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Numerical investigation into slitted leading-edge profiles for reducing interaction noise

Numerical investigation into slitted leading-edge profiles for reducing interaction noise
Numerical investigation into slitted leading-edge profiles for reducing interaction noise

Reducing aircraft noise has become a significant political issue over the last decade, with the establishment of more demanding regulations concerning noise emissions. Aerofoil-Turbulence Interaction noise is an inviscid phenomenon generated by the impingement of turbulent flows on the leading-edge of an aerofoil. Occurring during the interaction of the turbulent wakes from the rotor with the outlet guide vanes, ATI noise is believed to be the dominant broadband noise source on modern turbofan engines. A recent experimental study has shown the increased effectiveness of new innovative leading edge profiles for reducing ATI noise, in comparison to conventional sinusoidal or sawtooth profiles. Slitted leading-edges have been identified by far as the most effective geometry that has been tested in terms of noise reductions. This present project focuses on the investigation of these novel leading-edge geometries through a numerical approach and aims at understanding the noise reduction mechanisms in order to further optimize the serration geometries. In this study, a flat-plate in a uniform mean flow is numerically being impacted by vortical perturbations, modelled by a single spanwise vortex injected upstream of the aerofoil. The computational work is realised based on an optimized high-order finite difference solver, solving the full 3D compressible Euler equations in time-domain. Results concerning the surface pressure fluctuations generated on the flat-plate are being analysed and compared to results obtained with a straight LE. A special focus is laid on the identification of noise reduction mechanisms involved in the use of these particular serration profiles.

Aeroacoustics, Aerofoil-turbulence interaction, Serrations
1366-1373
International Institute of Acoustics and Vibration (IIAV)
Cannard, Marine
c0858ffc-6271-4a4f-930a-9117a6d543ce
Joseph, Phillip
9c30491e-8464-4c9a-8723-2abc62bdf75d
Chaitanya, Paruchuri
5c1def64-6347-4be3-ac2d-b9f6a314b81d
Kim, Jae Wook
fedabfc6-312c-40fd-b0c1-7b4a3ca80987
Cannard, Marine
c0858ffc-6271-4a4f-930a-9117a6d543ce
Joseph, Phillip
9c30491e-8464-4c9a-8723-2abc62bdf75d
Chaitanya, Paruchuri
5c1def64-6347-4be3-ac2d-b9f6a314b81d
Kim, Jae Wook
fedabfc6-312c-40fd-b0c1-7b4a3ca80987

Cannard, Marine, Joseph, Phillip, Chaitanya, Paruchuri and Kim, Jae Wook (2018) Numerical investigation into slitted leading-edge profiles for reducing interaction noise. In 25th International Congress on Sound and Vibration 2018, ICSV 2018: Hiroshima Calling. vol. 3, International Institute of Acoustics and Vibration (IIAV). pp. 1366-1373 .

Record type: Conference or Workshop Item (Paper)

Abstract

Reducing aircraft noise has become a significant political issue over the last decade, with the establishment of more demanding regulations concerning noise emissions. Aerofoil-Turbulence Interaction noise is an inviscid phenomenon generated by the impingement of turbulent flows on the leading-edge of an aerofoil. Occurring during the interaction of the turbulent wakes from the rotor with the outlet guide vanes, ATI noise is believed to be the dominant broadband noise source on modern turbofan engines. A recent experimental study has shown the increased effectiveness of new innovative leading edge profiles for reducing ATI noise, in comparison to conventional sinusoidal or sawtooth profiles. Slitted leading-edges have been identified by far as the most effective geometry that has been tested in terms of noise reductions. This present project focuses on the investigation of these novel leading-edge geometries through a numerical approach and aims at understanding the noise reduction mechanisms in order to further optimize the serration geometries. In this study, a flat-plate in a uniform mean flow is numerically being impacted by vortical perturbations, modelled by a single spanwise vortex injected upstream of the aerofoil. The computational work is realised based on an optimized high-order finite difference solver, solving the full 3D compressible Euler equations in time-domain. Results concerning the surface pressure fluctuations generated on the flat-plate are being analysed and compared to results obtained with a straight LE. A special focus is laid on the identification of noise reduction mechanisms involved in the use of these particular serration profiles.

Full text not available from this repository.

More information

Published date: 2018
Venue - Dates: 25th International Congress on Sound and Vibration 2018: Hiroshima Calling, ICSV 2018, Japan, 2018-07-07 - 2018-07-11
Keywords: Aeroacoustics, Aerofoil-turbulence interaction, Serrations

Identifiers

Local EPrints ID: 427258
URI: http://eprints.soton.ac.uk/id/eprint/427258
PURE UUID: 6504f155-30cc-41a0-aff8-c73ab8ba988c
ORCID for Jae Wook Kim: ORCID iD orcid.org/0000-0003-0476-2574

Catalogue record

Date deposited: 10 Jan 2019 17:30
Last modified: 27 Jan 2020 13:40

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