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dc.contributor.authorAcarer, Sercan
dc.contributor.authorOzkol, Unver
dc.date.accessioned2021-02-12T18:47:47Z
dc.date.available2021-02-12T18:47:47Z
dc.date.issued2015
dc.identifier.isbn978-0-7918-5664-2
dc.identifier.urihttps://hdl.handle.net/11147/10317
dc.descriptionASME Turbo Expo: Turbine Technical Conference and Expositionen_US
dc.description.abstractStreamline curvature technique for inverse through-flow modeling of turbomachinery is still one of the most prevalent alternatives in design. Even though the subject has been studied in numerous aspects over many years, open literature on fully coupled split-flow turbomachinery system design which is encountered in turbofan engines, is still limited. The principal method, viable for analysis mode, may easily give rise to undesired streamline distortion near the splitter leading edge whilst operating in design mode. Besides, spanwise discontinuity of flow properties along the stagnation streamline prior to final solution convergence may be another outcome. The present study is geared towards eliminating these potential drawbacks by developing an alternative generally applicable split-flow scheme incorporated in a recently developed streamline curvature software. This new scheme disposes the need to define a stagnation streamline, while preserving full coupling between the main and split ducts. This is achieved through removal of by-pass ratio restriction, which makes local velocity vector always perfectly aligned with the splitter leading edge without any limit on fan-splitter axial distance. A two-step validation strategy is followed: Firstly, 2D split-flow solutions of the developed method for representative duct geometries having design by-pass ratios ranging between 0.25 and 6.5, but without turbomachinery, are compared with a commercial CFD software; Secondly, the method is compared with 3D viscous CFD solution of NASA Rotor 37 geometry, whose flowpath is modified to include a downstream flowpath splitter. It is shown that the proposed scheme can be used as a practical alternative to the conventional treatment that promises minimal effort to implement to an existing compressor streamline curvature methodology.en_US
dc.description.sponsorshipInt Gas Turbine Insten_US
dc.language.isoengen_US
dc.publisherAMER SOC MECHANICAL ENGINEERSen_US
dc.rightsinfo:eu-repo/semantics/closedAccessen_US
dc.titleDEVELOPMENT OF A NEW UNIVERSAL INVERSE THROUGH-FLOW PROGRAM AND METHOD FOR FULLY COUPLED SPLIT-FLOW TURBOMACHINERY SYSTEMSen_US
dc.typeconferenceObjecten_US
dc.typeconferenceObjecten_US
dc.relation.journalAsme Turbo Expo: Turbine Technical Conference And Exposition, 2015, Vol 2Ben_US
dc.contributor.departmentIzmir Isntitute of Technologyen_US
dc.identifier.wosWOS:000380084700024
dc.relation.publicationcategoryMakale - Uluslararası Hakemli Dergi - Kurum Öğretim Elemanıen_US


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