This thesis is focused on shape optimization of Venturi´s nozzle with optimization method called response surface method. The first part of this work is concerned with the description of this method as well as explaining the basic principle. Furthermore, there is an explanation of the application of this method in synchronicity with CFD and its operating algorithm. The second part of this thesis is then focused on simple example with plane wing and simplified optimization of Venturi´s nozzle in which this method was tested. In the third part there is described full multiparameter shape optimalization of the nozzle for two geometries.

Le contrôle précis des modèles géométriques joue un rôle important dans de nombreux domaines. Pour l’optimisation de forme en CFD, le choix des paramètres de contrôle et la technique de déformation de forme est critique. Nous proposons un modeleur paramétrique avec une nouvelle méthode de déformation d’objets, ayant pour objectif d’être intégré dans une boucle d’optimisation automatique de forme avec un solveur CFD. Notre méthodologie est basée sur une double paramétrisation des objets : géométrique et architecturale. L’approche géométrique consiste à décrire les formes par un squelette, composé d’une famille de courbes B-Splines, appelées courbes génératrice et courbes de section. Le squelette est paramétré avec une approche architecturale. Au lieu d’utiliser les points de contrôle de la représentation classique par courbes B-Splines, la géométrie est contrôlée par ces paramètres architecturaux. Cela permet de réduire considérablement le nombre de degrés de liberté utilisés dans le problème d’optimisation de forme, et permet de maintenir une description haut niveau des objets. Notre technique intègre un contrôle de forme et un contrôle de régularité, permettant d’assurer la génération de nouvelles formes valides et réalistes. Les déformations de la géométrie sont réalisées en posant un problème inverse : déterminer une géométrie correspondant à un jeu de paramètres cibles. Enfin, une technique de reconstruction de surface est proposée. Nous illustrons le modeleur paramétrique développé et intégré dans une boucle d’optimisation automatique de forme sur trois cas : un profil d’aile d’avion, un foil AC45 d’un voilier de course et un bulbe de chalutier de pêche. / The precise control of geometric models plays an important role in many domains. For shape optimisation in CFD, the choice of control parameters and the way to deform a shape are critical. In this thesis, we propose a new approach to shape deformation for parametric modellers with the purpose of being integrated into an automatic shape optimisation loop with a CFD solver. Our methodology is based on a twofold parameterisation: geometrical and architectural. The geometrical approach consist of a skeleton-based representation of object. The skeleton is made of a family of B-Spline curves, called generating curve and section curves. The skeleton is parametrised with an architectural approach: meaningful design parameters are chosen on the studied object. Thus, instead of using the control points of a classical B-spline representation, we control the geometry in terms of architectural parameters. This reduce the number of degrees of freedom and maintain a high level description of shapes. We ensure to generate valid shapes with a strong shape consistency control based on architectural considerations. Deformations of the geometry are performed by solving optimisation problems on the skeleton. Finally, a surface reconstruction method is proposed to evaluate the shape’s performances with CFD solvers. We illustrate the parametric modeller capabilities on three problems, performed with an automatic shape optimisation loop: the wind section of an plane (airfoil), the foil of an AC45 racing sail boat and the bulbous bow of a fishing trawler.

No description available.

<p>NR 20140805</p>

Cette thèse est consacrée à la dérivation des modèles de fracture comme limite de modèles d'endommagement.L'étude est justifiée essentiellement à travers des simulations numériques.On s'intéresse à étudier un modèle d'endommagement initié par Allaire, Jouve et Vangoethem.Nous apportons des améliorations significatives à ce modèle justifiant la cohérence physique de cette approche.D'abord, on ajoute une contrainte sur l'épaisseur minimale de la zone endommagée, puis on ajoute la condition d'irréversibilité forte.Nous considérons en outre un modèle de fracture avec pénalisation de saut obtenu comme limite asymptotique d'un modèle d'endommagement.Nous justifions ce modèle par une étude numérique et asymptotique formelle unidimensionnelle.Ensuite, la généralisation dans le cas 2D est illustrée par des exemples numériques. / This thesis is devoted to the derivation of fracture models as limit damage models.The study is justified mainly through numerical simulations.We are interested in studying a damage model initiated by Allaire, Jouve and Vangoethem.We are making significant improvements to this model justifying the physical consistency of the approach.First, we add a constraint on the minimum thickness of the damaged area and then we add a condition of strong irreversibility.We see also a fracture model with jump penalization obtained as an asymptotic limit of a damage model.We justify this model by a one-dimensional formal asymptotic numerical study.Then, the generalization in the case 2D is illustrated by numerical examples.

