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Generation of discrete distortions (tightly-wound vortices) in an experimental environment

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Generation of discrete distortions (tightly-wound vortices) in an experimental environment

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dc.contributor.advisor Hoyas Calvo, Sergio es_ES
dc.contributor.author Lirola Fuentes, Leyre es_ES
dc.date.accessioned 2015-04-16T12:53:36Z
dc.date.available 2015-04-16T12:53:36Z
dc.date.created 2014-09-30
dc.date.issued 2015-04-16
dc.identifier.uri http://hdl.handle.net/10251/48903
dc.description.abstract The presence of inlet flow distortion has been identified as a potential problem for modern civil and military aircraft engines. In particular, the application of S-shaped intakes ahead of a compression system can lead to the generation of distorted flows which can degrade performance. Several studies have been carried out on the effect of self-generated and ingested distortions on compression systems within the UTC at Cranfield University. The next logical step is to explore and establish suitable techniques for the robust and consistent generation of complex distorted patterns, such as tightly-wound vortices, in an experimental environment. A versatile vortex generator is designed, optimized and analysed in this research. The Coanda effect by means of Circulation Control (CC) profiles is used to deflect the flow in a controlled manner. A proper CC blade arrangement can force the air to turn and create a specific swirl distortion pattern. The CC blade is designed to prescribe a distribution of velocities based on Vatistas’ vortex model. A 2D validation and parametric study is carried out over a pre-design geometry. After several modifications, the 3D baseline model is designed and a parametric study about the influence of Mach number and injection pressure over flow characteristics is performed. The results show the presence of two vortical structures between the blade and the annular supports. These junction vortices strongly affect flow characteristics. The regions corresponding to the locations of the inner and outer supports present peaks of swirl angle and vorticity, and Mach number and total pressure deficits. The radial homogeneity is studied showing high level of distortion in the near blade region but quite lower distortion in the outlet section. Nevertheless, the medium region is not affected by this phenomenon and shows promising vortex characteristics. Finally, a direct effect of injection pressure is observed on flow characteristics, feeding junction vortices strength. In contrast, the reduction of Mach number presents junction vortex detriment but higher global vortex characteristics. es_ES
dc.format.extent 133 es_ES
dc.language Inglés es_ES
dc.publisher Universitat Politècnica de València es_ES
dc.rights Reserva de todos los derechos es_ES
dc.subject Flow control es_ES
dc.subject Coanda effect es_ES
dc.subject Circulation control airfoil es_ES
dc.subject Swirl distortion es_ES
dc.subject Swirl vortex generator es_ES
dc.subject.classification INGENIERIA AEROESPACIAL es_ES
dc.subject.other Grado en Ingeniería Aeroespacial-Grau en Enginyeria Aeroespacial es_ES
dc.title Generation of discrete distortions (tightly-wound vortices) in an experimental environment es_ES
dc.type Proyecto/Trabajo fin de carrera/grado es_ES
dc.rights.accessRights Cerrado es_ES
dc.contributor.affiliation Universitat Politècnica de València. Escuela Técnica Superior de Ingeniería del Diseño - Escola Tècnica Superior d'Enginyeria del Disseny es_ES
dc.description.bibliographicCitation Lirola Fuentes, L. (2014). Generation of discrete distortions (tightly-wound vortices) in an experimental environment. Universitat Politècnica de València. http://hdl.handle.net/10251/48903 es_ES
dc.description.accrualMethod Archivo delegado es_ES


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