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dc.contributor.authorBENNETT, GARETHen
dc.date.accessioned2012-06-21T10:09:21Z
dc.date.available2012-06-21T10:09:21Z
dc.date.created6-8 Juneen
dc.date.issued2011en
dc.date.submitted2011en
dc.identifier.citationIan Davis, Gareth J. Bennett, Spatial Noise Source Identification of Tonal Noise in Turbomachinery Using the Coherence Function on a Modal Basis (AIAA-2011-2825), 17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference), Portland, Oregon, USA, 6-8 June, AIAA-2011-2825, 2011, CD-ROMen
dc.identifier.otherYen
dc.identifier.urihttp://hdl.handle.net/2262/63899
dc.descriptionPUBLISHEDen
dc.descriptionPortland, Oregon, USAen
dc.description.abstractIn modern helicopter engines, the core noise generated by the combustor and turbine stages dominates the core sound radiated from the engine exhaust. Identi cation of the specific contributions of each rotor-stator stage to the core noise is impeded by the lack of available space and the complex duct geometry within the engine. Modal decomposition is an advanced technique which can be used to analyse detailed information on the modal content of the core noise radiating from the engine. This paper advances previous work whereby a technique of identifying noise source location in ducts using the coherence function on a modal basis was developed. A proof of concept was developed using analytical data, with a full radial modal decomposition performed at two axial locations upstream and downstream in the duct. For the case of a real helicopter engine however, there is not enough space to perform a full modal decomposition upstream of the turbine. In this paper, the aforementioned technique is applied to experimental data in order to verify its usefulness for application inside a real turboshaft engine. The technique is also advanced to calculate the coherence between the modes found from a full modal decomposition close to the exit plane of the test duct in the flow (analogous to the engine exhaust) and a singlenpressure measurement upstream (analogous to a point inside the engine close to a noise source of interest). This better represents a realisable technique within the small confines of an engine, as only one pressure transducer is required in the region of each source location of interest. Experimental data measured within an FP7 European research project by one of the consortium partners (German Aerospace Centre (DLR)) was be used to validate this technique.en
dc.description.sponsorshipEuropean Union Seventh Framework Programme TEENI project which is funded under EU commission grant agreement 212367.en
dc.format.extentCD-ROMen
dc.language.isoenen
dc.relation.ispartofseriesAIAA-2011-2825en
dc.rightsYen
dc.subjectTurbomachineryen
dc.subjectAeroacousticsen
dc.subjectCoherenceen
dc.subjectNoise Source Identificationen
dc.subjectTurboshaften
dc.subjectAeroengineen
dc.subjectHelicopteren
dc.subjectBroadband Noiseen
dc.subjectTEENIen
dc.subjectAzimuthal Radial Acoustic Modeen
dc.subjectAcoustic Modal Decompositionen
dc.titleSpatial Noise Source Identification of Tonal Noise in Turbomachinery Using the Coherence Function on a Modal Basis (AIAA-2011-2825)en
dc.title.alternative17th AIAA/CEAS Aeroacoustics Conference (32nd AIAA Aeroacoustics Conference)en
dc.typeConference Paperen
dc.contributor.sponsorEuropean Union (EU)en
dc.type.supercollectionscholarly_publicationsen
dc.type.supercollectionrefereed_publicationsen
dc.identifier.peoplefinderurlhttp://people.tcd.ie/bennettgen
dc.identifier.rssinternalid74034en
dc.relation.ecprojectidinfo:eu-repo/grantAgreement/EC/FP7/212367
dc.rights.ecaccessrightsOpenAccess
dc.contributor.sponsorGrantNumber212367en
dc.identifier.rssurihttp://arc.aiaa.org/doi/abs/10.2514/6.2011-2825en


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