[pt] A crise atual pela qual passo mundo tornou-se a grande responsável pelo desenvolvimento científico-tecnológico, que se fará presente no próximo século. Dentre as diversas fontes alternativas, que se apresentam, a energia eólica tornou-se uma das mais destacadas, sobretudo devido ao uso de moinhos de vento (Cataventos). Os moinhos de vento são máquinas de fluxo que convertem a energia cinética dos ventos em outras formas de energia, fornecendo, portanto, substancias melhores ao dia-a-dia da humanidade. O trabalho que se apresenta trata do desenvolvimento teórico-experimental sobre o rotor de resistência, do tipo de eixo vertical, conhecido como rotor Savanius ou vulgarmente rotor S. Este tipo de rotor pode possuir as mais diversas formas geométricas para as pás. Entretanto, a mais divulgada, devido a sua facilidade de construção, é a semi-circunferencial, sobre a qual incidiu o desenvolvimento teórico deste trabalho. Um dos objetivos básicos do projeto da turbina eólica do tipo Savonius, é desenvolver tecnologia e obter experiência em operação de cata-ventos, em especial, visando o projeto e construção de unidades de grande porte. O desempenho do projeto do rotor é feito através de uma análise simplificada do modelo matemático. Por intermédio de valores experimentais, foram obtidas as curvas adimensionalisadas de torque (Ct) e de potência (Cp) versus a razão de velocidade (E), as quais podem servir para predizer o desempenho do rotor. Através deste procedimento, fez-se a análise para diversas formas geométricas de rotores. Finalmente comparando-se os resultados experimentais com a teoria desenvolvida, foram obtidas as curvas que relacionam o coeficiente de entrada (Ko) e a razão de velocidade(E). (Estas curvas foram obtidas somente, para o caso rotores de configuração de pás semi- circunferencial, que é o mais usual). / [en] The present crisis though which world passes now has become responsible for the scientific technological development that will take place in the next centrury. Among the various alternative aources in existence eolic energy has become one of the most outstanding, mainly by the use of the windmills (weathervane). Windimille are flow machines that convert wind kinetic energy into other of energy, whitch provide substancial goods to mankind. The present work deals wind kinetic energy into other of energy, which provide substancial goods to mankind. The present work deals with the theoretical-experimental development of the resistance rotor, of the vertical axle type, known as Savonius or commonly as S Rotor. One of the basic aims of the savonius type turbine is to develop techonology and to obtain experience in the operation of windmills, specially aiming at the desing and construction of large sinze unit ies. The analysis of performace of the rotor is made base on a simplified mathematical model. By means of experimental values, non admimensional curves of torque (Ct) and power (Cp), verusu speed rate (E) were obtained, and are usefull in predicting the rotor s performace. Through this procedure the analysis of various forms of geometryc rotors was performed. Finally, comparing the experimental results with the theory developed, curves of entry coeficient (Ko) related to the spedd rate ware obtarned for rotors of sami-circunferencial blades configuration only.

