O processo de conformação por spray é interessante devido à capacidade de conjugar, em apenas uma etapa do processo, a vantagem da técnica de solidificação rápida combinada com alta produtividade dos processos de fundição convencional. Este processo permite a obtenção de materiais livre de macrossegregações, livre de porosidades e com microestrutura refinada. A evolução recente das pesquisas está levando ao desenvolvimento de novas ligas e os resultados têm sido interessantes. O processo de solidificação rápida inerente da conformação por spray permite a produção de ligas com composições diferentes das obtidas pela fundição convencional. O objetivo deste trabalho foi o de caracterizar mecanicamente uma liga de alumínio AA-6082 conformada por spray. Os resultados de testes de dureza Vickers são apresentados para seções de um preformado em relação a sua altura (em um arranjo tridimensional). O material foi avaliado na condição como conformado por spray e após tratamento térmico de solubilização a 525 ºC por 1 h, seguido por envelhecimento a 125 ºC por períodos distintos de 1 h, 10 h, 100 h e 500 h. É mostrado que o a liga AA 6082 conformada por spray mostra uma boa estabilidade térmica em relação a variação da dureza durante o envelhecimento. / The spray forming technology combines in a single step the advantages of the rapid solidification techniques and high the productivity of the conventional casting processes, allowing obtention of preforms with a refined microstructure, almost without porosity and macrosegregation free. The development and research efforts are leading to interesting alloys and materials production. The rapid solidification processes inherent to the spray forming allow the production of alloys with different compositions from those obtained by conventional ingot processes. The aim of this work was to carry out mechanical properties characterization of a spray formed AA-6082 alloy. The hardness results are presented in different sections related to the height of the spray formed preform (in a three-dimensional arrangement). The material was evaluated in the as sprayed condition and after heat treatment of solution at 525 ºC for 1 h, and aging for 1 h, 10 h, 100 h and 500 h periods. It was shown that the spray formed AA-6082 aluminum alloy is very stable regarding hardness variation during aging.

Made available in DSpace on 2016-03-15T19:36:44Z (GMT). No. of bitstreams: 1 Andre Luis Teixeira Martins.pdf: 7704108 bytes, checksum: 576d699591dbb6b908403edc18197d71 (MD5) Previous issue date: 2014-08-26 / The beverage metal packaging industry figures as one of the most important worldwide aluminum consumer. A detailed knowledge of the raw material used in the beverage can body production is essential to maintain and improve the productivity levels imposed by the market. It is on this point that the present work focus, in the micro structural and mechanical characterization of three different AA 3104-H19 rolled coils, to be able to compare them in search of similarities and discrepancies. Their chemical compositions were analyzed by energy dispersion (EDS), and atomic absorption (AA) spectrometry, their micro structures were identified by optical microscopy and scanning electron microscopy. Their mechanical properties were described by tensile tests, Erichsen tests, forming limit curves (FLC), micro hardness Vickers tests, and surface roughness tests (Ra). The anisotropy coefficient R, also known as Lankford´s R, and the strain hardening exponent n were calculated using the results and specimens of the tensile tests. In addition, their crystallographic textures were analyzed by orientation distribution functions and pole figures. The experiment s results showed a strong similarity among all three rolled sheets, their properties differing only subtly. On average the yield strength of all three was found to be 265 MPa, their ultimate tensile strength 285 MPa. Elongation was very similar for all three, around 4.7%. The strain hardening exponent n averaged 0.078, a value comparable to some found in literature. The normal (R) and planar (UR) anisotropy values were found to be 0.77 and 0.22, respectively, indicating a slight tendency to form ears at 45o and good deep drawing formability. The microstructure analysis of all three sheets revealed two kinds of intermetallic compounds with distinct morphology, Al6(Fe,Mn) and Al12(Fe,Mn)3Si, not scattered homogeneously, together with well distributed dispersoids in the aluminum matrix. The crystallographic texture of the three sheets also exhibited similarities; all had the same dominant components with comparable intensities. On all three it was possible to notice that the typical strain hardening textures, Brass {110}<112> and Copper {112}<111>, together with Goss {110}<001>, were balanced by the Cube {001}<100> component, typical of recrystallization. The notable differences found could be summarized in slightly higher mechanical properties for one of the