Les ensembles turbo-alternateurs des centrales électriques sont de grandes machines tournantes de plus de 50 mètres de long et de plusieurs centaines de tonnes. Lors du fonctionnement normal d'une telle machine, une probabilité non nulle existe d'un détachement accidentel d'une aube. Dans une telle situation, un balourd important est généré et du contact apparaît entre les parties tournantes et non tournantes de la machine. Il est alors capital de pouvoir simuler efficacement la dynamique de ce type d'évènement faisant intervenir de fortes non linéarités dans le système. Cette thèse a été réalisée dans le cadre du projet ANR (Agence Nationale de la Recherche) IRINA (SImulation et maîtRise des rIsques en coNception des mAchines tournantes) et en particulier entre le LaMCoS (LAboratoire de Mécanique des Contacts et des Structures) de l'INSA de Lyon et le département AMA (Analyses Mécaniques et Acoustiques) d'EDF R et D à Clamart. Elle a pour objectif de mettre au point une technique rapide de simulation du comportement des lignes d'arbres de machines tournantes en cas de présence de non linéarité de type contact entre rotor et stator. Pour atteindre cet objectif, une double démarche a été mise en place. La première consiste à mettre au point des modèles simplifiés afin de réduire le nombre de degrés de liberté du problème. De surcroît, une technique de réduction de modèle adaptée au cas de non linéarité localisée est utilisée afin de réduire encore plus la taille du système à résoudre. La seconde démarche consiste à mettre au point une technique de résolution rapide du système réduit afin d'obtenir la solution encore plus rapidement. Pour cela, au lieu d'utiliser les traditionnelles techniques d'intégration temporelle directe, c'est la méthode de la balance harmonique qui est mise à profit. Cette technique permet d'obtenir directement la réponse stabilisée du système grâce à une résolution des équations dans le domaine fréquentiel. Dans ce cadre, une maquette numérique a été mise au point mettant en oeuvre les fonctionnalités citées. Cette dernière permet de reproduire les phénomènes physiques périodiques ainsi que quasi-périodiques et de déterminer leur stabilité. Des études paramétriques sur des exemples de problèmes de contact rotor-stator viennent illustrer cette démarche. Enfin, une application sur un cas industriel de groupe turbo alternateur EDF est présentée.

Chirality is a nuclear symmetry which is suggested to occur in nuclei when the total angular momentum of the system has an aplanar orientation [Fra97, Fra01]. It can occur for nuclei with triaxial shape, which have valence protons and neutrons with predominantly particle and hole nature. It is expected that the angular momenta of an odd particle and an odd hole (both occupying high-j orbitals) are aligned predominantly along the short and the long axes of the nucleus respectively, whereas the collective rotation occurs predominantly around the intermediate axis of a triaxially deformed nucleus in order to minimize the total energy of the system. Such symmetry is expected to be exhibited by a pair of degenerate DI = 1 rotational bands, i.e. all properties of the partner bands should be identical. The results suggested that spin independence of the energy staggering parameter S(I ) within two-quasiparticle chiral bands (previously suggested a fingerprint of chirality) is found only if the Coriolis interaction can be completely neglected. However, if the configuration is nonrestricted, the Coriolis interaction is often strong enough to create considerable energy staggering. It was also found that staggering in the intra- and inter-band B(M1) reduced transition probabilities (proposed as another fingerprint of chirality) may be a result of effects other than strongly broken chirality. Therefore, the use of the B(M1) staggering as a fingerprint of strongly broken chiral symmetry seems rather risky, in particular if the phase of the staggering is not checked.