A Escola Politécnica da Universidade de São Paulo (EPUSP) e o Instituto Dante Pazzanese de Cardiologia (IDPC) estão realizando um projeto conjunto visando o desenvolvimento de um implante Dispositivo de Assistência Ventricular (DAV). Esta dissertação é parte do desenvolvimento de um VAD implantável em que o rotor da bomba é suspenso por uma suspensão magnética com um grau de liberdade (1-DOF). A suspensão magnética aqui utilizada apresenta o controle ativo somente na direção axial do rotor. Este mancal magnético foi apresentado por Silva e Horikawa (2000) no qual o controle ativo é executado apenas na direção axial do rotor. Neste trabalho o mancal magnético será referenciado como MMA-EPUSP. O motor de corrente contínua sem escovas (BLDC) foi selecionado pelo mesmo motivo que o mancal magnético: o motor não pode ter nenhum contato com o rotor, minimizando os problemas de danos aos componentes do sangue. Entretanto, o acionamento do motor através de forças magnéticas pode interferir na suspensão magnética. Como a estabilidade da suspensão magnética é garantida pela rigidez axial, é razoável presumir que a interação magnética entre o mancal magnético e o motor elétrico pode interferir na suspensão magnética. Este estudo analisa experimentalmente o motor BLDC com rotor apoiado pelo MMA-EPUSP, para identificar o comportamento desse conjunto utilizando duas configurações distintas de motor com fluxo magnético: radial e axial. A análise inclui: (i) projeto, construção e teste de um motor BLDC axial e um radial; (ii) projeto, construção e teste do MMA- EPUSP e do rotor para ser acionado pelos motores BLDC; (iii) estimativa do comportamento dos motores BLDC utilizando análise MEF; e (iv) execução dos testes experimentais para identificar como cada opção de montagem do motor interage com o MMA-EPUSP. A análise MEF corrobora com a recomendação do motor BLDC de fluxo magnético radial como a melhor opção de motorização para o DAV com o MMA-EPUSP, já que este motor não induz nenhuma força magnética axial que precise ser compensada pela suspensão magnética. Entretanto, o projeto do DAV pode ser mais complexo devido à interferência mecânica entre a saída do sangue do DAV e o estator do motor. Já a força magnética axial induzida pelo motor BLDC de fluxo axial é suficientemente forte para desestabilizar o MMA-EPUSP, demandando uma alta corrente do controle de posição do rotor. Os dados indicam que o projeto do controlador atual não conseguirá garantir a estabilidade do mancal magnético com este tipo de motor a altas velocidades. Neste caso, estudos adicionais são recomendados para avaliar a estabilidade dinâmica do rotor com MMA-EPUSP com o rotor imerso em sangue, já que um ambiente líquido poderá absorver a energia das oscilações e minimizar as restrições associadas à instabilidade da suspensão magnética a velocidades inferiores a 5000 RPM. / The Escola Politécnica of São Paulo University (EPUSP) and the Institute Dante Pazzanese of Cardiology (IDPC) is conducting a joint project aiming the development of an implantable Ventricular Assist Device (VAD). This study is part of the development of an implantasuporte@poli.usp.brble VAD in which the pump rotor is suspended by single degree of freedom (1-DOF) magnetic suspension. The magnetic suspension here utilized presents active control only in the rotor axial direction. This magnetic bearing had been presented by Silva and Horikawa (2000) in which the active control is executed only in the axial direction of a rotor. In this work this Axial Magnetic Bearing is referred as AMB-EPUSP. The brushless direct current (BLDC) motor has been elected due to the same reason why a magnetic bearing: the motor should not contact the rotor, minimizing problems of damage to the blood components. However, the driving of the rotor by magnetic forces may interfere in the magnetic suspension. As the stability of this magnetic suspension has been established by the axial stiffness, it is reasonable to expect that the magnetic interaction between the magnetic bearing and the used electric motor may interfere in the magnetic suspension. This study analyzes experimentally the BLDC motor, which rotor is supported by the AMB- EPUSP, to identify the behavior of this set using two distinct magnetic flux motor configurations: axial and radial. The analysis includes: (i) design, construction and testing of the axial and the radial BLDC motors; (ii) design, construction and testing of AMB-EPUSP and the rotor to be driven be both BLDC motors; (iii) estimate the BLDC motors behavior using FEM analysis; and (iv) experimental tests execution to identify how each motor assemble option interact with the AMB- EPUSP. The FEM analysis corroborates on the recommendation of the radial magnetic flux BLDC motor option as the best choice to drive the VAD with AMB- EPUSP, since this motor does not generate any axial magnetic force to be compensated by the magnetic suspension. However, a more complex VAD design may be required due to the mechanical interference between the VAD outlet and the motors winding. The axial force generated by the axial magnetic flux BLDC motor option, induces a strong instability on the AMB-EPUSP, demanding high current to control the rotor position. The data indicates the current controller design will not be able to guarantee the magnetic bearing stability with this motor on higher velocities. On any case, additional study is recommend to evaluate the rotordynamic rotor dynamic instability of the AMB- EPUSP with the rotor surrounded by blood, since the liquid environment should absorb the oscillation energy and minimize the restriction due to the magnetic suspension instability on speed below 5000 RPM.

