Downstream subsonic jet noise: link with vortical structures intruding into the jet core

Bogey, Christophe; Bailly, Christophe

doi:10.1016/s1631-0721(02)01499-7

Cited by 5 publications

(4 citation statements)

References 17 publications

(30 reference statements)

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“…Grinstein also focused on reactive jets and flame. Bogey et al [4,5] simulated 3D jets using LES, and Rembold et al [6] simulated 3D jets using RANS, LES, and DNS, principally in order to predict the noise emission. In these simulations, turbulence was of great interest for its impact on the noise generated.…”

Section: Introductionmentioning

confidence: 99%

Vortex method for simulation of a 3D round jet in a cross-stream

Pinon

Bratec

Huberson

et al. 2005

Journal of Turbulence

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In this paper, the three-dimensional (3D) flow of a jet in a crossflow was investigated. This is a numerical study based on a vortex particle method. In order to account for the lower length scales, a crude LES turbulence model was implemented together with a regridding procedure. The numerical simulation was done with an injection ratio R inj = W jet /U ∞ = 4.0. The code was run until an averaged steady state of the jet was reached. The resulting vortex structures were shown to be consistent with previously published analyses of the flow, from both experiments and numerical simulations. In particular, the onset of counter-rotating vortex pairs (CVP) was also investigated.

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Section: Introductionmentioning

confidence: 99%

Vortex method for simulation of a 3D round jet in a cross-stream

Pinon

Bratec

Huberson

et al. 2005

Journal of Turbulence

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“…The maximum acoustic level turns out to be 4 dB lower for the excited jet than for the free jet. Since the noise emitted at this particular angle is linked to the vortex pairing at the end of the potential core (Bogey and Bailly [6]), the present result suggests that the vortex pairing noise can be reduced by acting on the large-scale structure at the nozzle exit. At larger observer angles (θ > 60 • ), on the other hand, the acoustic levels of forced jet exceed slightly those of the natural jet.…”

Section: Resultsmentioning

confidence: 64%

“…Pour modéliser le bruit rayonné par le jet, nous avons considéré la solution intégrale (5) de l'équation de Lighthill (4) dans la région lointaine du domaine de calcul. Une expression de l'intensité acoustique est ainsi obtenue (6). L'évaluation du niveau sonore est effectuée pour des angle θ variant de 0 à 180 • par rapport à la direction de l'écoulement et pour une distance de 60R à partir de la sortie de la tuyère d'éjection (R est le rayon amont du jet).…”

Section: Version Française Abrégéeunclassified

“…On constate que le bruit des jets est prépondérant en aval et presente un maximum pour des angles d'observation θ compris entre 30 et 35 • . Ce bruit est lié à la dynamique et l'appariement tourbillonnaire des grosses structures turbulentes qui apparaissent dans la zone de transition (Bogey et Bailly [6]). Sur ces deux figures, il est clair que, pour des angles d'observation inférieurs à 60 • , les niveaux sonores du jet subsonique ont diminué nettement lorsqu'on excite sa couche de mélange amont en superposant une perturbation variqueuse harmonique et une perturbation alternée sous-harmonique.…”

Section: Version Française Abrégéeunclassified

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Estimation of aerodynamic noise generated by forced compressible round jets

Maidi

2006

Comptes Rendus. Mécanique

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An acoustic numerical code based on Ligthill's analogy is combined with large-eddy simulations techniques in order to evaluate the noise emitted by subsonic (M = 0.7) and supersonic (M = 1.4) round jets. We show first that, for centerline Mach number M = 0.9 and Reynolds number Re = 3.6 × 10 3 , acoustic intensities compare satisfactorily with experimental data of the literature in terms of levels and directivity. Afterwards, high Reynolds number (Re = 3.6 × 10 4 ) free and forced jets at Mach 0.7 and 1.4 are studied. Numerical results show that the jet noise intensity depends on the nature of the upstream mixing layer. Indeed, the subsonic jet is 4 dB quieter than the free jet when acting on this shear layer by superposing inlet varicose and flapping perturbations at preferred and first subharmonic frequency, respectively. The maximal acoustic level of the supersonic jet is, on the other hand, 3 dB lower than the free one with a flapping upstream perturbation at the second subharmonic. The results reported in this paper confirm previous works presented in the literature demonstrating that jet noise may be modified according to the inlet conditions.

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Sound Generated by an Unsteady Flow Field, Using a Hybrid Method

Mihăescu

Fuchs

2004

Modelling Fluid Flow

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Downstream subsonic jet noise: link with vortical structures intruding into the jet core

Cited by 5 publications

References 17 publications

Vortex method for simulation of a 3D round jet in a cross-stream

Vortex method for simulation of a 3D round jet in a cross-stream

Estimation of aerodynamic noise generated by forced compressible round jets

Sound Generated by an Unsteady Flow Field, Using a Hybrid Method

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