Rotordynamic instability can be disastrous for the operation of high speed turbomachinery in the industry. Most ??instabilities?? are due to de-stabilizing cross coupled forces from variable fluid dynamic pressure around a rotor component, acting in the direction of the forward whirl and causing subsynchronous orbiting of the rotor. However, all subsynchronous whirling is not unstable and methods to diagnose the potentially unstable kind are critical to the health of the rotor-bearing system. The objective of this thesis is to explore means of diagnosing whether subsynchronous vibrations are benign or have the potential to become unstable. Several methods will be detailed to draw lines of demarcation between the two. Considerable focus of the research has been on subharmonic vibrations induced from non-linear bearing stiffness and the study of vibration signals typical to such cases. An analytical model of a short-rigid rotor with stiffness non-linearity is used for numerical simulations and the results are verified with actual experiments. Orbits filtered at the subsynchronous frequency are shown as a diagnostic tool to indicate benign vibrations as well as ??frequency tracking?? and agreement of the frequency with known eigenvalues. Several test rigs are utilized to practically demonstrate the above conclusions. A remarkable finding has been the possibility of diagnosing instability using the synchronous phase angle. The synchronous phase angle ?? is the angle by which the unbalance vector leads the vibration vector. Experiments have proved that ?? changes appreciably when there is a de-stabilizing cross coupled force acting on the rotor as compared to when there is none. A special technique to calculate the change in ?? with cross-coupling is outlined along with empirical results to exemplify the case. Subsequently, a correlation between the synchronous phase angle and the phase angle measured with most industrial balancing instruments is derived so that the actual measurement of the true phase angle is not a necessity for diagnosis. Requirements of advanced signal analysis techniques have led to the development of an extremely powerful rotordynamic measurement teststand ?? ??LVTRC??. The software was developed in tandem with this thesis project. It is a stand-alone application that can be used for field measurements and analysis by turbomachinery companies.

The turbine blade platform can be protected from hot mainstream gases by injecting cooler air through the gap between stator and rotor. The effectiveness of this film cooling method depends on the geometry of the slot, the quantity of injected air, and the secondary flows near the platform. The purpose of this study was to measure the effect of the upstream vane or stator on this type of platform cooling, as well as the effect of changes in the width of the gap. Film cooling effectiveness distributions were obtained on a turbine blade platform within a linear cascade with upstream slot injection. The width of the slot was varied as well as the mass flow rate of the injected coolant. Obstacles were placed upstream to model the effect of the upstream vane. The coolant was injected through an advanced labyrinth seal to simulate purge flow through a stator-rotor seal. The width of the opening of this seal was varied to simulate the effect of misalignment. Stationary rods were placed upstream of the cascade in four phase locations to model the unsteady wake formed at the trailing edge of the upstream vane. Delta wings were also placed in four positions to create a vortex similar to the passage vortex at the exit of the vane. The film cooling effectiveness distributions were measured using pressure-sensitive paint (PSP). Reducing the width of the slot was found to decrease the area of coolant coverage, although the film cooling effectiveness close to the slot was slightly increased. The unsteady wake was found to have a trivial effect on platform cooling, while the passage vortex from the upstream vane may significantly reduce the film cooling effectiveness.