Small-scale wind turbines were not considered viable in the past due to their poor efficiencies, mainly because of their aerodynamic effects around the irfoil shape. Recently researchers have renewed interest in enhancing the aerodynamic performances of the blades’ designs inspired by the aerodynamic pattern of biological characteristics of insects and marine mammals such as locusts, dragonflies, damselflies, Humpback Whales etc. Bioinspired wing designs have advantages compared to conventional smooth irfoil blades as they can counter the bending forces that the wings experience during flapping. Bio-inspired corrugated airfoil based on dragonfly wing geometries have been reported to perform well compared to conventional airfoil at low Reynolds numbers. Corrugated airfoils reduce flow separation and enhance aerodynamic performance by trapping vortices in the corrugations thus drawing flow towards the airfoil’s surface. This results in the higher lift whilst incurring only marginally higher drag. Such airfoils also have an advantage when it comes to span-wise structural stiffness due to the corrugated cross-sections. Replacing conventional turbine blades by tubercles or corrugated blades could enhance turbine performance by reducing the pressure gradient along the leading edge; however, the aerodynamic effects at the leading edge will depend on the variations of wavelength and amplitude. In this study, two types of computational studies were investigated: Optimising a corrugated airfoil and investigating the aerodynamic effects of a sinusoidal shape at the leading edge of a blade. Previous studies used an idealized geometry based on the dragonfly wing cross-section profile but did not attempt to optimize the geometry. In the present study: a two-dimensional CFD model is constructed using ANSYS Fluent Workbench-Design Explorer to determine the optimal corrugated blade profile for four angles of attack (AOA) from 5° to 20° corresponding to typical AOA of small-scale wind turbine blades. Two modified blades with variations of wavelength and amplitude at the leading edge were studied to investigate the aerodynamic effects. Three-dimensional models were constructed using Qblade software and 3D points were exported to AutoCAD Inventor to generate the CAD model. The governing equations used are continuity and Navier-Stokes equations written in a frame reference rotating with the blade. The CFD package used is ANSYS FLUENT 19.0. The simulation was run under steady-state, using SST-k omega turbulence model. The modifications have improved the aerodynamic performance. The optimised corrugated blade produced a maximum increase of CL and L/D. Both modified blades (1 and 2) had their performances measured separately and compared to that of baseline blade SG6042 (Conventional blade). Modified blade 1 had a lower wavelength and amplitude at the leading edge of 14.3 % and 4 % respectively of the chord. It was noted that the aerodynamic performance decreased by 6%. Modified model 2, on the other hand had a higher wavelength and amplitude at the leading edge. of 40.4 % and 11.9 % respectively of the chord. It was also noted the aerodynamic performance increased by 6%. From the empirical evidence highlighted above, it can be observed that there is a direct correlation between wavelength, amplitude, and aerodynamic performance of the blade. / Electrical and Mining Engineering / M. Tech. (Engineering)

In this study, the effect of a passive trapped-vortex cell on lift to drag (L/D) ratio of an FFA-W3-301 airfoil is studied. The upper surface of the airfoil was modified to incorporate a cavity defined by seven parameters. The L/D ratio of the airfoil is modeled using a radial basis function metamodel. This model is used to find the optimal design parameter values that give the highest L/D. The numerical results indicate that the L/D ratio is most sensitive to the position on an airfoil’s upper surface at which the cavity starts, the position of the end point of the cavity, and the vertical distance of the cavity end point relative to the airfoil surface. The L/D ratio can be improved by locating the cavity start point at the point of separation for a particular angle of attack. The optimal cavity shape (o19_aXX) is also tested for a NACA0024 airfoil.

