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Modeling gaseous non-reactive flow in a lean direct injection gas turbine combustor through an advanced mesh control strategy

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Modeling gaseous non-reactive flow in a lean direct injection gas turbine combustor through an advanced mesh control strategy

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dc.contributor.author Payri, Raul es_ES
dc.contributor.author Novella Rosa, Ricardo es_ES
dc.contributor.author Carreres, Marcos es_ES
dc.contributor.author Belmar-Gil, Mario es_ES
dc.date.accessioned 2021-05-27T03:35:39Z
dc.date.available 2021-05-27T03:35:39Z
dc.date.issued 2020-09 es_ES
dc.identifier.issn 0954-4100 es_ES
dc.identifier.uri http://hdl.handle.net/10251/166848
dc.description.abstract [EN] Fuel efficiency improvement and harmful emissions reduction are the main motivations for the development of gas turbine combustors. Numerical computational fluid dynamics (CFD) simulations of these devices are usually computationally expensive since they imply a multi-scale problem. In this work, gaseous non-reactive unsteady Reynolds-Averaged Navier-Stokes and large eddy simulations of a gaseous-fueled radial-swirled lean direct injection combustor have been carried out through CONVERGE (TM) CFD code by solving the complete inlet flow path through the swirl vanes and the combustor. The geometry considered is the gaseous configuration of the CORIA lean direct injection combustor, for which detailed measurements are available. The emphasis of the work is placed on the demonstration of the CONVERGE (TM) applicability to the multi-scale gas turbine engines field and the determination of an optimal mesh strategy through several grid control tools (i.e., local refinement, adaptive mesh refinement) allowing the exploitation of its automatic mesh generation against traditional fixed mesh approaches. For this purpose, the normalized mean square error has been adopted to quantify the accuracy of turbulent numerical statistics regarding the agreement with the experimental database. Furthermore, the focus of the work is to study the behavior when coupling several large eddy simulation sub-grid scale models (i.e., Smagorinsky, Dynamic Smagorinsky, and Dynamic Structure) with the adaptive mesh refinement algorithm through the evaluation of its specific performances and predictive capabilities in resolving the spatial-temporal scales and the intrinsically unsteady flow structures generated within the combustor. This investigation on the main non-reacting swirling flow characteristics inside the combustor provides a suitable background for further studies on combustion instability mechanisms. es_ES
dc.description.sponsorship The author(s) disclosed receipt of the following financial support for the research, authorship, and/or publication of this article: This work was partly sponsored by the program "Ayuda a Primeros Proyectos de Investigacion (PAID-06-18), Vicerrectorado de Investigacion, Innovacion y Transferencia de la Universitat Politecnica de Valencia (UPV), Spain.'' The support given to Mr. Mario Belmar by Universitat Politecnica de Valencia through the "FPI-Subprograma 2'' grant within the "Programa de Apoyo para la Investigacion y Desarrollo (PAID-01-18)'' is gratefully acknowledged. es_ES
dc.language Inglés es_ES
dc.publisher SAGE Publications es_ES
dc.relation.ispartof Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering es_ES
dc.rights Reserva de todos los derechos es_ES
dc.subject Gas turbine combustor es_ES
dc.subject Turbulent swirling flow es_ES
dc.subject U-RANS es_ES
dc.subject Large eddy simulation es_ES
dc.subject Adaptive mesh refinement es_ES
dc.subject Non-reactive flow es_ES
dc.subject CONVERGE (TM) es_ES
dc.subject.classification INGENIERIA AEROESPACIAL es_ES
dc.subject.classification MAQUINAS Y MOTORES TERMICOS es_ES
dc.title Modeling gaseous non-reactive flow in a lean direct injection gas turbine combustor through an advanced mesh control strategy es_ES
dc.type Artículo es_ES
dc.identifier.doi 10.1177/0954410020919619 es_ES
dc.relation.projectID info:eu-repo/grantAgreement/UPV//PAID-06-18/ es_ES
dc.relation.projectID info:eu-repo/grantAgreement/UPV//PAID-01-18/ es_ES
dc.relation.projectID info:eu-repo/grantAgreement/UPV//SP20180178/ es_ES
dc.rights.accessRights Abierto es_ES
dc.contributor.affiliation Universitat Politècnica de València. Departamento de Máquinas y Motores Térmicos - Departament de Màquines i Motors Tèrmics es_ES
dc.description.bibliographicCitation Payri, R.; Novella Rosa, R.; Carreres, M.; Belmar-Gil, M. (2020). Modeling gaseous non-reactive flow in a lean direct injection gas turbine combustor through an advanced mesh control strategy. Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering. 234(11):1788-1810. https://doi.org/10.1177/0954410020919619 es_ES
dc.description.accrualMethod S es_ES
dc.relation.publisherversion https://doi.org/10.1177/0954410020919619 es_ES
dc.description.upvformatpinicio 1788 es_ES
dc.description.upvformatpfin 1810 es_ES
dc.type.version info:eu-repo/semantics/publishedVersion es_ES
dc.description.volume 234 es_ES
dc.description.issue 11 es_ES
dc.relation.pasarela S\417346 es_ES
dc.contributor.funder Universitat Politècnica de València es_ES
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