Διαμόρφωση των Κελυφών της Περιστρεφόμενης Πτερύγωσης NASA Rotor 37, με χρήση του λογισμικού PUMA

Κοτσαρίνης, Κωνσταντίνος; Kotsarinis, Konstantinos

dc.contributor.author	Κοτσαρίνης, Κωνσταντίνος	el
dc.contributor.author	Kotsarinis, Konstantinos	en
dc.date.accessioned	2022-02-28T19:18:02Z
dc.date.available	2022-02-28T19:18:02Z
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/54872
dc.identifier.uri	http://dx.doi.org/10.26240/heal.ntua.22570
dc.rights	Αναφορά Δημιουργού - Μη Εμπορική Χρήση - Παρόμοια Διανομή 3.0 Ελλάδα	*
dc.rights	Αναφορά Δημιουργού-Μη Εμπορική Χρήση-Όχι Παράγωγα Έργα 3.0 Ελλάδα	*
dc.rights	Αναφορά Δημιουργού-Μη Εμπορική Χρήση-Όχι Παράγωγα Έργα 3.0 Ελλάδα	*
dc.rights	Αναφορά Δημιουργού-Μη Εμπορική Χρήση-Όχι Παράγωγα Έργα 3.0 Ελλάδα	*
dc.rights	Αναφορά Δημιουργού-Μη Εμπορική Χρήση-Όχι Παράγωγα Έργα 3.0 Ελλάδα	*
dc.rights	Αναφορά Δημιουργού-Μη Εμπορική Χρήση-Όχι Παράγωγα Έργα 3.0 Ελλάδα	*
dc.rights	Αναφορά Δημιουργού - Μη Εμπορική Χρήση - Παρόμοια Διανομή 3.0 Ελλάδα	*
dc.rights.uri	http://creativecommons.org/licenses/by-nc-sa/3.0/gr/	*
dc.subject	NASA Rotor 37	en
dc.subject	Compressor Aerodynamics	en
dc.subject	CFD	en
dc.subject	PUMA (PCOpt/NTUA) Validation	el
dc.subject	Endwall Modification	el
dc.subject	Υπολογιστική ρευστοδυναμική	el
dc.subject	Αεροδυναμική Συμπιεστών	el
dc.subject	Περιστρεφόμενη Πτερύγωση NASA Rotor 37	el
dc.subject	Διαμόρφωση Κελυφών	el
dc.subject	Λογισμικό PUMA	el
dc.title	Διαμόρφωση των Κελυφών της Περιστρεφόμενης Πτερύγωσης NASA Rotor 37, με χρήση του λογισμικού PUMA	el
dc.title	NASA Rotor 37 Endwall Profiling Using the GPU-Enabled CFD Solver PUMA	en
dc.contributor.department	Laboratory of Thermal Turbomachines	el
heal.type	bachelorThesis
heal.classification	Thermal Turbomachines	el
heal.language	el
heal.language	en
heal.access	campus
heal.recordProvider	ntua	el
heal.publicationDate	2021-09-30
heal.abstract	In this diploma thesis, turbomachinery endwall shape design methods are applied in the open case of NASA Rotor 37, aiming to a performance and operability bene t. The purpose of this diploma thesis is to present solutions of the endwall shape produced by a manual iterative design process, after cross validating results computed by the PUMA CFD ow solver, developed by PCOpt/NTUA, against computational results and experimental data available from NASA literature. For compressors, the endwall regions are associated with losses, being critical regions of low momentum uid, that lead to operational restrictions. Endwall contouring was used in order to control the overturned boundary layer of the highly loaded compressor blade, reduce the ow separation which is generated in the ow at the root of the blade and mitigate the total pressure losses over the design speed. Speci cally, the endwall surfaces were perturbed near the region of the blade to create convex and concave shapes with the use of B-Splines. The endwall contours were investigated for the hub and the casing of the rotor and provided satisfying improvements to both the performance and the operability of the NASA Rotor 37 case. For the design of the endwall geometries and the discretisation of the domain, the CFD mesh generation tool PADRAM (Parametric Design and Rapid Meshing { developed by Rolls-Royce plc.) was used to mesh the di erent geometries of NASA Rotor 37, while the the GPU-enabled CFD ow solver PUMA was used for simulating the ow in the rotor blade row. A part of the work was carried out at the Rolls-Royce Plc premises in Derby.	en
heal.advisorName	Γιαννάκογλου, Κυριάκος	el
heal.advisorName	Giannakoglou, Kyriakos
heal.committeeMemberName	Γιαννάκογλου, Κυριάκος	el
heal.committeeMemberName	Αρετάκης, Νικόλαος	el
heal.committeeMemberName	Μαθιουδάκης, Κωνσταντίνος	el
heal.committeeMemberName	Mathioudakis, Konstantinos	en
heal.committeeMemberName	Aretakis, Nikolaos	en
heal.committeeMemberName	Mathioudakis, Konstantinos
heal.academicPublisher	Σχολή Μηχανολόγων Μηχανικών	el
heal.academicPublisherID	ntua
heal.numberOfPages	109
heal.fullTextAvailability	false
heal.fullTextAvailability	false