Rotordynamic instability can be disastrous for the operation of high speed turbomachinery in the industry. Most ??instabilities?? are due to de-stabilizing cross coupled forces from variable fluid dynamic pressure around a rotor component, acting in the direction of the forward whirl and causing subsynchronous orbiting of the rotor. However, all subsynchronous whirling is not unstable and methods to diagnose the potentially unstable kind are critical to the health of the rotor-bearing system. The objective of this thesis is to explore means of diagnosing whether subsynchronous vibrations are benign or have the potential to become unstable. Several methods will be detailed to draw lines of demarcation between the two. Considerable focus of the research has been on subharmonic vibrations induced from non-linear bearing stiffness and the study of vibration signals typical to such cases. An analytical model of a short-rigid rotor with stiffness non-linearity is used for numerical simulations and the results are verified with actual experiments. Orbits filtered at the subsynchronous frequency are shown as a diagnostic tool to indicate benign vibrations as well as ??frequency tracking?? and agreement of the frequency with known eigenvalues. Several test rigs are utilized to practically demonstrate the above conclusions. A remarkable finding has been the possibility of diagnosing instability using the synchronous phase angle. The synchronous phase angle ?? is the angle by which the unbalance vector leads the vibration vector. Experiments have proved that ?? changes appreciably when there is a de-stabilizing cross coupled force acting on the rotor as compared to when there is none. A special technique to calculate the change in ?? with cross-coupling is outlined along with empirical results to exemplify the case. Subsequently, a correlation between the synchronous phase angle and the phase angle measured with most industrial balancing instruments is derived so that the actual measurement of the true phase angle is not a necessity for diagnosis. Requirements of advanced signal analysis techniques have led to the development of an extremely powerful rotordynamic measurement teststand ?? ??LVTRC??. The software was developed in tandem with this thesis project. It is a stand-alone application that can be used for field measurements and analysis by turbomachinery companies.

L’utilisation de revêtements abradables pour assurer l’étanchéité dynamique des turboréacteurs est une solution répandue qui permet d’augmenter la fiabilité et le rendement aérodynamique des turboréacteurs. En fonctionnement, des touches inévitables entre le revêtement et le bout d’aubes de rotor peuvent être à l’origine d’une usure excessive du revêtement abradable et/ou de la rupture d’aube. La simulation numérique de tels incidents butte sur un manque de connaissance des interactions aube/carter et des forces mises en jeu au contact, forces qui résultent notamment de couplages entre le frottement, l’usure du revêtement et des phénomènes vibratoires.Cette thèse a pour objectif de mieux appréhender les mécanismes d’interaction entre l’aube et le revêtement abradable. Elle résulte d’une collaboration entre l’ONERA de Lille et le Laboratoire de Mécanique de Lille et concerne le revêtement de type Al-Si/hbN (Metco 320NS), couramment utilisé dans les compresseurs à basse pression.Les propriétés physico-chimiques et le comportement mécanique – notamment en dynamique – du revêtement abradable sont étudiés. Compte-tenu d’une asymétrie du comportement en traction et en compression, l’exploitation en corrélation d’images numériques d’un essai original inspiré de l’essai Brésilien permet de rendre compte des mécanismes de dégradation. Le comportement tribologique est étudié sur tribomètre dans différentes configurations de contact. L’interaction entre l’aube et le revêtement ainsi que les couplages avec les vibrations d’aube sont investigués et caractérisés dans une configuration simplifiée et fortement instrumentée, sur un banc rotatif spécifique développé à l’ONERA de Lille / Abradable seals are extensively used in jet engines to ensure smaller rotor/stator dynamic clearances and lead to higher aerodynamic efficiencies. However, the resulting reduced rotor/stator gap can cause excessive seal wear and/or a significant increase in rotor blades solicitation, both of which can be highly detrimental to the engine’s structural integrity. To allow numerical modelling of such accidental scenarios, there is a need to better comprehend the blade/seal interactions as well as the contact forces involved and that can be influenced by the couplings occurring between friction, seal wear and blade vibration.This thesis aims at contributing to a better understanding of the blade/seal interaction mechanisms, in the framework of a cooperation between ONERA de Lille and the Laboratoire de Mécanique de Lille. The abradable material is of Al-Si/hBN type (Metco 320NS), commonly used in low pressure compressors. The physicochemical properties and the mechanical behaviour – under static and dynamic loading – of this abradable material are tested. Given the anti-symmetry of its tension and compression behaviour, use of the Digital Image Correlation technique to analyze an experiment derived from the Brazilian test allows qualification of the damage mechanisms. The friction behaviour of the abradable seal is studied on a tribometer using different contact configurations. Characterisation of the blade/seal interaction and of some of the associated coupling phenomena is done on a dedicated and instrumented device developed at ONERA de Lille

