the same experimental setup considered in this work. 9 In these tests, the code showed a remarkable reproduction of the temperature map obtained through non-intrusive PLIF images, including the reconstruction of flow structures in the upstream separation zone that were not present in RANS simulations of the same flow.…”

Section: Cfd Methodologymentioning

confidence: 99%

Simulation of Laser-Induced-Plasma Ignition in a Hypersonic Crossflow

Gibbons

Gehre

Brieschenk

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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A numerical study of a laser-induced-plasma ignition system in a scramjet-like geometry is conducted. Simulations are based on experiments in which hydrogen is injected into hypersonic air-crossflow, compressed by a 9 • ramp from a freestream Mach number of 8 to below hydrogen autoignition conditions. Ignition of the jet is conducted using a laser pulse, modelled in the simulations as a small region of high temperature and pressure corresponding to the energy input measured in the experiments. To capture the highly unsteady nature of the fuel-air interface and its coupling with the dynamics of the expanding laser spark, Wall-Modelled Large Eddy Simulations are used to resolve the majority of turbulent motion. Detailed non-equilibrium thermochemistry models are included in the calculations. Simulations have revealed that the cloud of hydroxyl radicals detected in the experiments is created by the blast wave which forms from the expanding plasma kernel merging with the jet's bow shock. This event raises the temperature and pressure in the upstream mixing layer and spontaneous ignition of the fuel is observed. Shortly after this ignition, combustion ceases due to hostile conditions for flame anchoring. Downstream of the jet, the simulations suggest that the plasma kernel remains can initiate some radical formation in the wake region, but no stable flame forms due to nominally low pressures in the experimental condition studied.

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“…The geometry of the cavity (see Fig. 14) is taken similar to that presented in [78]. The span-wise dimension and inflow boundary layer thickness are taken same as the step height (unity) of the cavity.…”

Section: Three Dimensional Supersonic Turbulent Flow With a Ramped Camentioning

confidence: 99%

Explicit discontinuous spectral element method with entropy generation based artificial viscosity for shocked viscous flows

Chaudhuri

Jacobs

Don

et al. 2017

Journal of Computational Physics

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A spatio-temporal adaptive artificial viscosity (AV) based shock-capturing scheme is proposed for the solution of both inviscid and viscous compressible flows using a high-order parallel Discontinuous Spectral Element Method (DSEM). The artificial viscosity and artificial thermal conduction coefficients are proportional to the viscous and thermal entropy generating terms, respectively, in the viscous entropy conservation law. The magnitude of AV is limited based on the explicit stable CFL criterion, so that the stable artificial viscous time step size is greater than the convective stable time step size. To further ensure the stability of this explicit approach, an adaptive variable order exponential filter is applied, if necessary, in elements where the AV has been limited. In viscous flow computations a modified Jameson's sensor (Ducros et al., JCP 152 (2)) limits the AV to small values in viscous shear regions, so as to maintain a high-order resolution in smooth regions and an essentially non-oscillatory behavior near sharp gradients/shocks regions. We have performed a systematic and extensive validation of the algorithm with one-dimensional problems (inviscid moving shock and viscous shock-structure interaction), two-dimensional problems (inviscid steady and unsteady shocked flows and viscous shock-boundary layer interaction), and a three-dimensional supersonic turbulent flow over a ramped cavity. These examples demonstrate that the explicit DSEM scheme with adaptive artificial

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Numerical Investigation of a Supersonic Cavity Flameholder

Cited by 24 publications

References 27 publications

Hybrid Reynolds-Averaged/Large-Eddy Simulation of a Scramjet Cavity Flameholder

Hybrid Reynolds-Averaged/Large-Eddy Simulation of a Scramjet Cavity Flameholder

Simulation of Laser-Induced-Plasma Ignition in a Hypersonic Crossflow

Explicit discontinuous spectral element method with entropy generation based artificial viscosity for shocked viscous flows

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