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

Lorteau, Mathieu; Wiart, Ludovic; Kopiev, V. F.; Denisov, S. L.

doi:10.2514/6.2019-2519

Cited by 9 publications

(8 citation statements)

References 21 publications

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“…To study the acoustic confinement effects of a turbofan in a wind-tunnel, we intend to compute the noise radiated by this turbofan taking into account the wind-tunnel geometry and the mean flow effects. To this aim, the full-Immersed Boundary methodology detailed in Mincu et al [1] and Lorteau et al [2] is used, so only a brief summary is given in this section. A two-step methodology is used: CFD then CAA.…”

Section: Numerical Methodologymentioning

confidence: 99%

“…Two mean flow fields are mandatory: one for the isolated nacelle without its support ("free-field" in table 2), the other for the nacelle and its support inside the wind-tunnel ("confined" in table 2). Similarly to Lorteau et al [2], the mean flow around the geometry is computed via a RANS approach using the Cartesian solver of FastS [17][18][19][20][21][22] developped at ONERA, the geometry being taken into account via the IBM. More details on the IBM implemented in FastS can be found in Péron et al [18,21].…”

Section: B Mean Flow Computationmentioning

confidence: 99%

“…This study focuses on the fan noise confinement effects in the ONERA S1MA wind-tunnel. To this aim, the methodology first implemented by Mincu et al [1] and further improved by Lorteau et al [2] is used, the latter authors studied fan noise installation effects considering a realistic aircraft geometry using the Immersed Boundary Method (IBM). This method is particularly straightforward to take into account the effects of, not only the solid walls, but other boundary conditions and thus enables to overcome the mesh design difficulties inherent to complex geometries.…”

Section: Introductionmentioning

confidence: 99%

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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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Section: Numerical Methodologymentioning

confidence: 99%

Section: B Mean Flow Computationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

Lorteau¹,

Garrec²

2021

Aiaa Aviation 2021 Forum

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“…Furthermore, several studies focused on the aeroacoustic aspect of the BLI concept. Mincu et al [92] and later Lorteau [93] presented methodologies using CAA (Computational Aero-Acoustic) solvers with 3D CFD simulations to assess the noise emission of the aircraft. Further aeroacoustics studies were presented by Romani et al [94,95] by conducting CFD/CAA simulations.…”

Section: Nova Conceptmentioning

confidence: 99%

Recent Advances in Boundary Layer Ingestion Technology of Evolving Powertrain Systems

2022

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The increasing environmental concern during the last years is driving the research community towards reducing aviation’s environmental impact. Several strict goals set by various aviation organizations shifted the research focus towards more efficient and environmentally friendly aircraft concepts. Boundary Layer Ingestion (BLI) is currently investigated as a potential technology to achieve different design goals such as energy efficiency improvement and noise emission reductions in the next generation of commercial aircraft. The technology principle is to place the propulsive unit within the boundary layer generated by the airframe body. Although several studies showed its theoretical benefits, a multidisciplinary nature is introduced in the design phase. This imposes new challenges on the current design tools. An increasing number of publications are focusing on assessing this technology while taking into account interlinks between different disciplines. The goal of this work is to review the current state-of-the-art of BLI evaluation studies. Particular focus is given to the underlying assumptions of each work, the methodology employed, and the level of fidelity of the tools used. By organizing the available work in a comprehensive manner, the up-to-date results are interpreted. The current trends and trade-offs emerging from studies are presented. Through reviewing the ongoing published work, the next steps for further development of the methods that will assess this technology are derived.

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“…Only recently have we observed a return to interest in OWN aerodynamic performance [11][12][13][14][15][16][17], including distributed over-wing propulsion [18], and noise shielding characteristics [19][20][21][22]. One study by Hooker et al [13] is of particular interest.…”

Section: Introductionmentioning

confidence: 99%

Sensitivity Analysis of the Overwing Nacelle Design Space

Ahuja

Renganathan

Mavris

2022

Journal of Aircraft

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The over-wing nacelle (OWN) concept refers to aircraft designs where the engine is installed above the wing. The OWN configuration offers several advantages over conventional under-wing nacelle (UWN) vehicles, which include improved fuel-burn and propulsive efficiencies due to the feasibility of ultra high bypass ratio turbofans, and reduced noise. However, a non-optimal OWN design can result in large transonic drag penalties that can potentially outweigh the aforementioned benefits. We study the OWN design problem from an aerodynamics and propulsion perspective, using the NASA common research model, a notional 90,000 pound thrust class turbofan model, and Reynolds-Averaged Navier-Stokes simulations. We first quantify the sensitivity of drag, lift, and pressure recovery to variations in engine location and power setting, and identify trends. Then, we perform aerodynamic design optimization of the wing and nacelle to determine OWN performance improvement from outer mold line refinement at a favorable engine installation location. A 20% reduction in drag is achieved for the optimized OWN configuration, highlighting the sensitivity of OWN aerodynamics to airframe contours. However, compared to the UWN baseline, the optimized OWN drag is 5% higher at the same lift and worsens significantly at higher lift.

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

Cited by 9 publications

References 21 publications

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

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

Recent Advances in Boundary Layer Ingestion Technology of Evolving Powertrain Systems

Sensitivity Analysis of the Overwing Nacelle Design Space

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