The sustainability, smooth operation and operational life of rotating machinery significantly rely on the techniques that detect the symptoms of incipient faults. Among the faults in rotating systems, the presence of a crack is one of the most dangerous faults that dramatically decreases the safety and operational life of the rotating systems, thereby leading to catastrophic failure and potential injury to personnel if it is undetected. Although many valuable techniques and models have been developed to identify a crack (or cracks) in stationary and rotating systems, finding an efficient technique (or model) that can identify a unique vibration signature of the cracked rotor is still a great challenge in this field. This is because of the unceasing necessity to develop high performance rotating machines and driving towards significant reduction of the time and cost of maintenance. Most of the crack identification techniques and models in the available literature are based on vibration-based methods. The main idea of the vibration-based method is that the presence of a crack in a rotor induces a change in the mass, damping, and stiffness of the rotor, and consequently detectable changes appear in the modal properties (natural frequencies, modal damping, and mode shapes). Among all these modal properties, the choice of the modal natural frequency change is more attractive as a tool for crack identification. The changes in natural frequencies due to a crack can be conveniently measured from just a few accessible points on the cracked rotor. Furthermore, measuring the natural frequencies does not require expensive measuring instruments, and the natural frequency data is normally less contaminated by experimental noise. However, the change that a crack induces in the natural frequencies is usually very small and can be buried in the ambient noise. Moreover, the natural frequencies are not affected if the crack is located at the nodes of modes or far from the location of inertia force and out-of-unbalance force that the disc generates in the shaft. To overcome these problems (or limitations), therefore, this study is conducted using the idea of the roving mass (roving disc in rotor case). The modal natural frequencies are used for the identification and location of cracks of various severities at different locations in both stationary and rotating shafts. The fundamental idea of the roving disc is that an extra inertia force is traversed along the cracked rotor to significantly excite the dynamics of the rotor near the crack locations. In other words, the location of a crack can be anywhere on the shaft which is contrary to the developed techniques in the available literature in which the location of a crack should be close to the disc. Along with the roving disc idea, three crack identification techniques are developed in this study using the natural frequencies of the cracked and intact shafts. Each of these techniques has its merits and limitations for crack identification. These techniques are implemented using data that are numerically generated by the finite element method based on the Bernoulli-Euler shaft elements and experimentally validated in the laboratory environment. The numerical and experimental results clearly demonstrate the capability of the suggested approach for the identification and location of cracks in stationary and rotating shafts.

Le coût, l'autonomie et la durée de vie sont les principaux aspects qui freine le public dans l'achat d'une voiture électrique. Tous ces aspects sont liés à la batterie qui ne permet de stocker qu'une quantité limitée d'énergie. Dans ces conditions, il est indispensable de maîtriser les pertes d'énergie de la chaîne de traction. La machine électrique étant le principal consommateur d'énergie, elle joue un rôle important dans l'efficacité énergétique globale. Dans ce contexte, comment réduire les pertes de la machine électrique pour la rendre plus efficace ? Pour répondre à cette question, l'objectif de ce travail est de modéliser (avec une précision suffisante) et réduire les pertes fer dans notre application machine électrique de traction afin de les maîtriser. On comblera ainsi le manque de confiance en les modèles de pertes fer que peut avoir le concepteur de machine du concepteur de machine en lui permettant de réaliser des optimisations fines jusque dans les dernières phases de développement. Dans la première partie de ce manuscrit, le lecteur découvrira alors une machine synchrone à rotor bobiné du point de vue du matériau magnétique doux. Les premières conclusions montrent qu'une modélisation fine est nécessaire pour bien prendre en compte les phénomènes générateurs de pertes. On s'intéresse également à la mesure des matériaux magnétiques doux afin de comprendre de manière générale et tangible les pertes dans le matériau. On prend également conscience de la toute première source