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Sound radiation of fan tones from an installed turbofan aero-engine: fuselage boundary-layer refraction effects

Sound radiation of fan tones from an installed turbofan aero-engine: fuselage boundary-layer refraction effects
Sound radiation of fan tones from an installed turbofan aero-engine: fuselage boundary-layer refraction effects
A distributed source model to predict fan tone noise levels of an installed turbofan aero-engine is extended to include the refraction effects caused by the fuselage boundary layer. The model is a simple representation of an installed turbofan, where fan tones are represented in terms of spinning modes radiated from a semi-infinite circular duct, and the aircraft's fuselage is represented by an infinitely long, rigid cylinder. The distributed source is a disc, formed by integrating infinitesimal volume sources located on the intake duct termination. The cylinder is located adjacent to the disc. There is uniform axial flow, aligned with the axis of the cylinder, everywhere except close to the cylinder where there is a constant thickness boundary layer. The aim is to predict the near-field acoustic pressure, and to quantify the effect of the boundary layer on the sound pressure levels on the cylinder's surface. Thus no far-field approximations are included in the modelling. The sound propagation through the boundary layer is calculated by solving the Pridmore-Brown equation. Results from the theoretical method show that the boundary layer has a significant, nuanced effect on the sound pressure levels on the cylindrical fuselage, owing to sound radiation of fan tones from an installed turbofan aero-engine.
Gaffney, James
7d1a9e19-a1cc-4066-8d98-e9e29c2a0177
McAlpine, Alan
aaf9e771-153d-4100-9e84-de4b14466ed7
Kingan, Michael
2d2daafa-d6d7-41aa-a9fc-2307259ac9f0
Gaffney, James
7d1a9e19-a1cc-4066-8d98-e9e29c2a0177
McAlpine, Alan
aaf9e771-153d-4100-9e84-de4b14466ed7
Kingan, Michael
2d2daafa-d6d7-41aa-a9fc-2307259ac9f0

Gaffney, James, McAlpine, Alan and Kingan, Michael (2016) Sound radiation of fan tones from an installed turbofan aero-engine: fuselage boundary-layer refraction effects. 22nd AIAA/CEAS Aeroacoustics Conference, Lyon, France. 30 May - 01 Jun 2016. 23 pp . (doi:10.2514/6.2016-2878).

Record type: Conference or Workshop Item (Paper)

Abstract

A distributed source model to predict fan tone noise levels of an installed turbofan aero-engine is extended to include the refraction effects caused by the fuselage boundary layer. The model is a simple representation of an installed turbofan, where fan tones are represented in terms of spinning modes radiated from a semi-infinite circular duct, and the aircraft's fuselage is represented by an infinitely long, rigid cylinder. The distributed source is a disc, formed by integrating infinitesimal volume sources located on the intake duct termination. The cylinder is located adjacent to the disc. There is uniform axial flow, aligned with the axis of the cylinder, everywhere except close to the cylinder where there is a constant thickness boundary layer. The aim is to predict the near-field acoustic pressure, and to quantify the effect of the boundary layer on the sound pressure levels on the cylinder's surface. Thus no far-field approximations are included in the modelling. The sound propagation through the boundary layer is calculated by solving the Pridmore-Brown equation. Results from the theoretical method show that the boundary layer has a significant, nuanced effect on the sound pressure levels on the cylindrical fuselage, owing to sound radiation of fan tones from an installed turbofan aero-engine.

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Accepted/In Press date: 2 February 2016
e-pub ahead of print date: 30 May 2016
Venue - Dates: 22nd AIAA/CEAS Aeroacoustics Conference, Lyon, France, 2016-05-30 - 2016-06-01
Organisations: Acoustics Group

Identifiers

Local EPrints ID: 403984
URI: http://eprints.soton.ac.uk/id/eprint/403984
PURE UUID: 594efb5e-eb4e-46bf-bc5d-8f715a8fd80f
ORCID for Alan McAlpine: ORCID iD orcid.org/0000-0003-4189-2167

Catalogue record

Date deposited: 19 Dec 2016 14:34
Last modified: 16 Mar 2024 03:02

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Contributors

Author: James Gaffney
Author: Alan McAlpine ORCID iD
Author: Michael Kingan

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