The present work is a result of collaboration between the LMFA (Laboratoire de Mécanique des Fluides et d'Acoustique, Ecole Centrale de Lyon - France), Snecma and the Cerfacs. It aims at studying the flow in the 3.5-stages high-speed axial compressor CREATE (Compresseur de Recherche pour l'Etude des effets Aérodynamique et TEchnologique - rotation speed: 11543 RPM, Rotor 1 tip speed: 313 m/s), designed and built by Snecma and investigated at LMFA on a 2-MW test rig. Steady measurements, as well as laser velocimetry, fast-response wall static and total pressure measurements have been used to experimentally investigate the flow. The analysis focuses on two main aspects: the study of the flow at stable operating points, with a special interest on the rotor-stator interactions, and the study of the instabilities arising in the machine at low mass flow rates.The description of the unsteady flow field at stable operating points is done through measurements of wall-static pressure, total pressure and velocity, but also total temperature, entropy and angle of the fluid. It is shown that the complexity and unsteadiness of the flow in a multistage compressor strongly increases in the rear part of the machine, because of the interactions between steady and rotating rows. Therefore, a modal analysis method developed at LMFA and based on the decomposition of Tyler and Sofrin is presented to analyze these interactions. It is first applied to the pressure measurements, in order to extract the contributions of each row. It shows that all the complex pressure interactions in CREATE can be reduced to three main types of interactions. The decomposition method is then applied to the entropy field extracted from URANS CFD calculations performed by the Cerfacs, in order to evaluate the impact of the interactions on the performance of the machine in term of production of losses.The last part of this work is devoted to the analysis of the instabilities arising in CREATE at low mass flows. It shows that rotating pressure waves appear at stable operating points, and increase in amplitude when going towards the surge line, until reaching a critical size provoking the onset a full span stall cell bringing the machine to surge within a few rotor revolutions. The study of these pressure waves, and the understanding of their true nature is achieved through the experimental results and the use of some analytical models. A precise description of the surge transient through wall-static pressure measurements above the rotors is also provided, as well as a description of a complete surge cycle. An anti-surge control system based on the detection of the amplitude of the pressure waves is finally proposed.

L'écoulement dans les turbomachines est tri-dimensionnel et instationnaire. Actuellement, les concepteurs de moteurs cherchent à réduire l'encombrement et le poids des machines. En conséquence, les interactions entre les roues, appelées interactions rotor-stator, sont renforcées. Parmi elles, l'effet potentiel remontant n'est désormais plus négligeable malgré sa rapide atténuation spatiale. Dans cette étude, cet effet potentiel remontant a été analysé sur une configuration spécialement conçue : une grille linéaire d'aubes de turbine, suivie de barreaux défilants en aval à une distance de 20% de corde axiale, simulant des aubes de rotor en aval. La grande échelle du banc d'essais facilite l'étude du comportement de la couche limite des aubes de la grille. Des mesures de pression et d'anémométrie laser à deux composantes, synchronisées avec le défilement des barreaux aval sont réalisées. Le nombre de Reynolds, basé sur la corde, est 1.6 × 105. Une grille de turbulence placée en amont de la grille d'Aube afin de pouvoir augmenter le taux de turbulence amont a été utilisée. Des résultats de mesures en absence de cette grille (faible taux de turbulence amont) sont également présentés et analysés. Une modélisation numérique, basée sur un calcul laminaire avec un préconditionnement basse vitesse pour la même configuration, a montré la déformation des lignes de courant de l'écoulement dans le canal inter-aubes, en fonction de la position du barreau aval. La distribution de pression autour de l'aube est également périodiquement modifiée. Les résultats stationnaires expérimentaux, en absence de tout barreau aval, ont révélé un décollement de la couche limite à l'extrados de l'aube à bas taux de turbulence amont(Tu−am = 1.2%) qui est supprimé à haut taux de turbulence amont (Tu−am = 4.2%) ; la couche limite commence alors sa transition par un mode by-pass. Aucun effet instationnaire dans la couche limite n'a été observé à l'intrados, quel que soit le taux de turbulence amont. L'étude instationnaire, avec le défilement des barreaux en aval, a permis de mettre en évidence un décollement périodique de la couche limite à l'extrados à bas taux de turbulence amont (Tu−am = 1.8%). Dans ce cas, la couche limite suit deux modes de transition au cours d'une période : une transition par décollement et une transition bypass. Au contraire, dans le cas à fort taux de turbulence amont (Tu−am = 4.0%), aucun décollement de la couche limite n'a été décelé. La couche limite est sujette à l'effet instationnaire à l'extrados. Elle est devenue turbulente au bord de fuite à tout instant par un mode by-pass. Cette étude a montré que l'effet potentiel issu d'un roue en aval est du même ordre de grandeur que les effets de sillage et doit être pris en compte dans l'analyse des phénomènes. Par des méthodes d'indexation de roues, le décollement de la couche limite pourrait être supprimé.