La conception aérodynamique des pales du rotor principal d’un hélicoptère doitsimultanément prendre en compte plusieurs objectifs relatifs aux critères du vol stationnaire etvol d’avancement. Cette thèse vise à développer une boucle d’optimisation automatiséecombinant des algorithmes d’optimisation avancés et des outils de simulation. Deux outils desimulation sont employés pour la prédiction des performances rotor : le code de mécanique devol HOST, ainsi que le code de Mécanique des Fluides Numérique (MFN) elsA. Une analyse deces outils est effectuée pour des cas test bien documentés afin d’estimer leur capacité à prédiredes tendances de performances rotor en fonction de la géométrie de pale. L’influence desparamètres numériques est également caractérisée. Aussi, une stratégie d’optimisation estdéveloppée, permettant la prise en compte de plusieurs objectifs et de contraintes complexes,ainsi que la détermination d’optima globaux pour ce problème multimodale. Suivant cescritères, un algorithme génétique (AG) est sélectionné. Afin de réduire le nombre d’évaluationsnécessaires, une stratégie d’optimisation multi-fidélité est proposée : une optimisationpréliminaire utilisant l’AG et HOST est utilisée pour la réduction de l’espace des paramètres ensélectionnant la zone de haute performance. Ensuite, une surface de réponse est construiteavec des calculs haute-fidélité des pales de haute performance comme vu par l’étapepréliminaire. L’optimisation est finalement effectuée sur cette surface de réponse haute-fidélité.L’approche proposée résulte en une augmentation significative des performances rotor, tout enrespectant le critère industriel relatif au nombre de calculs coûteux comme MFN. L’approcheproposée se révèle être un outil efficace pour la conception de pales du rotor principald’hélicoptère. / The aerodynamic design of helicopter rotor blades requires taking into accountedmultiple objectives simultaneously, to provide a compromise solution for the conflictingrequirements associated to hover and forward flight conditions. The present work aims atdeveloping an automated optimization based on the combination of advanced optimizationalgorithms and simulation tools. As a preliminary step, candidate simulation methods andoptimization algorithms are assessed in detail. Two simulation methods are employed for thecomputation of rotor performance: the in-house Helicopter Overall Simulation Tool (HOST),based on the blade element method, and ONERA’s Computation Fluid Dynamics (CFD) codeelsA. An in-detail analysis of both simulation tools for well documented test cases is carried out,with focus on their capability of predicting trends of the global rotor performance as a function ofblade geometry. The impact of computation settings is also characterized. Then, an optimizationstrategy is developed, allowing the incorporation of multiple objectives and complex constraints,and the detection of global optima for multi-modal problems. Based on these criteria, a geneticalgorithm (GA) is selected. To reduce the number of simulations required to find optimalsolutions, a Multi-Fidelity Optimization (MFO) strategy is proposed: a preliminary low-fidelity GAoptimization stage based on HOST simulations is used to reduce the design space by selectinga high-performance subspace. Then, a CFD-based surrogate model is constructed on thereduced design space by using a sample of high-performance blade from the low-fidelity step.The final optimization step is run on the high-fidelity surrogate. The proposed MFO approachresults in significant rotor performance improvements while using a far lower number of costlyCFD evaluations of the objective functions with respect to a full GA optimization. The proposedapproach is shown to represent an efficient design tool for industrial helicopter rotor blade

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The subject of this thesis is about the balancing of large flexible rotors which exhibit mixed modal characteristics. The objective of the research was to develop a balancing procedure to determine correction masses without trial runs. This required the determination of(a) the modal vibration vectors for each resonance, (b) the modal damping ratios,(c) the mode shapes and(d) the equivalent mass of the rotor for each mode. It was made clear from the beginning that trial runs are unavoidable either, when the mode shapes cannot be determined using an analytical or numerical method, or when there is dual vibration at normal operating speed, produced by the influence of higher unbalanced modes, is too high to allow continuous operation of the machine. Therefore, the scope of the project was limited to the possible determination of correction masses without trial runs for the vibration modes included within the normal operating range. Some studies about the minimisation or complete elimination of trial runs have been