d'incertitude des modèles, la mesure du matériau. Enfin, nous présentons les démarches couramment rencontrées dans la littérature pour la modélisation des pertes fer. Face aux limitations des modèles couramment rencontrés, le modèle LS (un modèle d'hystérésis scalaire qui décompose les pertes en une contribution statique et une contribution dynamique) est redéveloppé afin qu'il réponde encore mieux aux exigences de l'industrie automobile. Il est précis et facilement identifiable à partir de mesures faciles à réaliser. La contribution statique reprend le modèle de Preisach formulé à l'aide des fonctions d'Everett dont l'identification à partir des caractéristiques mesurées est directe. La contribution dynamique quant à elle est dorénavant identifiable à partir de caractérisations en induction sinusoïdales. La précision du modèle ainsi améliorée est ensuite validée sur 63 cas tests exigeants dont la forme de l'induction est à fort contenus harmoniques. Le modèle développé est ensuite couplé avec un modèle électromagnétique élément finis de la machine électrique et validé par l'expérience. Les mesures faites sur le matériau étant l'un des points faibles des modèles, une méthodologie permettant d'évaluer la pertinence de la plage des mesures est proposée. On dresse également un état de l'art de l'impact du process (découpage, empilement et assemblage des tôles) sur les pertes fer afin d'aider le concepteur à mettre en balance les impacts liés au process qui n'ont pu être modélisés. Enfin des méthodologies parmi lesquels, les méthodologies des plans d'expériences sont mises en place afin d'optimiser les cartographies de commandes en des temps de calcul raisonnables. On montre des gains allant jusqu'à 50% de réduction des pertes totales de la machine dans certaines zones de fonctionnement par rapport à une optimisation dont l'objectif serait de minimiser uniquement les pertes dans les conducteurs de la machine. Ces résultats montrent l'intérêt d'utiliser un modèle de pertes fer précis afin de réduire les pertes totales de la machine. / Cost, range and lifetime are the main aspects that hold back the consumer to buy electric cars. These three aspects are all related to the battery which stores a limited amount of energy. Under such condition energy consumption is a major concern in electric cars. As the major electricity consumer, electrical machines play a key role for global energy savings. In this context how the electric machine can be made more energy efficient? To answer this question this thesis aim to model (accurately enough) and reduce the iron losses in traction electrical machine for electrical car. Indeed iron loss model suffer from a lack of confidence when it comes to fine optimization during the late phase of development. This thesis answers this question and takes into account the development criteria of the car industry and the constraints of the electric car. The first part of the thesis gives an overview of the application by taking a wounded rotor synchronous machine as a case study. The reader will discover the electrical machine with a soft magnetic material perspective. First, conclusion show that fine modelling of the electric machine is necessary to achieve desired accuracy. An overview on soft magnetic material behavior and measurements is then given. The reader will then acquire a broad feeling on soft magnetic material behavior and understands the first source of inaccuracy of the models (the measurements). Then, the typical models for predicting iron losses in magnetic materials are presented in a literature review. The second part of this study focus on iron loss modelling aspect. The loss surface model (a scalar hysteresis model made of a static and dynamic contribution) is used as the base of this modelling work. The static contribution is re-developed using Everett function formulation of the Preisach model is used to allow easy identification of the model directly from measurements. The identification of the dynamic contribution is re-worked to allow identification from sine-wave measurements (triangular wave measurement previously required). The model accuracy is improved and validated on 63 test cases with high harmonic distortion wave forms. The iron loss model is then coupled to finite element model of the electric machine and the limits of the model are investigated. One of the limits coming from measurement limitation, a methodology to evaluate the relevance of the measurement range is proposed. A literature review of the main impact of the process including cutting, stacking and assembling effects on electrical steel magnetic characteristics is intended to complement the modelling work to help the decision making of the designer on aspects that cannot be modeled. Finally methodologies playing with the modelling hypothesis and involving design of experiment and response surface are presented to reduce computational time and allow the optimization of the control of the machine. The optimizations carried out show total machine loss reduction up to 50% for some working point of the machine compared to an optimization dedicated to minimize only Joule's losses. This results show the interest of using a reliable iron loss model to reduce the total loss of the machine.