A Computational Fluid Dynamics/Computational Fluid Dynamics (CFD/CSD) coupling interface was developed to obtain aeroelastic solutions of a morphing rotor. The methodology was implemented in Fully Unstructured Navier-Stokes (FUN3D) solver, which communicates aerodynamic forces on the blade surface to University of Michigan’s Nonlinear Active Beam Solver (UM/NLABS) and then imports structural deflections of the blade surface during each time step. Development of this methodology adds the capability to model elastic rotors with flexible airfoils. The method was validated through an aerodynamic work analysis, comparison of sectional blade loads and deflections with experimental data, and two-dimensional stability analyses for pitch/plunge flutter and camber flutter. Computational simulations were performed for a rotor in forward flight with the CFD/CSD solver and with a comprehensive CSD solver using finite-state (F-S) aerodynamics, and results were compared. Prescribed three-per-revolution camber deflections were then applied, and solutions of the CFD/CSD and comprehensive CSD computations indicated that three-per-revolution camber actuation has the potential to minimize hub forces and moments with deflections as small as 0.25%c. In anticipation of active rotor experiments inside enclosed facilities, the capability of CFD for accurately simulating flow inside enclosed volumes was examined. It was determined that URANS models are not suitable for rotor simulations in an enclosed facility, and components that are a distance of two to three rotor radii from the hub were also observed to have a large influence on recirculation and performance.

This study is devoted to the development of moderate-cost methodologies for the aerodynamic simulation of open rotors. The main goals are, on one side, to develop and validate these rapid methodologies, and, on the other side, to better understand the mechanisms behind propeller in-plane loads, also called the 1P loads. To reach the first goal, the HOST-MINT code, based on the lifting-line theory, has been adapted and improved for the unsteady simulation of propellers and open rotors. The code has been assessed by comparison with experimental data and more complex and precise CFD simulations. Finally, the first developments and tests of a Lagrangian/Eulerian coupling strategy between HOST-MINT and the elsA CFD code have been performed. These studies enable to endeavor a number of applications of this type of rapid methodologies in the aerodynamic design of future open rotors. Moreover, these methodologies may be adapted for other domains linked to aerodynamics, such as aeroelastic problems or preliminary aeroacoustic predictions.

Dans le contexte du développement des machines moléculaires, l'objet de ce travail est la synthèse de solides cristallins amphidynamiques basés sur des rotors 1,4-diéthynylbicyclo[2.2.2]octane (BCO) fonctionnels, auto-assemblés ou organisés par coordination à un métal. Ces rotors chiraux possèdent deux degrés de liberté caractérisés à l'état solide de deux manières indépendantes. Des expériences de relaxation spin-réseau du proton en fonction de la température pour étudier le mouvement de rotation du rotor hélicoïdal sur son axe ont été réalisées. De plus, des expériences d'optique non-linéaire ont mis en évidence la génération d'un signal de seconde harmonique, conséquente au mouvement de torsion des pales de l'hélice au sein de 'mutamères'. Les expériences de RMN du solide, réalisées sur des échantillons polycristallins statiques (barrières expérimentales de rotation et fréquence des sauts stochastiques du BCO) ont été couplées à des calculs d'énergie d'interaction des rotors avec leur environnement (barrières de rotation). Nous avons montré qu'il est possible d'interpréter la dynamique au sein de ces systèmes et notamment la très grande influence des liaisons hydrogènes au sein de l'environnement proche de la partie mobile sur la rotation du rotor. En parallèle, des expériences d'optique non linéaire sur monocristal ont mis en évidence la brisure de symétrie d'inversion de l'espace inhérente au changement de configuration hélice-gauche / hélice-droite du BCO. Dans le but d'exploiter cette propriété optique singulière, des stratégies de synthèse organique et d'ingénierie cristalline ont été mises en place afin de diriger l'orientation des rotors lors de leur assemblage au sein des matériaux. Cela permet d'obtenir des objets pour lesquels la présence d'une réponse en optique non-linéaire est directement corrélée à la dimensionnalité du système étudié.

