Numerical study on the relation between hydrodynamic fluctuations and noise in hot jets at high Reynolds number

Biolchini, Romain; Bailly, Christophe; Boussuge, Jean‐François; Fernando, Rasika

doi:10.2514/6.2016-3048

Cited by 3 publications

(4 citation statements)

References 9 publications

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“…Bogey et al [24] introduced vorticity perturbations (vortex rings) in the nozzle laminar boundary layer in order to generate highly disturbed boundary layers that feed the initial stages of the mixing layer development with enough perturbations to allow a fully turbulent behaviour. The same technique is used by Biolchini et al [32]. Bühler et al [33] used successfully the Synthetic Eddy Method [28] for DNS simulations at moderate Reynolds number.…”

Section: Introductionmentioning

confidence: 99%

On the generation of turbulent inflow for hybrid RANS/LES jet flow simulations

Gand¹,

Huet²

2021

Computers & Fluids

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The present work is devoted to the assessment of a low-noise turbulence generation methodology used to produce boundary layer with three-dimensional resolved turbulence at the exit of a jet nozzle to reproduce experimental conditions. The method relies on the use of roughness elements introduced in the computational domain with Immersed Boundary Conditions and ZDES mode 3 (Wall Modelled LES branch of ZDES). The simulation of a round jet at M=0.9 and Reynold number 10 6 with turbulence generation is compared to a simulation with no resolved turbulence in the nozzle boundary layer using ZDES mode 2. The behaviour of the boundary layer downstream of the roughness elements inside the nozzle is scrutinized using two grids. The turbulence generation method combined with ZDES mode 3 produces satisfying levels of resolved turbulence at the nozzle exit. The early stages of the shear layer development are modified by the ZDES mode 3 simulations providing an initially turbulent boundary layer. On the other hand, the ZDES mode 2 simulations, with a turbulent mean exit velocity profile but no resolved turbulence, display a short area of strong shear layer instabilities leading to the quick development of threedimensional turbulence in the mixing layer. The present results give insights on the level of turbulent modelling of the nozzle boundary layer needed depending on the purposes of the jet flow simulations considered.

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Section: Introductionmentioning

confidence: 99%

On the generation of turbulent inflow for hybrid RANS/LES jet flow simulations

Gand¹,

Huet²

2021

Computers & Fluids

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“…The flux reconstruction for conforming grids presented in this section has been successfully applied to massively parallel aeroacoustic simulations of jet flows at high Reynolds numbers …”

Section: Flux Reconstruction Technique For Conforming Gridsmentioning

confidence: 99%

“…Therefore, in a previous study, a technique of flux reconstruction at the interface of conforming grids has been developed. Based on the application of noncentered spatial schemes at the block interface and the use of ghost cells, the technique allowed us to successfully perform massively parallel aerodynamic and aeroacoustic computations of jet flows …”

Section: Introductionmentioning

confidence: 99%

“…Based on the application of noncentered spatial schemes at the block interface and the use of ghost cells, the technique allowed us to successfully perform massively parallel aerodynamic and aeroacoustic computations of jet flows. [14][15][16][17] In the present study, a flux reconstruction technique for the interface of nonconforming grids is proposed. The technique, derived from the method developed for conforming grids, 12 is based on the application of noncentered schemes at the grid interface.…”

Section: Introductionmentioning

confidence: 99%

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A technique of flux reconstruction at the interfaces of nonconforming grids for aeroacoustic simulations

Bras

Deniau

Bogey

2019

Numerical Methods in Fluids

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Summary A flux reconstruction technique is presented to perform aeroacoustic computations using implicit high‐order spatial schemes on multiblock structured grids with nonconforming interfaces. The use of such grids, with mesh spacing discontinuities across the block interfaces, eases local mesh refinements, simplifies the mesh generation process, and thus facilitates the computation of turbulent flows. In this work, the spatial discretization consists of sixth‐order finite‐volume implicit schemes with low‐dispersion and low‐dissipation properties. The flux reconstruction is based on the combination of noncentered schemes with local interpolations to define ghost cells and compute flux values at the grid interfaces. The flow variables in the ghost cells are calculated from the flow field in the grid cells using a meshless interpolation with radial basis functions. In this study, the flux reconstruction is applied to both plane and curved nonconforming interfaces. The performance of the method is first evaluated by performing two‐dimensional simulations of the propagation of an acoustic pulse and of the convection of a vortex on Cartesian and wavy grids. No significant spurious noise is produced at the grid interfaces. The applicability of the flux reconstruction to a three‐dimensional computation is then demonstrated by simulating a jet at a Mach number of 0.9 and a diameter‐based Reynolds number of 4×105 on a Cartesian grid. The nonconforming grid interface located downstream of the jet potential core does not appreciably affect the flow development and the jet sound field, while reducing the number of mesh points by a factor of approximately two.

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