Hybrid Reynolds-Averaged and Large-Eddy Simulations of a Supersonic Cavity Flameholder

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

doi:10.2514/6.2013-2483

Cited by 22 publications

(16 citation statements)

References 24 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%

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%

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

Baurle

2017

AIAA Journal

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“…Pressure data in the immediate vicinity of the cavity indicate even smaller changes, suggesting that the particular region of interest of the flowfield is not appreciably affected by the seeding method used. This result is confirmed by recent CFD analysis 27,28 .…”

Section: Resultssupporting

confidence: 93%

Velocimetry Measurements of a Scramjet Cavity Flameholder with Inlet Distortion

Kirik

Goyne

Peltier

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Particle image velocimetry (PIV) measurements were made in the center plane of a scramjet cavity flameholder to analyze the effects of simulated inlet flow distortion in the direct-connect test environment. Mach 3 non-reacting tests examined the effects of a fullspan wedge configured such that an oblique shock impinged upon locations in and upstream of the cavity flameholder, including cases with wall-normal air injection upstream of the cavity to simulate fuel injection. Addition of flow distortion altered the size and shape of the primary recirculation region within the cavity by deflecting the bounding shear layer: the recirculation region was compressed by shock impingement upstream of the cavity, while shock impingement on the cavity itself expanded it. Air injection upstream of the cavity thickened the shear layer and produced a stronger effect on velocity direction than magnitude, preventing the formation of a large-scale recirculation region in two of the three shock locations studied. Flow distortion and air injection both increased flow unsteadiness, with the greatest increases in root-mean-square velocity occurring in the shear layer and above the cavity closeout ramp. At the most-upstream shock impingement location examined, flow patterns indicated fuel injected through the ramp at the center plane may not be recirculated within the cavity, providing a potential mechanism for a previouslyobserved lack of flameholding in this configuration. Additionally, results suggest the formation of spanwise secondary flow patterns that may account for flow nonuniformities observed in prior studies. This work presents the first PIV characterization of a scramjet cavity flameholder under distorted-flow conditions and with simulated upstream fuel injection.

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“…Pressure data in the immediate vicinity of the cavity indicate even smaller changes, suggesting that the particular region of interest of the flowfield is not appreciably affected by the seeding method used. This conclusion was confirmed by recent computational fluid dynamics (CFD) analysis [29].…”

Section: Resultssupporting

confidence: 84%

Velocimetry Measurements of a Scramjet Cavity Flameholder with Inlet Distortion

Kirik¹,

Goyne²,

Peltier³

et al. 2014

Journal of Propulsion and Power

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Particle image velocimetry measurements were made along the center plane of a scramjet cavity flameholder to analyze simulated inlet flow distortion in the direct-connect test environment. Mach 3 nonreacting tests examined an oblique shock impinging upon locations in-and upstream of the cavity, including cases with wall-normal air injection upstream of the cavity to simulate fuel injection. Addition of flow distortion altered the size and shape of the primary recirculation region within the cavity by deflecting the bounding shear layer: the recirculation region was compressed by shock impingement upstream of the cavity, and shock impingement on the cavity itself expanded it. Air injection upstream of the cavity thickened the shear layer and produced a stronger effect on velocity direction than magnitude, preventing the formation of a large-scale recirculation region in two of the three shock locations studied. Flow distortion and upstream air injection both increased flow unsteadiness, with the greatest increases occurring in the shear layer and above the cavity closeout ramp. Additionally, results suggest the formation of spanwise secondary flow patterns that may account for flow nonuniformities observed in prior studies. This work presents the first velocimetry characterization of a scramjet cavity flameholder under distorted-flow conditions.

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Hybrid Reynolds-Averaged and Large-Eddy Simulations of a Supersonic Cavity Flameholder

Cited by 22 publications

References 24 publications

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

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

Velocimetry Measurements of a Scramjet Cavity Flameholder with Inlet Distortion

Velocimetry Measurements of a Scramjet Cavity Flameholder with Inlet Distortion

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