Este trabalho apresenta a simulação numérica do escoamento turbulento em torno de uma turbina eólica de eixo vertical de pequeno porte, Savonius tipo helicoidal com torção de 180° nas pás. Com o intuito de avaliar a metodologia computacional empregada os resultados numéricos obtidos são comparados com os resultados experimental e numérico contidos no estado da arte. Também, compara-se o coeficiente de toque da turbina Savonius helicoidal com a turbina Savonius convencional. As simulações numéricas são baseadas no Método de Volumes Finitos, e para tal emprega-se o programa Fluent /Ansys versão 13.0 que resolve as equações da continuidade e as equações de Navier-Stokes com médias de Reynolds, juntamente com o modelo de turbulência . As simulações são desenvolvidas empregando diferentes malhas computacionais em estudos transientes, tridimensionais, com a turbina estacionária. A avaliação da qualidade da malha é realizada através do método de Índice de Convergência de Malha (GCI) o qual analisa o quão longe os resultados estão da solução assintótica para a malha utilizada. Após a análise da qualidade de malha, realizam-se simulações com a turbina em rotação as quais fazem uso da malha contendo uma região móvel possibilitando a imposição de uma velocidade angular ao rotor. O coeficiente de torque é obtido nas simulações e a partir dele calcula-se o coeficiente de potência. Além da análise do desempenho do rotor realiza-se uma análise qualitativa das características do escoamento sobre a turbina. A turbina Savonius helicoidal apresenta um valor de coeficiente de potência de 0,175 para a razão de velocidade de ponta de 0,58 considerando correção do efeito de bloqueio. Os resultados obtidos apresentam boa concordância com os resultados publicados por outros autores. / This dissertation presents the numerical simulation of the turbulent flow around of a small sized vertical axis wind turbine, consisting in a helical Savonius type with a 180° degree of blade twist. In order to evaluate the used methodology the obtained results are compared with the state of the art numerical and experimental data. It will be also presented the comparison between the torque coefficient of the conventional Savonius turbine and the helical Savonius turbine. The numerical simulations are based on the Finite Volume Method (FVM), using the commercial code Fluent/ANSYS version 13.0, which solves the continuity and Navier-Stokes through the Reynolds time-averaged methodology, including the turbulence model. The simulations are developed using different computational meshes for transient and three-dimensional studies with the stationary turbine. The evaluating the quality of the mesh is performed by of Grid Convergence Index (GCI) method which analyzes how far the results are the asymptotic solution to the mesh used. After the evaluation of the mesh quality, it was simulated a case considering the rotor motion using the moving mesh configuration, allowing the imposition of an angular velocity to the turbine. In the post-processing stage, it is possible to obtain the torque coefficient on the rotor shaft, allowing the calculation of the power coefficient for the turbine. In addition to the performance analysis, it is also made a qualitative analysis of the flow characteristics over the turbine rotor and in both cases presenting a good correspondence with the results in the literature. The helical Savonius turbine presents a value of power coefficient of 0.175 to a tip speed ratio of 0.58 whereas blocking effect correction.

Les motoristes aéronautiques souhaitent disposer de la représentation la plus fidèle possible du fonctionnement des propulseurs, dans une perspective d'amélioration continue de leurs performances. Les modèles numériques doivent donc intégrer au maximum les détails géométriques susceptibles d'influencer la physique de l'écoulement analysé. La prise en compte de tels effets technologiques s'avère difficile dans le contexte des solveurs structurés disponibles.Une stratégie hybride de prise en compte des effets technologiques fait coexister au sein d'un même domaine de calcul des zones structurées et non structurées. La flexibilité de génération d'un maillage non structuré permet une prise en compte aisée des détails géométriquement complexes tandis que la préservation de zones structurées dans une majeure partie du domaine de calcul permet de bénéficier de l'efficacité d'un solveur structuré. La présente thèse contribue au développement de cette stratégie hybride au sein du solveur elsA de l'ONERA en proposant des gains de précision et de robustesse par rapport à la version initialement développée pour établir la faisabilité et l'intérêt de l'approche. Après un état de l'art des techniques de discrétisation spatiale disponibles dans cette version initiale, différentes améliorations (techniques de moindres carrés, approche dite quasi-Green, méthode d'estimation des gradients aux faces) ont été analysées puis implémentées et validées sur des cas académiques. Le choix d'une stratégie hybride avec raccords coïncidents entre zones structurées et non-structurées conduit à des déformations de maillage dans la zone d'interface structuré / non-structuré qui ont exigé le développement supplémentaire de techniques d'amélioration de la robustesse (limiteurs physiques ou géométriques). Le solveur hybride rassemblant ces différentes fonctionnalités a permisde simuler avec succès des géométries d'aubes isolées dotées d'effets technologiques tels que congé de raccordement, trous de refroidissement, fentes de bord de fuite, cheminées internes d'alimentation. Enfin, une stratégie permettant l'utilisation de l'approche hybride