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dc.contributor.authorChilla, M
dc.contributor.authorPullan, G
dc.contributor.authorGallimore, S
dc.date.accessioned2019-03-12T00:30:16Z
dc.date.available2019-03-12T00:30:16Z
dc.date.issued2019
dc.identifier.isbn9780791858554
dc.identifier.urihttps://www.repository.cam.ac.uk/handle/1810/290431
dc.description.abstract<jats:title>Abstract</jats:title> <jats:p>The effects of blade row interactions on stator-mounted instrumentation in axial compressors are investigated using unsteady numerical calculations. The test compressor is an 8-stage machine representative of an aero-engine core compressor. For the unsteady calculations, a 180deg sector (half-annulus) model of the compressor is used.</jats:p> <jats:p>It is shown that the time-mean flow field in the stator leading edge planes is circumferentially non-uniform. The circumferential variations in stagnation pressure and stagnation temperature respectively reach 4.2% and 1.1% of the local mean. Using spatial wave number analysis, the incoming wakes from the upstream stator rows are identified as the dominant source of the circumferential variations in the front and middle of the compressor, while towards the rear of the compressor, the upstream influence of the eight struts in the exit duct becomes dominant. Based on three circumferential probes, the sampling errors for stagnation pressure and stagnation temperature are calculated as a function of the probe locations. Optimization of the probe locations shows that the sampling error can be reduced by up to 77% by circumferentially redistributing the individual probes. The reductions in the sampling errors translate to reductions in the uncertainties of the overall compressor efficiency and inlet flow capacity by up to 50%.</jats:p> <jats:p>Recognizing that data from large-scale unsteady calculations is rarely available in the instrumentation phase for a new test rig or engine, a method for approximating the circumferential variations with single harmonics is presented. The construction of the harmonics is based solely on the knowledge of the number of stators in each row and a small number of equi-spaced probes. It is shown how excursions in the sampling error are reduced by increasing the number of circumferential probes.</jats:p>
dc.description.sponsorshipIndustry funded
dc.publisherAmerican Society of Mechanical Engineers
dc.rightsAll Rights Reserved
dc.rights.urihttp://www.rioxx.net/licenses/all-rights-reserved
dc.titleReducing instrumentation errors caused by circumferential flow field variations in multi-stage axial compressors
dc.typeConference Object
prism.publicationDate2019
prism.publicationNameProceedings of the ASME Turbo Expo
prism.volume2A-2019
dc.identifier.doi10.17863/CAM.37658
dcterms.dateAccepted2019-02-05
rioxxterms.versionofrecord10.1115/GT2019-90839
rioxxterms.versionAM
rioxxterms.licenseref.urihttp://www.rioxx.net/licenses/all-rights-reserved
rioxxterms.licenseref.startdate2019-01-01
dc.contributor.orcidChilla, Martin [0000-0002-7854-2948]
rioxxterms.typeConference Paper/Proceeding/Abstract
cam.issuedOnline2019-11-05
pubs.conference-nameASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition
pubs.conference-start-date2019-06-17
cam.orpheus.successThu Nov 05 11:53:36 GMT 2020 - Embargo updated
pubs.conference-finish-date2019-06-21
rioxxterms.freetoread.startdate2020-01-01


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