Exploring-optimizing the impact of bumps on the endwalls of a transonic compressor rotor.

Μπουζαλάς, Κωνσταντίνος; Kostantinos, Bouzalas

dc.contributor.author	Μπουζαλάς, Κωνσταντίνος	el
dc.contributor.author	Kostantinos, Bouzalas	en
dc.date.accessioned	2025-07-28T06:29:41Z
dc.date.available	2025-07-28T06:29:41Z
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/62187
dc.identifier.uri	http://dx.doi.org/10.26240/heal.ntua.29883
dc.rights	Αναφορά Δημιουργού 3.0 Ελλάδα	*
dc.rights.uri	http://creativecommons.org/licenses/by/3.0/gr/	*
dc.subject	Endwall	en
dc.subject	Turbomachinery	en
dc.subject	Contouring	en
dc.subject	Rotor 37	en
dc.subject	Optimization	en
dc.subject	Βελτιστοποίηση	el
dc.subject	Διαμόρφωση κελυφών	el
dc.subject	Στροβιλομηχανές	el
dc.subject	Υπολογιστική ρευστοδυναμική	el
dc.subject	Κινητή πτερύγωση Rotor 37	el
dc.title	Exploring-optimizing the impact of bumps on the endwalls of a transonic compressor rotor.	en
dc.title	Διερεύνηση-βελτιστοποίηση της επίδρασης διαμορφώσεων στα κελύφη κινητής πτερύγωσης διηχητικού συμπιεστή.	el
heal.type	bachelorThesis
heal.classification	Thermal Turbomachinery	en
heal.language	el
heal.language	en
heal.access	free
heal.recordProvider	ntua	el
heal.publicationDate	2025
heal.abstract	This thesis investigates the effects of endwall contouring on the aerodynamic per- formance of NASA Rotor 37, the inlet rotor of a transonic axial compressor, with emphasis on improving isentropic efficiency. NASA Rotor 37 is a widely recognized benchmark in the field of turbomachinery, offering both extensive computational and experimental data, which makes it an ideal candidate for this study. The primary objective of this research is to explore how variations in the contour of the rotor’s hub and shroud regions, particularly outside the blade passage, affect the overall flow dynamics and performance. Endwall contouring has emerged as a key focus in optimizing turbomachinery through Computational Fluid Dynamics (CFD), with extensive studies aimed at gaining a deeper understanding of flow behavior within these systems. The endwall region, in particular, plays a critical role in the overall performance of turbomachinery, where the interaction of boundary layers and the formation of secondary flows significantly affects pressure losses and flow uniformity. These complexities in the endwall region motivate the need for targeted optimization strategies that can mitigate secondary flows and enhance overall efficiency. In this study, axisymmetric arch-shaped endwall contouring is applied to the sections outside the blade passage. Initially, a parametric study is performed to identify the most beneficial region for optimization, while exploring the different results of the regions and their impact on rotor performance. Secondly, the flow behavior is analyzed in response to the applied changes, enabling the evaluation of how the optimized geometry affects performance parameters, such as pressure losses and the velocity field. i The flow solver, PUMA(Parallel Unstructured Multi-row & Adjoint solver), and the optimization framework, EASY (Evolutional Algorithms SYstem), both of which are developed by the Parallel CFD & Optimization Unit (PCOpt) at NTUA, are utilized in this study. PUMA, a GPU-enabled software tool designed for flow simulations, ensures efficient and accurate computational analysis. Meanwhile, EASY, a generic optimization platform based on evolutionary algorithms and assisted by artificial intelligence, facilitates optimization by exploring and evaluating a wide design space. For the shape parameterization, Bézier curves are employed to define the endwall profile in the meridional plane offering flexibility and control over the design while the interpolation of the produced displacement to the interior is handled using Radial Basis Function (RBF) interpolation, ensuring smooth transitions across the geometry.	en
heal.advisorName	Giannakoglou, Kyriakos C.	en
heal.committeeMemberName	Mathioudakis, Konstantinos	en
heal.committeeMemberName	Aretakis, Nikolaos	en
heal.academicPublisher	Εθνικό Μετσόβιο Πολυτεχνείο. Σχολή Μηχανολόγων Μηχανικών. Τομέας Ρευστών. Εργαστήριο Θερμικών Στροβιλομηχανών	el
heal.academicPublisherID	ntua
heal.numberOfPages	69 σ.	el
heal.fullTextAvailability	false