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Near-field sound radiation of fan tones from an installed turbofan aero-engine

Near-field sound radiation of fan tones from an installed turbofan aero-engine
Near-field sound radiation of fan tones from an installed turbofan aero-engine
The development of a distributed source model to predict fan tone noise levels of an installed turbofan aero-engine is reported. The key objective is to examine a canonical problem: how to predict the pressure field due to a distributed source located near an infinite, rigid cylinder. This canonical problem is a simple representation of an installed turbofan, where the distributed source is based on the pressure pattern generated by a spinning duct mode, and the rigid cylinder represents an aircraft fuselage. The radiation of fan tones can be modelled in terms of spinning modes. In this analysis, based on duct modes, theoretical expressions for the near-field acoustic pressures on the cylinder, or at the same locations without the cylinder, have been formulated. Simulations of the near-field acoustic pressures are compared against measurements obtained from a fan rig test. Also, the installation effect is quantified by calculating the difference in the sound pressure levels with and without the adjacent cylindrical fuselage. Results are shown for the blade passing frequency fan tone radiated at a supersonic fan operating condition
0001-4966
1313-1324
McAlpine, Alan
aaf9e771-153d-4100-9e84-de4b14466ed7
Gaffney, James
7d1a9e19-a1cc-4066-8d98-e9e29c2a0177
Kingan, Michael
bd863b89-3d60-4c7b-800f-394e7918f8fb
McAlpine, Alan
aaf9e771-153d-4100-9e84-de4b14466ed7
Gaffney, James
7d1a9e19-a1cc-4066-8d98-e9e29c2a0177
Kingan, Michael
bd863b89-3d60-4c7b-800f-394e7918f8fb

McAlpine, Alan, Gaffney, James and Kingan, Michael (2015) Near-field sound radiation of fan tones from an installed turbofan aero-engine. Journal of the Acoustical Society of America, 138 (3), 1313-1324. (doi:10.1121/1.4928130).

Record type: Article

Abstract

The development of a distributed source model to predict fan tone noise levels of an installed turbofan aero-engine is reported. The key objective is to examine a canonical problem: how to predict the pressure field due to a distributed source located near an infinite, rigid cylinder. This canonical problem is a simple representation of an installed turbofan, where the distributed source is based on the pressure pattern generated by a spinning duct mode, and the rigid cylinder represents an aircraft fuselage. The radiation of fan tones can be modelled in terms of spinning modes. In this analysis, based on duct modes, theoretical expressions for the near-field acoustic pressures on the cylinder, or at the same locations without the cylinder, have been formulated. Simulations of the near-field acoustic pressures are compared against measurements obtained from a fan rig test. Also, the installation effect is quantified by calculating the difference in the sound pressure levels with and without the adjacent cylindrical fuselage. Results are shown for the blade passing frequency fan tone radiated at a supersonic fan operating condition

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__soton.ac.uk_ude_PersonalFiles_Users_amca_mydocuments_My Work Stuff_Papers (AMcA)_Installation acoustics_JASA 2015_Final peer-reviewed copy_McAlpine_etal_JASA2015_final_accepted_version.pdf - Accepted Manuscript
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Accepted/In Press date: 22 July 2015
e-pub ahead of print date: 3 September 2015
Published date: September 2015
Organisations: Inst. Sound & Vibration Research

Identifiers

Local EPrints ID: 381517
URI: http://eprints.soton.ac.uk/id/eprint/381517
ISSN: 0001-4966
PURE UUID: b75a0385-72a0-4860-99ae-3cd8141217bc
ORCID for Alan McAlpine: ORCID iD orcid.org/0000-0003-4189-2167

Catalogue record

Date deposited: 08 Oct 2015 11:03
Last modified: 15 Mar 2024 03:00

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Contributors

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

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