The McTronX research group at the North–West University designs and develops Active Magnetic Bearings (AMBs). The group’s focus shifted to the design and development of AMB supported drive systems. This includes the electromagnetic and mechanical design of the electric machine, AMBs, auxiliary bearings as well as the development of the control system. The research group is currently developing an AMB supported high speed Induction Machine (IM) drive system that will facilitate tests in order to verify the design capability of the group. The research presented in this thesis describes the mechanical design and manufacturing of a high speed IM rotor section. The design includes; selecting the IM rotor topology, material selection, detail stress analysis and selecting appropriate manufacturing and assembly procedures. A comprehensive literature study identifies six main design considerations during the mechanical design of a high speed IM rotor section. These considerations include; magnetic core selection, rotor cage design, shaft design, shaft/magnetic core connection, stress due to operation at elevated temperatures and design for manufacture and assemble (DFMA). A critical overview of the literature leads to some design decisions being made and is used as a starting point for the detail design. The design choices include using a laminated cage rotor with a shrink fit for the shaft/magnetic core connection. Throughout the detail design an iterative process was followed incorporating both electromagnetic and mechanical considerations to deliver a good design solution. The first step of the iterative design process was, roughly calculating the material strengths required for first iteration material selection followed by more detailed interference fit calculations. From the detail stress analysis it became apparent that the stress in the IM rotor section cannot be calculated accurately using analytical methods. Consequently, a systematically verified and validated Finite Element Analysis (FEA) model was used to calculate the interferences required for each component. The detail stress analysis of the assembly also determined the allowable manufacturing dimensional tolerances. From the detail stress analysis it was found that the available lamination and squirrel cage material strengths were inadequate for the design speed specification of 27,000 r/min. The analysis showed that a maximum operating speed of 19,000 r/min can be achieved while complying with the minimum factor of safety (FOS) of 2. Each component was manufactured to the prescribed dimensional tolerances and the IM rotor section was assembled. With the failure of the first assembly process, machine experts were consulted and a revised process was implemented. The revised process entailed manufacturing five small lamination stacks and assembling the stack and squirrel cage afterwards. The end ring/conductive bar connection utilises interference fits due to the fact that the materials could not be welded. The process was successful and the IM rotor section was shrink fitted onto the shaft. However, after final machining of the rotor’s outer diameter (OD), inspections revealed axial displacement of the end rings and a revised FEA was implemented to simulate the effect. The results indicated a minimum FOS 0.6 at very small sections and with further analytical investigation it was shown that the minimum FOS was reduced to only 1.34. Although the calculations indicated the FOS was below the minimum prescribed FOS ? 2, the rotor spin tests were scheduled to continue as planned. The main reasons being that the lowest FOS is at very small areas and is located at non critical structural positions. The fact that the rotor speed was incrementally increased and multiple parameters were monitored, which could detect early signs of failure, further supported the decision. In testing the rotor was successfully spun up to 19,000 r/min and 27 rotor delevitation test were conducted at speeds of up to 10,000 r/min. After continuous testing a secondary rotor inspection was conducted and no visible changes could be detected. The lessons learnt leads to mechanical design and manufacturing recommendations and the research required to realise a 27,000 r/min rotor design. / Thesis (M.Ing. (Mechanical Engineering))--North-West University, Potchefstroom Campus, 2011.