published by several authors, but a literature search revealed no reports of systematic application of these procedures to field balancing of large turbo generators. This suggested that some practical difficulties had still to be overcome, opening the possibility for further research on this area. Analysis of the rotor response demonstrated the necessity of considering the angular position of the transducers when registering the rotor vibration. It was shown that measuring in a direction other than those of the principal axes of stiffness introduces errors when determining the magnitude and phase of the correction masses. That is to say, failing to consider the effects of the transducer angular position eliminates the possibility of balancing the rotor without trial runs. This is the first time that this problem has been recognised. The procedure developed was verified using an experimental rotor rig. The successful application of the procedure to the balancing of this rotor demonstrates that balancing withouttrialrunsisnotonlyatheoreticalbutalsoapracticalpossibility. The dynamic characteristics of the rotor rig, however, were some what limited and did not cover all the possibilities considered during the project. Therefore, a more complete numerical example was also successfully solved using the computer model of a rotor with characteristics similar to those of a real turbine, and whose unbalanced distribution was not initially known by this author.

Wind power counts for roughly 3 % of the global electricity production. In the chase to produce greener power, much attention lies on getting more electricity from the wind, extraction of kinetic energy, with help of wind turbines. Wind turbines have been used for electricity production since 1887 and have since then developed into more efficient designs and become significantly bigger and with a higher efficiency. The operational conditions change considerably over the rotor length. Inner sections are typically exposed to more complex operational conditions than the outer sections. However, the outer blade sections have a much larger impact on the power and load generation. Especially here the demand for good aerodynamic performance is large. Airfoils have to be identified and investigated on mid/outer sections of a 7.0 MW rotor with 165 m diameter. Blade performance criteria were determined and investigations like sensitivity analysis were made. With the use of XFLR5 (XFoil) and Qblade, the airfoils were made into a blade and tested with the blade element momentum theory. This simulation gave detailed information regarding performance and operational loads depending on the different airfoils used. These results were then validated in a professional aero-elastic code (Flex5), simulating steady state, turbulent and wind shear conditions. The best airfoils to use from this reports airfoil catalogue are the NACA 63-6XX and NACA 64-6XX. With the implementation of these airfoils, blade design 2 and 3 have a very high performance coefficient compared to large commercial HAWT rotors.

Reducing secondary leakage is a common challenge in numerous machines, particularly in steam and gas turbines. Too large leakage in seals produces a substantial loss in efficiency and power delivery with an increase in specific fuel consumption. Various seal types exist, each with unique advantages and disadvantages as per leakage, power loss, and wear. Labyrinth seals are most common due to their simple design and low cost. Their main drawback is a too high leakage due to enlarged (worn) clearances when a rotor vibrates. More complicated seal types, such as brush seals can withstand rotor excursions and ensure lower leakage rates than with labyrinth seals. Brush seals utilize a bristle bed which contacts the rotor and wears out thereby reducing leakage performance. The HALOTM seal, an all-metal seal with flexibly supported shoes, is engineered as a clearance control seal to reduce leakage even more, in particular for operation with high pressure differentials and with high surface rotor speeds. Static leakage tests with hot air at a high temperature (max. 300°C) conducted in a test rig holding a labyrinth seal and a novel all-metal seal (HALOTM seal), both of the same diameter, length and clearance, show the novel seal leaks ~1/5 the flow of a labyrinth seal for pressure ratios (Ps/Pa) > 3.5. The savings in leakage are maximized during operation at high pressure differentials. Leakage measurements with a rotor spinning to a maximum speed of 2,700 rpm (surface speed = 23.6 m/s) produce a slight decrease in leakage with increasing rotor speed. The research product is a reliable leakage data base enabling the application of a state of the art sealing technology that increases system efficiency by reducing leakage and extends maintenance intervals by eliminating wear of components.

No description available.