Influence of Periodicity on Simulations of a Round Supersonic Combustor Using Hybrid RANS/LES

Peterson, David M.; Bornhoft, Brett

doi:10.2514/6.2020-0875

Cited by 2 publications

(1 citation statement)

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“…In this situation, the limitations of Reynolds-averaged Navier-Stokes simulations (RANSs) and the excessive computational expense of a wall-resolved LES make the use of the hybrid turbulence methods a compromise [8]. Some prior work in applying hybrid RANS/LES methods for simulations of high-fidelity supersonic turbulent combustion has been reported [9][10][11], wherein the boundary layers along with the vortex from the mixing layers were adequately resolved.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Very Large Eddy Simulation Method for Applications of Supersonic Turbulent Combustion

Yan

Cao

et al. 2023

Aerospace

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The very large eddy simulation (VLES) method was investigated for supersonic reacting flows in the present work. The advantages and characteristics of the VLES model and the widely used improved delayed detached eddy simulation (IDDES) method were revealed through a supersonic ramped-cavity cold flow. Compared to the IDDES model, the VLES model transformed from RANS mode to LES mode faster, resulting in a smaller gray region caused by the mode transition. However, the original volume-averaging truncation length scale could lead to poor predictions of the velocity profiles and wall pressure distribution. By introducing a hybrid truncation length scale combining the maximum grid length and the shear layer adaptive (SLA) length with different coefficients, the accuracy of the VLES method was significantly improved, and the issue of the low shear layer position was solved. Moreover, owing to the resolution control function, the VLES method could adaptively model more turbulent kinetic energy and maintain a good accuracy in a coarser mesh. Finally, the modified VLES method was applied in conjunction with a hybrid combustion model constructed by the partially stirred reactor (PaSR) model and the Ingenito supersonic combustion model (ISCM) in simulations of the supersonic flame in the DLR scramjet combustor. After introducing the correction of the molecular collision frequency by the ISCM, the results obtained by the hybrid combustion model were more consistent with the experimental results, especially for the time-averaging temperature profile in the ignition zone.

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