Please use this identifier to cite or link to this item: http://hdl.handle.net/10397/92760
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dc.contributorDepartment of Mechanical Engineeringen_US
dc.contributorDepartment of Aeronautical and Aviation Engineeringen_US
dc.creatorZhang, Zen_US
dc.creatorWen, Cen_US
dc.creatorZhang, Wen_US
dc.creatorLiu, Yen_US
dc.creatorJiang, Zen_US
dc.date.accessioned2022-05-16T09:07:35Z-
dc.date.available2022-05-16T09:07:35Z-
dc.identifier.issn0010-2180en_US
dc.identifier.urihttp://hdl.handle.net/10397/92760-
dc.language.isoenen_US
dc.publisherElsevieren_US
dc.subjectBoundary layer separationen_US
dc.subjectCombustoren_US
dc.subjectNormal detonation waveen_US
dc.subjectOblique detonation engineen_US
dc.subjectOblique detonation waveen_US
dc.titleFormation of stabilized oblique detonation waves in a combustoren_US
dc.typeJournal/Magazine Articleen_US
dc.identifier.spage423en_US
dc.identifier.epage436en_US
dc.identifier.volume223en_US
dc.identifier.doi10.1016/j.combustflame.2020.09.034en_US
dcterms.abstractInitiation and stabilization of oblique detonation waves (ODWs) are important to the successful application of oblique detonation engines (ODEs), which, however, have been rarely studied under realistic combustor conditions. In this study, the flow structures, stabilization characteristics and potential thrust performance (under different combustor's geometries with different ODW reflection locations) in a typical hydrogen-fueled ODE combustor are numerically studied by solving the two-dimensional multi-species Reynolds-averaged conservation equations with a detailed hydrogen combustion mechanism. Results suggest that all the detonation waves/shock waves can be stabilized in the space-confined combustor, and the boundary layer separation induced by the ODW-boundary layer interaction is found crucial to determining the types of combustion mode in the combustor. Except for the expected ODW-induced combustion, fast combustion induced by a stabilized overdriven normal detonation wave (NDW) may exist in the combustor simultaneously (even up to a large extent, >73.7%). It is demonstrated that the stabilization of the overdriven NDW in the combustor can be attributed to the formation of an effective aerodynamic convergent-divergent nozzle that quickly accelerates the subsonic flow behind the NDW to supersonic, preventing downstream disturbances from propagating upstream. Benefiting from the chemical equilibrium shift caused by the expansion effect of the flow, more heat is released to compensate for the compression loss and the simulated thrust performance is shown not deteriorate significantly even with a large percentage of NDW-induced combustion existing in the ODE combustor. This work would be beneficial to the future developments of the ODEs.en_US
dcterms.accessRightsembargoed accessen_US
dcterms.bibliographicCitationCombustion and flame, Jan. 2021, v. 223, p. 423-436en_US
dcterms.isPartOfCombustion and flameen_US
dcterms.issued2021-01-
dc.identifier.scopus2-s2.0-85094107677-
dc.description.validate202205 bckwen_US
dc.description.oaNot applicableen_US
dc.identifier.FolderNumberAAE-0059-
dc.description.fundingSourceOthersen_US
dc.description.fundingTextNational Natural Science Foundation of Chinaen_US
dc.description.pubStatusPublisheden_US
dc.date.embargo2023-01-31en_US
dc.identifier.OPUS43059015-
Appears in Collections:Journal/Magazine Article
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