Use of non-intrusive flow diagnostics for aero-engine inlet flow distortion measurements in an industrial wind-tunnel

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dc.contributor.authorPiovesan, Tommaso
dc.contributor.authorZachos, Pavlos K.
dc.contributor.authorMacManus, David
dc.contributor.authorMichaelis, Dirk
dc.contributor.authorvan Rooijen, Bart
dc.contributor.authorSheaf, Christopher
dc.contributor.authorArzoglou, Dimitris
dc.date.accessioned2025-04-11T09:01:01Z
dc.date.available2025-04-11T09:01:01Z
dc.date.freetoread2025-04-11
dc.date.issued2025-01-06
dc.date.pubOnline2025-01-03
dc.description.abstractIn crosswind conditions, aero-engine intakes experience unsteady flow distortions at the fan face, typically caused by the ingestion of ground vortices and flow separation. These distortions can negatively impact both intake performance and the compatibility of the downstream propulsion system. Understanding the aerodynamics of these flows is crucial for developing next-generation aircrafts with propulsion systems integrated more closely with the airframe. Optical measurement techniques provide detailed datasets in both space and time to support this understanding, but several challenges limit their widespread use in propulsion integration testing. This study demonstrates a novel application of non-intrusive flow diagnostics in an industrial setting for propulsion integration testing. Optical measurements were conducted within an aspirated intake configuration and, later, within a fully coupled fan-intake propulsion system representative of a modern high-bypass aero-engine. Several innovative solutions were developed to improve the integration of optical systems into industrial settings and enhance data acquisition efficiency. The analysis of the results yielded significant contributions about the unsteady interactions within civil intakes at crosswind and high incidence conditions, which are expected to have a notable impact on the development of future, closely integrated propulsion systems architectures able to meet the specified NetZero targets.
dc.description.conferencenameAIAA SCITECH 2025 Forum
dc.description.sponsorshipThe work presented herein was conducted under the NIFTI project which received funding from the Clean Sky 2 Joint Undertaking (JU) under Grant Agreement No 866521
dc.identifier.citationPiovesan T, Zachos PK, MacManus D, et al., (2025) Use of non-intrusive flow diagnostics for aero-engine inlet flow distortion measurements in an industrial wind-tunnel. AIAA SCITECH 2025 Forum, 6-10 January 2025, Orlando, FL, USA. Paper number AIAA
dc.identifier.elementsID564673
dc.identifier.paperNoAIAA 2025-2111
dc.identifier.urihttps://doi.org/10.2514/6.2025-2111
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23743
dc.language.isoen
dc.publisherAIAA
dc.publisher.urihttps://arc.aiaa.org/doi/10.2514/6.2025-2111
dc.rightsAttribution-NonCommercial 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by-nc/4.0/
dc.subject4012 Fluid Mechanics and Thermal Engineering
dc.subject4007 Control Engineering, Mechatronics and Robotics
dc.subject40 Engineering
dc.titleUse of non-intrusive flow diagnostics for aero-engine inlet flow distortion measurements in an industrial wind-tunnel
dc.typeConference paper
dcterms.coverageOrlando, USA
dcterms.dateAccepted2024-08-26
dcterms.temporal.endDate10-Jan-2025
dcterms.temporal.startDate06-Jan-2025

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