Unsteady swirl distortion in a short intake under crosswind conditions

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dc.contributor.authorPiovesan, Tommaso
dc.contributor.authorZachos, Pavlos K
dc.contributor.authorMacManus, David G
dc.contributor.authorSheaf, Christopher
dc.date.accessioned2025-01-21T15:01:21Z
dc.date.available2025-01-21T15:01:21Z
dc.date.freetoread2025-01-21
dc.date.issued2024-12-31
dc.date.pubOnline2024-12-13
dc.description.abstractUnder crosswind operating conditions, the flow field of an aero-engine intake can be characterized by notable unsteady flow distortion. These distortions are typically associated with flow separation within the intake as well as with the ingestion of the ground vortex. This unsteady flow distortion can have a detrimental effect on the intake performance and potentially on the operability of the downstream compression system. Measurements of the unsteady velocity field within a model-scale intake under crosswind conditions were acquired using stereo particle image velocimetry (S-PIV). This work analyzes the S-PIV data to quantify the unsteady flow distortion, as well as the characteristics of the ingested ground vortex, in a short intake under crosswind conditions. The swirl distortion metrics were calculated for a range of crosswind velocities and intake mass flow capture ratios (MFCRs). The conditions at which the intake flow separates depend on crosswind velocity, ground clearance, the design of the intake, and the MFCR. Flow characteristics of both low MFCR diffusion-driven and high MFCR shock-induced separation were identified. The circumferential extent and intensity of the swirl distortion are strongly dependent on the crosswind velocity and mass flow rate. The swirl distortion caused by the diffusion-driven separation is greater than that due to the shock-induced separation. The diffusion-driven separation affects a larger portion of the intake aerodynamic interface plane with greater time-averaged and peak distortion levels compared to shock-induced separation. The ground vortex characterization at the aerodynamic interface plane showed a decreasing level of unsteadiness in vortex meandering with increasing MFCR.
dc.description.journalNameAIAA Journal
dc.description.sponsorshipThis work presented in this paper was conducted under project NIFTI which received funding from the CLEAN SKY 2 Joint Undertaking (JU) under Grant Agreement no. 864911. The JU receives support from the European Union’s Horizon 2020 research and innovation programme and the CLEAN SKY 2 JU members other than the Union.
dc.format.extentpp.
dc.identifier.citationPiovesan T, Zachos PK, MacManus DG, Sheaf C. (2024) Unsteady swirl distortion in a short intake under crosswind conditions. AIAA Journal, Available online 13 December 2024
dc.identifier.eissn1533-385X
dc.identifier.elementsID561023
dc.identifier.issn0001-1452
dc.identifier.urihttps://doi.org/10.2514/1.j064226
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23408
dc.languageEnglish
dc.language.isoen
dc.publisherAmerican Institute of Aeronautics and Astronautics (AIAA)
dc.publisher.urihttps://arc.aiaa.org/doi/10.2514/1.J064226
dc.rightsAttribution 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/
dc.subjectVortex Dynamics
dc.subjectMass Flow Rate
dc.subjectParticle Image Velocimetry
dc.subjectBoundary Layers
dc.subjectFlow Conditions
dc.subjectAircraft Engines
dc.subjectFluid Flow Properties
dc.subjectCompression Systems
dc.subjectAerodynamic Characteristics
dc.subjectGerman Dutch Wind Tunnels
dc.subject4012 Fluid Mechanics and Thermal Engineering
dc.subject40 Engineering
dc.subjectAerospace & Aeronautics
dc.subject4001 Aerospace engineering
dc.subject4012 Fluid mechanics and thermal engineering
dc.titleUnsteady swirl distortion in a short intake under crosswind conditions
dc.typeArticle
dc.type.subtypeArticle
dc.type.subtypeEarly Access
dcterms.dateAccepted2024-11-05

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