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dc.contributor.authorDi Sabatino, Francesco
dc.contributor.authorGuiberti, Thibault
dc.contributor.authorMoeck, Jonas
dc.contributor.authorRoberts, William
dc.contributor.authorLacoste, Deanna
dc.date.accessioned2021-03-01T08:30:52Z
dc.date.available2021-03-01T08:30:52Z
dc.date.created2020-01-31T15:47:34Z
dc.date.issued2020
dc.identifier.citationJournal of Propulsion and Power. 2020, 36 (2), 271-284.en_US
dc.identifier.issn0748-4658
dc.identifier.urihttps://hdl.handle.net/11250/2730785
dc.description.abstractThis paper reports on the effects of fuel and equivalence ratio on the response of lean premixed swirl flames to acoustic perturbations of the flow, at atmospheric pressure. The response is analyzed using flame transfer functions, which relate the relative heat release rate fluctuations from the flame to the relative velocity fluctuations of the incoming flow. Two fuels, propane and methane, and five equivalence ratios are considered. The 10 flames investigated are selected to exhibit the local maximum of the transfer function gain around the same frequency, 176 Hz. The results show that changing fuel and equivalence ratio influences both the gain and the phase of the transfer function. The changes observed at 176 Hz, where the dynamics of the flame is mainly controlled by the flame vortex roll-up mechanism, are discussed. Based on the analysis of the flowfields and the flame wrinkling, the laminar burning velocity and the flame temperature are identified as the main parameters controlling the gain. They have two competing effects: first, by enhancing the flame vortex roll-up and, second, by affecting the strength of the vortex generated by the acoustic forcing due to changes in the height of the flame stabilization location.en_US
dc.language.isoengen_US
dc.publisherAmerican Institute of Aeronautics and Astronautics Inc.en_US
dc.titleFuel and Equivalence Ratio Effects on Transfer Functions of Premixed Swirl Flamesen_US
dc.typePeer revieweden_US
dc.typeJournal articleen_US
dc.description.versionacceptedVersionen_US
dc.source.pagenumber271-284en_US
dc.source.volume36en_US
dc.source.journalJournal of Propulsion and Poweren_US
dc.source.issue2en_US
dc.identifier.doi10.2514/1.B37537
dc.identifier.cristin1788700
dc.description.localcodeCopyright © 2019 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.en_US
cristin.ispublishedtrue
cristin.fulltextpostprint
cristin.qualitycode1


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