sheets and smaller and less widespread intermetallic compounds for another. / A indústria de embalagens metálicas para bebidas se destaca como uma das mais importantes no consumo mundial de alumínio. O conhecimento detalhado da matéria prima utilizada para a produção de latas para bebidas é essencial para manter e melhorar os níveis de produtividade impostos pelo mercado. O foco do presente trabalho encontra-se na caracterização microestrutural e mecânica de três diferentes laminados da liga de alumínio 3104-H19, a fim de compará-los em busca de similaridades e discrepâncias. As suas composições químicas foram avaliadas através de espectroscopia de dispersão de energia (EDS-MEV) e de absorção atômica (AA). Suas microestruturas foram analisadas através de microscopia óptica e microscopia eletrônica de varredura. Suas propriedades mecânicas foram apuradas pelo uso de ensaios de tração uniaxiais, ensaios Erichsen, curvas limite de conformação (CLC), microdureza Vickers, e rugosidade (Ra). O coeficiente de anisotropia, R de Lankford, e o expoente de encruamento (n), foram calculados através dos resultados dos ensaios de caracterização mecânica.Em adição, uma análise da textura cristalográfica dos laminados foi realizada através do uso de funções de distribuição de orientação e figuras de polo. Os resultados demostraram semelhança entre os três laminados, suas propriedades e características diferindo apenas sutilmente. Na média o limite de escoamento dos três ficou em 265 MPa e o limite de resistência a tração em 285 MPa. Os alongamentos percentuais ficaram todos ao redor de 4,7%. O expoente de encruamento n ficou na média em 0,078, valor próximo a alguns encontrados na literatura. Os índices de anisotropia normal (R) e planar (UR) ficaram próximos a 0,77 e -0,22, respectivamente, indicando uma leve tendência ao orelhamento a 45º e boa conformabilidade em repuxo profundo. A análise microestrutural dos três laminados revelou dois tipos de compostos intermetálicos com morfologia distinta, Al6(Fe,Mn) e Al12(Fe,Mn)3Si, espalhados não homogeneamente, junto à dispersoides bem distribuídos na matriz de alumínio. A textura cristalográfica dos três laminados também exibiu similitudes, todas com as mesmas componentes dominantes em intensidades parecidas. Nos três notou-se que a textura típica de deformação para ligas de alumínio, latão {110}<112> e cobre {112}<111>, junto a textura Goss {110}<001>, estavam balanceadas pela textura cubo {001}<100>, típica de recristalização. As diferenças encontradas resumiram-se a propriedades mecânicas sutilmente superiores em um dos laminados e compostos intermetálicos menores e em menor volume em outro.

A indústria aeronáutica tem buscado melhorias no conceito de integridade estrutural, a partir do desenvolvimento de projetos mais otimizados com a produção de aeronaves mais leves e seguras. Tais projetos garantem aeronaves operacionalmente mais viáveis e redução no consumo de combustível, beneficiando o fabricante, os operadores e a população em geral, pois aplica o conceito de aeronave verde. Estruturas aeronáuticas em operação recebem solicitações de cargas típicas de vôo, como pressurização, sustentação, que por sua vez, geram esforços dos mais variados tipos e suas combinações, como tração, compressão, fadiga, torção, flexão, flambagem, cargas aeroelásticas, vibrações e flutter, associados a ambientes críticos. O conhecimento sobre o comportamento do material estrutural perante ambientes corrosivo ou de baixa temperatura, é importante para avaliação da vida útil das aeronaves. Neste contexto, o objetivo deste trabalho foi avaliar o comportamento da liga AA2050-T84 sob ponto de vista de corrosão-fadiga e tenacidade a fratura em criogenia e, correlacionar com a microestrutura e fractografia através de ensaios mecânicos e de tenacidade a fratura em temperatura ambiente e criogênica. As condições de ensaios foram determinadas próximas a de serviço a que o material será inserido sendo, para criogenia -54 ºC e para os ensaios de propagação de trinca por fadiga em atmosfera ambiente e névoa salina com concentração de solução de 3,5% e 5% NaCl, frequência de 15Hz e razões de carga R = 0,1 e 0,5. Os resultados em criogenia mostraram que há melhora nas propriedades trativas e estabilidade na tenacidade, pois o material retém dutilidade com o decréscimo da temperatura. Os ensaios de propagação de trinca por fadiga foram executados com &Delta;K decrescente e os parâmetros para geração de névoa salina foram determinados experimentalmente. As curvas de crescimento de trinca e determinação do fator limite foram comparadas quanto a razão de carga e atmosfera de ensaio. Observou-se que para os ensaios de propagação de trinca por fadiga a presença da névoa salina acelera a taxa de propagação e resultam em um fator limite menor. / The aviation industry has sought improvements with the concept of structural integrity, from the development of more optimized designs with production aircraft with low weight