The McTronX research group at the North–West University designs and develops Active Magnetic Bearings (AMBs). The group’s focus shifted to the design and development of AMB supported drive systems. This includes the electromagnetic and mechanical design of the electric machine, AMBs, auxiliary bearings as well as the development of the control system. The research group is currently developing an AMB supported high speed Induction Machine (IM) drive system that will facilitate tests in order to verify the design capability of the group. The research presented in this thesis describes the mechanical design and manufacturing of a high speed IM rotor section. The design includes; selecting the IM rotor topology, material selection, detail stress analysis and selecting appropriate manufacturing and assembly procedures. A comprehensive literature study identifies six main design considerations during the mechanical design of a high speed IM rotor section. These considerations include; magnetic core selection, rotor cage design, shaft design, shaft/magnetic core connection, stress due to operation at elevated temperatures and design for manufacture and assemble (DFMA). A critical overview of the literature leads to some design decisions being made and is used as a starting point for the detail design. The design choices include using a laminated cage rotor with a shrink fit for the shaft/magnetic core connection. Throughout the detail design an iterative process was followed incorporating both electromagnetic and mechanical considerations to deliver a good design solution. The first step of the iterative design process was, roughly calculating the material strengths required for first iteration material selection followed by more detailed interference fit calculations. From the detail stress analysis it became apparent that the stress in the IM rotor section cannot be calculated accurately using analytical methods. Consequently, a systematically verified and validated Finite Element Analysis (FEA) model was used to calculate the interferences required for each component. The detail stress analysis of the assembly also determined the allowable manufacturing dimensional tolerances. From the detail stress analysis it was found that the available lamination and squirrel cage material strengths were inadequate for the design speed specification of 27,000 r/min. The analysis showed that a maximum operating speed of 19,000 r/min can be achieved while complying with the minimum factor of safety (FOS) of 2. Each component was manufactured to the prescribed dimensional tolerances and the IM rotor section was assembled. With the failure of the first assembly process, machine experts were consulted and a revised process was implemented. The revised process entailed manufacturing five small lamination stacks and assembling the stack and squirrel cage afterwards. The end ring/conductive bar connection utilises interference fits due to the fact that the materials could not be welded. The process was successful and the IM rotor section was shrink fitted onto the shaft. However, after final machining of the rotor’s outer diameter (OD), inspections revealed axial displacement of the end rings and a revised FEA was implemented to simulate the effect. The results indicated a minimum FOS 0.6 at very small sections and with further analytical investigation it was shown that the minimum FOS was reduced to only 1.34. Although the calculations indicated the FOS was below the minimum prescribed FOS ? 2, the rotor spin tests were scheduled to continue as planned. The main reasons being that the lowest FOS is at very small areas and is located at non critical structural positions. The fact that the rotor speed was incrementally increased and multiple parameters were monitored, which could detect early signs of failure, further supported the decision. In testing the rotor was successfully spun up to 19,000 r/min and 27 rotor delevitation test were conducted at speeds of up to 10,000 r/min. After continuous testing a secondary rotor inspection was conducted and no visible changes could be detected. The lessons learnt leads to mechanical design and manufacturing recommendations and the research required to realise a 27,000 r/min rotor design. / Thesis (M.Ing. (Mechanical Engineering))--North-West University, Potchefstroom Campus, 2011.

Three-dimensional design and three-dimensional CFD analysis of a compressor rotor stage are performed. The design methodology followed is based on a mean line analysis and a radial equilibrium phase. The radial equilibrium is established at a selected number of radii. NACA 65 series airfoils are selected and stacked according to the experimental data available. The CFD methodology applied is based on a three-dimensional, finite difference, compressible flow Euler solver that includes the source terms belonging to rotational motion. The accuracy of the solver is shown by making use of two different test cases. The CFD solution of the designed geometry predicts the static pressure rises and flow turning angles to a good degree of accuracy.