Structural Optimization techniques are widely used in product development process in ‘modern industry’ to generate optimal designs with only sufficient material to serve the purpose of the component. In conventional design problems, the design process usually generates overdesigned components with excess material and weight. This will in turn increase the life time cost of machines, both in terms material wastage and expense of usage. The thesis “Design of a weight optimized casted ADI component using topology and shape optimization” deals with redesigning a component from a welded steel plate structure into a castable design for reduced manufacturing cost and weight reduction. The component “Drill Steel Support” mounted in front of the drilling boom of a Face Drilling Machine is redesigned during this work. The main objective of the thesis is to provide an alternative design with lower weight that can be mounted on the existing machine layout without any changes in the mounting interfaces. This thesis report covers in detail procedure followed for attaining the weight reduction of the “Drill Steel Support” and presents the results and methodology which is based on both topology and shape optimization. / Strukturoptimering används ofta i produktutvecklingsprocessen i modern industri för att ta fram optimala konstruktioner med minsta möjliga materialåtgång för komponenten. Konventionella konstruktionsmetoder genererar vanligtvis överdimensionerade komponenter med överflödigt material och vikt. Detta ökar i sin tur livstidskostnaderna för maskiner både i termer av materialavfall och användning. Avhandlingen "Konstruktion av viktoptimerad gjuten ADI-komponent" behandlar omkonstruktionen av en komponent från en svetsad stålplåtstruktur till en gjutbar konstruktion med minskad tillverkningskostnad och vikt. Komponenten “Borrstöd” monterad i framkant av bommen på en ortdrivningsmaskin är omkonstruerad under detta arbete. Huvudsyftet med avhandlingen är ta fram en alternativ konstruktion med lägre vikt och som kan monteras på befintlig maskinlayout utan någon ändring i monteringsgränssnittet. Denna avhandling innehåller en detaljerad beskrivning av förfarandet för att uppnå viktminskningen av "borrstödet" och presenterar resultaten samt metodiken som baseras på både topologi- och parameter- optimering.

It is important to understand the aerodynamic properties of tensioned cables (e.g. used in suspension bridges and yacht riggings), both for drag reduction and vibrational suppression purposes. In this study, the cross-sectional shape and surface structure of solid cables were investigated in order to improve the performance of sailing racing yachts. The apparent wind angle range 15-60° was identified as the most important for drag reduction. Thereafter, the aerodynamic properties of different shapes and surfaces were investigated in the Reynolds number range 5 x 10^3 ≤ Re ≤ 4 x 10^4, by performing computational fluid dynamics simulations and wind tunnel tests (the aerodynamic forces were measured using load cells). No significant effect of changing the surface roughness could be found for the investigated Reynolds number range. The results were compared to literature values for validation. Elliptical shapes with a fineness ratio between 1:1-3:1, together with three complex shapes, were tested. It could be shown that the largest performance gain was obtained for cables with more sail-like aerodynamic properties (for apparent wind angles below 90° a large lift/drag ratio is sought). This study was performed in collaboration with Carbo-Link AG, as an outlook, the manufacturability of carbon fiber reinforced polymer cables in the most aerodynamically efficient shape was explored.

In the past decades of years, huge amounts of people chose to move to big cities for better education and medical service, which also makes many cities are very crowded and noisy. Moreover, the house rent in city center is some kind too expensive for many people, especially for the youth. In this sense, more people are willing to live in suburb instead of city center. Due to the larger distance between home and office, people’s requirement for a faster public transportation method is enormous. Elon Musk first publicly mentioned the concept of Hyperloop in 2012[1], which is a sealed tube or system of tubes with nearly vacuum condition through which a pod can transport people or objects at super high velocity. With the linear induction motor and magnetic levitation technology, the drag force on the pod can be reduced tremendously, thus increasing the peak velocity to 1200 km/h. To gather more ideas for this concept, SpaceX holds the Hyperloop Pod Competition where worldwide teams will design their own Hyperloop pod to demonstrate their technical feasibility of new ideas [2]. A Hyperloop system is currently in development by the Integrated Transport Research Lab (ITRL) at KTH Royal Institute of Technology to participate in the upcoming Hyperloop Pod Competition. KTH Hyperloop group has some primary design of chassis and shell. However, they have no idea how good of their current design is. Furthermore, since the velocity is the only criteria for this competition, they also want to reduce the mass as much as possible. In this sense, some finite element analysis and optimization analysis are necessary. The objective of this master’s thesis is to analyze the current shell and chassis design to assess the quality of the attachments and integrity of the design and to reduce the total mass while keeping the stiffness within the safety range. The used tools are HyperMesh, Optistruct and HyperView which are parts of the software HyperWorks from Altair. / Ett Hyperloop-system utvecklas för närvarande av Integrated Transport Research Lab (ITRL) vid KTH Royal Institute of Technology för att delta i den kommande Hyperloop Pod-tävlingen. Hyperloop-gruppen vid KTH har utvecklat en primärkonstruktion av chassi och skal. De har dock ingen aning om hur bra deras nuvarande design är. Eftersom hastigheten är de enda kriterierna för denna tävling, vill de också minska massan så mycket som möjligt. I detta avseende är det nödvändigt med finita element- och optimeringsanalyser. Syftet med denna masteruppsats är att analysera den aktuella skal- och chassikonstruktionen för att utvärdera kvaliteten på dess fästen och integriteten hos designen, samt att minska den totala massan samtidigt som styvheten uppfyller specificerat krav. De använda verktygen är HyperMesh, Optistruct och HyperView som är delar av programvaran HyperWorks från Altair.