Towards Numerical Simulation of Fan Broadband Noise Propagation and Radiation from Aero-Engines

Reboul, G.; Polacsek, Cyril; Desquesnes, G.

doi:10.2514/6.2009-3337

Cited by 4 publications

(6 citation statements)

References 9 publications

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“…The CAA calculations are conducted with Onera's sAbrinA_v0 solver [2][3][4][5][6]. sAbrinA_v0 is a structured grid, time-accurate CAA code that solves either the full or the linear Euler equations, in a conservative and perturbed form (with a splitting of the complete variables into a "frozen" mean flow and a "fluctuating" perturbation).…”

Section: Caa Solver: Sabrina_v0mentioning

confidence: 99%

“…This will influence the propagation of the acoustic mode, downstream of the nacelle for the fan/OGV stage modelling and upstream of the nacelle for the pylon. To make use of the full potential of the temporal approach of the solver sAbrinA_v0, more realistic fan noise source terms [3,5] will be used in order to compute several acoustic modes at the same time, which we can study separately afterwards through Fourier analysis. The multimodal simulations will require longer simulated time for convergence purpose.…”

Section: Perspectivesmentioning

confidence: 99%

“…In the present work, we propose to use the IBM workflow implemented in the CAA solver sAbrinA_v0 [2][3][4][5][6] to study the installation effects in OWN configuration of the fan noise taking into account the aircraft and nacelle geometries in presence of a realistic mean flow at a Mach number M = 0.25 corresponding to take-off / landing flight conditions. To this aim, we compare the acoustic far field directivity of the OWN configuration and the more classic UWN configuration.…”

Section: Introductionmentioning

confidence: 99%

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Numerical study, with experimental validation, of fan noise installation effects in Over-Wing Nacelle configuration using the Immersed Boundary Method

Lorteau¹,

Wiart²,

Kopiev³

et al. 2019

25th AIAA/CEAS Aeroacoustics Conference

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This work is part of the ONERA-TsAGI cooperative project NOWNA (NextGen Over the Wing Nacelle Aircraft) which investigates the potential of fan noise shielding for a transonic transport aircraft by installing a UHBR engine over its wing. The studied configuration is a derivative of the NOVA (Next Generation Onera Versatile Aircraft) for which cruise aerodynamic performance and low speed acoustics are evaluated and compared to a reference configuration with under wing engines. The present activity is a continuation of previous work on the numerical investigation of the acoustic advantages of Over the Wing Nacelle (OWN) configurations using ONERA's in-house CAA solver sAbrinA_v0 (see Mincu et al., AIAA 2017-3504). Whereas early computations did not assume any mean flow, the present work takes into account a realistic mean flow computed with ONERA's CFD solver FastS, at a global Mach number of 0.25 corresponding to take-off/landing flight conditions, and with a simple flow-through condition for the nacelle. Both CFD and CAA solvers use the Immersed Boundary Method (IBM) to deal with the realistic aircraft and nacelle geometries, which greatly simplifies the meshing stage. Here, this OWN configuration is compared to a more classic UWN (Under the Wing Nacelle) configuration, in terms of far field noise directivity.

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Section: Caa Solver: Sabrina_v0mentioning

confidence: 99%

Section: Perspectivesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Numerical study, with experimental validation, of fan noise installation effects in Over-Wing Nacelle configuration using the Immersed Boundary Method

Lorteau¹,

Wiart²,

Kopiev³

et al. 2019

25th AIAA/CEAS Aeroacoustics Conference

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“…Another technique 16 to cancel the correlation between modes (at BPF tones here) is to add a random phase per mode and to perform a quadratic averaging over N k independent runs. This technique applied to tone noise simulations is unpractical because too many realizations are required to make the statistical errors acceptable.…”

Section: Iiic Mode Coherence Cancelingmentioning

confidence: 99%

Prediction of BPF tones emitted by the inlet of an aero-engine model using in-duct angular mode spectrum measurements