en étage complet a été proposée et appliquée à la simulation hybride de l'interaction rotor/stator pour la configuration VKI-BRITE CT3, en stationnaire et en instationnaire, respectivement via une condition de plan de mélange et une condition de chorochronicité. / The aerospace engine manufacturers wish to rely on the most accurate description of their propulsion systems in order to continuously improve their performance levels. Therefore, numerical models must include as much as possible geometrical details likely to impact the physics of the flow under study. Taking into account such technological effects turns out to be a difficult task when working with available structured solvers. A hybrid strategy takes advantage of structured and unstructured zones within the same computational domain in order to efficiently describe technological effects. Geometrically complex local details are easily accounted for thanks to the flexibility of unstructured grid generation while keeping structured zones in the remainder of the flow domain allows to benefit from the tried and tested structured solver efficiency. The present work contributes to the development of such a hybrid strategy in ONERA elsA solver and enhances accuracy and robustness with respect to the solver initially developed to establish the feasibility and interest of hybridization. Following a review of the space discretization techniques available in the initial solver, several improvements (least square techniques, quasi-Green approach, computation of face gradients) have been analysed, then implemented and validated for academic test-cases. The choice of a hybrid strategy with coincident matching between structured and unstructured zones leads to highly deformed cells in the structured / unstructured interface region, requiring the development of supplementary robustness improvement techniques (physics- or geometry-based limiters). The hybrid solver gathering these various options allows to successfully compute isolated blade geometries including technological effects such as blade fillet, cooling holes, trailing edge cutbacks, internal coolant supply channel. Finally, a structured / unstructured strategy has been proposed and applied to the hybrid simulation of a rotor/stator interaction for the steady and unsteady

Les essais en environnement libre et en soufflerie ont été effectués pour étudier la performance propulsive et la déformation de pales de référence et de pales souples. La poussée et le couple ont été évalués par deux méthodes: une mesure directe par balance et une estimation indirecte par bilan de quantité de mouvement, les deux méthodes ayant leurs avantages et limitations respectifs. La méthode indirecte s’est construite sur l’acquisition de champs de vitesse obtenus par PIV et s’appuie sur une estimation de la pression par mise en œuvre de l’équation de Poisson. En vol stationnaire, les pales flexibles ne peuvent pas aider à l’amélioration du rendement en mode rotor (FM), à chargement faible, puisque la distribution de vrillage est sans doute assez éloignée de l’optimal de vol stationnaire. En vol avancé, le rendement propulsif des pales flexibles est la plupart du temps plus élevé que l’hélice rigide de référence en raison de la torsion bénéfique généré en rotation. Dans le cas des pales flexibles, la vitesse axiale se trouve être inférieure au cas rigide, à même station aval; ceci correspondant à la la déformation de vrillage négatif. Pour les deux pales, la différence de poussée entre celle déduite du champ PIV test 2et celle obtenue avec la balance est plus grande que la différence entre les valeurs déduites du champ PIV test 1 et de la mesure directe. La technique de mesure laser pour les déplacements(LDS) a été utilisée pour mesurer la déformation stationnaire des pales lors de leur rotation. Par analyse du nuage de points mesurés par la LDS, la flexion et la torsion de la lame en rotation ont été identifiées à l’aide des régressions multiples. / The wind tunnel tests were conducted to explore the performance difference caused by the potential twist deformation between baseline blades and flexible blades. The balance was built in SaBre wind tunnel for measuring the thrust and torque of blades. The BEMT predictions of blades with varied twist were also performed in hover and forward flight, respectively. In hover,flexible blades cannot help in improving the FM at light disk loading since the twist generated on flexible blades is probably beyond the ideal hover twist. In forward flight, the propulsive efficiency η of flexible blades is mostly higher than baseline blades due to the beneficial twist generated in rotation. A Particle Image Velocimetry (PIV) approach of loads determination was developed based on control volume method to obtain thrust and torque of small-scale proprotor,especially for off-optimum conditions. The pressure Poisson equation was implemented for the pressure estimation based on the PIV velocity data. The axial velocity of flexible blades is found to be lower than baseline blades on the same station at downstream. This corresponds to the lower inflow ratio distribution along flexible blade, which results from the negative twist deformation. For both baseline blades and flexible blades, the thrust differences between PIV test 2 and balance are larger when compared to the differences between PIV test 1 based on nearfield and balance. The Laser Displacement Sensor (LDS) technique was employed for measuring the stationary deformation of rotating flexible blades. By obtaining the LDS point cloud, the bending and torsion of the rotating blade were identified using the multiple regressions.