Reboul

Polacsek

Billonnet

et al. 2014

20th AIAA/CEAS Aeroacoustics Conference

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The goal of this study was to realize predictions of tonal noise generated by a SNECMA turbofan mock up with a heterogeneous stator and radiated from the inlet using as input a modal decomposition made in the inlet duct wall. A numerical approach based on the CAA (Computational AeroAcoustics) code sAbrinA.V0 with an equivalent source term recently implemented is used as well as an analytical methodology using a Wiener-Hopf technique and an uniform flow assumption. Even if directivities from raw experimental data exhibit significant variations of noise level in the azimuthal direction proving that correlation effect between modes seems to be not negligible for tonal noise, the hypothesis of incoherent modes inducing axisymmetric directivities allow to compare reasonably well with measured data averaged azimuthally. Comparisons between theoretical and numerical predictions confirm the practical interest of using simplified analytical methods even if clear improvement are provided by more complex and time consuming methods like CAA. Especially, for polar angles between 20 • and 70 • , a very good agreement is obtained with a maximum discrepancy of 0.7 dB on overall sound pressure level for the three first tones.

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“…In the present work, the IBM workflow implemented in the CAA solver sAbrinA_v0 [3][4][5][6][7] is used to study the confinement effects in a closed test-section, equipped with acoustic absorbent material, of the noise radiated by a turbofan bench with a realistic geometry in presence of a realistic mean flow at a Mach number M ∼ 0.25 corresponding to take-off / landing flight conditions. To this aim, the radiated acoustic field from the same turbofan bench is compared in the confined and in free-field configurations.…”

Section: Introductionmentioning

confidence: 99%

Numerical assessment of fan noise confinement effects in a closed wind-tunnel

Lorteau¹,

Garrec²

2021

Aiaa Aviation 2021 Forum

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This work investigates, through numerical simulations, the acoustic confinement effects of a modern turbofan noise bench installed in the ONERA S1MA wind-tunnel with a closed test section at low Mach number equipped with a dedicated acoustic liner. These simulations aim at preparing acoustic experimental measurements of the D13 UHBR engine demonstrator SA2FIR (Simulator of Aerodynamic and Acoustic Fan IntegRation) of the Clean Sky 2 LPA IADP (Large Passenger Aircraft -Innovative Aircraft Demonstration Platform) and more precisely in the workpackage WP1.1.12 of the ADEC (ADvanced Engine and aircraft Configurations) project.The present activity makes use of a full immersed boundary workflow developed in previous works, which consists in computing with a CAA solver, the propagation of the acoustic waves generated by analytic fan/OGV interaction modes injected in the nacelle duct, in the presence of complex geometries and a realistic non-uniform mean flow previously obtained with a CFD solver. Both CFD and CAA solvers use the Immersed Boundary Method to deal with the bench and wind tunnel geometries, which greatly simplifies the meshing stage and also drastically reduces the overall computational time.The confined configuration with lined walls is compared to an isolated nacelle configuration without nacelle support, in terms of acoustic levels and directivity diagrams. Comparisons also include two additional simulations: confined set-up with rigid walls and isolated nacelle with its support to complete the results. The numerical simulations demonstrate the ability of the lined facility to recover the radiated acoustic field of the target free-field configuration.

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Towards Numerical Simulation of Fan Broadband Noise Propagation and Radiation from Aero-Engines

Cited by 4 publications

References 9 publications

Numerical study, with experimental validation, of fan noise installation effects in Over-Wing Nacelle configuration using the Immersed Boundary Method

Numerical study, with experimental validation, of fan noise installation effects in Over-Wing Nacelle configuration using the Immersed Boundary Method

Prediction of BPF tones emitted by the inlet of an aero-engine model using in-duct angular mode spectrum measurements

Numerical assessment of fan noise confinement effects in a closed wind-tunnel

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