Este trabalho apresenta a simulação numérica do escoamento turbulento em torno de uma turbina eólica de eixo vertical de pequeno porte, Savonius tipo helicoidal com torção de 180° nas pás. Com o intuito de avaliar a metodologia computacional empregada os resultados numéricos obtidos são comparados com os resultados experimental e numérico contidos no estado da arte. Também, compara-se o coeficiente de toque da turbina Savonius helicoidal com a turbina Savonius convencional. As simulações numéricas são baseadas no Método de Volumes Finitos, e para tal emprega-se o programa Fluent /Ansys versão 13.0 que resolve as equações da continuidade e as equações de Navier-Stokes com médias de Reynolds, juntamente com o modelo de turbulência . As simulações são desenvolvidas empregando diferentes malhas computacionais em estudos transientes, tridimensionais, com a turbina estacionária. A avaliação da qualidade da malha é realizada através do método de Índice de Convergência de Malha (GCI) o qual analisa o quão longe os resultados estão da solução assintótica para a malha utilizada. Após a análise da qualidade de malha, realizam-se simulações com a turbina em rotação as quais fazem uso da malha contendo uma região móvel possibilitando a imposição de uma velocidade angular ao rotor. O coeficiente de torque é obtido nas simulações e a partir dele calcula-se o coeficiente de potência. Além da análise do desempenho do rotor realiza-se uma análise qualitativa das características do escoamento sobre a turbina. A turbina Savonius helicoidal apresenta um valor de coeficiente de potência de 0,175 para a razão de velocidade de ponta de 0,58 considerando correção do efeito de bloqueio. Os resultados obtidos apresentam boa concordância com os resultados publicados por outros autores. / This dissertation presents the numerical simulation of the turbulent flow around of a small sized vertical axis wind turbine, consisting in a helical Savonius type with a 180° degree of blade twist. In order to evaluate the used methodology the obtained results are compared with the state of the art numerical and experimental data. It will be also presented the comparison between the torque coefficient of the conventional Savonius turbine and the helical Savonius turbine. The numerical simulations are based on the Finite Volume Method (FVM), using the commercial code Fluent/ANSYS version 13.0, which solves the continuity and Navier-Stokes through the Reynolds time-averaged methodology, including the turbulence model. The simulations are developed using different computational meshes for transient and three-dimensional studies with the stationary turbine. The evaluating the quality of the mesh is performed by of Grid Convergence Index (GCI) method which analyzes how far the results are the asymptotic solution to the mesh used. After the evaluation of the mesh quality, it was simulated a case considering the rotor motion using the moving mesh configuration, allowing the imposition of an angular velocity to the turbine. In the post-processing stage, it is possible to obtain the torque coefficient on the rotor shaft, allowing the calculation of the power coefficient for the turbine. In addition to the performance analysis, it is also made a qualitative analysis of the flow characteristics over the turbine rotor and in both cases presenting a good correspondence with the results in the literature. The helical Savonius turbine presents a value of power coefficient of 0.175 to a tip speed ratio of 0.58 whereas blocking effect correction.