and secure. These projects ensure an aircraft more operationally doable and reduced fuel consumption, benefiting the manufacturer, operators and the people, applying the concept of green aircraft. Aerospace structures in operation receive requests loads typical of flight, how pressurization support and lift that produce several types and combinations of requests, such as tensile, compression, fatigue, torsion, bending, buckling , aeroelastic loads, vibration and flutter associated with critical environments. Knowledge about the behavior of the structural material into corrosive environments or cryogenic temperature, it is important for evaluation to the lifetime of the aircraft. Accordingly , the aim of this study was to estimate the behavior of AA2050 - T84 alloy, about corrosion-fatigue and fracture toughness at cryogenic situations and correlate with microstructure and fractography, by mechanical tests and fracture toughness at room temperature and cryogenic. The test conditions has been determined near of the service that the material will be inserted, for cryogenic temperature -54 ºC and testing of fatigue crack propagation in air and salt spray with concentration of 3.5% and 5% NaCl, frequency 15Hz and load ratios R = 0.1 and 0.5. The cryogenic results showed that there improvement in tensile properties and stability in toughness due the restraint of ductility with decreasing temperature. Tests of fatigue crack propagation were carried out with &Delta;K decreasing and the parameters to obtain salt spray were determined experimentally. The crack growth curves and determination of the threshold were compared the according to load ratio and test atmosphere. In the fatigue crack propagation it was observed that presence of salt spray accelerates the rate of propagation and result in a lower threshold.

Le soudage par friction malaxage « Friction Stir Welding » est un procédé d'assemblage de pièces en phase semi solide. Le cordon de soudure est obtenu grâce à un outil de révolution composé d'un épaulement et d'un pion. Ce procédé utilise le principe de la conversion de l'énergie mécanique en énergie thermique par frottement de l'outil avec les pièces à assembler. Ce travail de thèse est une contribution à la modélisation expérimentale et à la simulation numérique de ce procédé permettant de fournir des modèles pour aider à la compréhension des phénomènes thermiques et mécaniques ainsi que les interactions entre les paramètres de soudage. Les études expérimentales sont principalement orientées vers la caractérisation de l'écoulement de matière à l'aide de marqueurs et vers l'optimisation des paramètres du procédé. L'effet de la géométrie de l'outil (outil à pion cylindrique ou outil avec méplats) sur l'écoulement de la matière au cours du soudage est étudié. Pour représenter la géométrie de l'écoulement et prédire les champs thermiques et mécaniques à l'état stationnaire, des modèles formulés sur la base de la dynamique des fluides sont adoptés dans la présente thèse. Deux modèles thermomécaniques sont développés: (1) un premier modèle numérique construit sous Fluent permet d'étudier le comportement thermomécanique et l'écoulement au cours du soudage FSW. Une loi de comportement dépendante de la température et de la vitesse de déformation est utilisée et une discussion sur les conditions de contact entre l'outil et les plaques à souder est présentée. Les résultats de l'écoulement sont comparés avec ceux obtenus expérimentalement dans le cas de suivi des trajectoires de particules de cuivre. (2) un deuxième modèle original basé sur une procédure itérative est mis en œuvre permettant le soudage de plaque de grandes dimensions. En effet, pour une meilleure prise en compte des conditions aux limites thermiques, un modèle thermomécanique construit autour de l'outil de soudage et couplé avec un modèle thermique pour tout le reste du domaine étudié. Ce modèle permet de prendre en compte le transfert de chaleur dans l'outil et dans la plaque support. Les cycles thermiques et la plage de viscosité pour deux alliages d'aluminium (AA7020-T6 et AA6061-T3) sont analysés et comparés avec succès aux résultats expérimentaux. Les efforts et le couple de soudage calculés numériquement sont validés par rapport à la littérature. / The friction stir welding is a process for assembling a semisolid phase parts. The weld seam is achieved by a revolution tool consists of the shoulder and the pin. This process converts the mechanical energy into heat energy by friction of the tool with the parts to be joined.This thesis is a contribution to the experimental modeling and numerical simulation of this process in order to provide models to assist in understanding the thermal and mechanical phenomena and interactions between the welding parameters. Experimental studies are used for the characterization of the material flow with markers and to optimize the process parameters. The effect of tool geometry (cylindrical pin or tool with flats) on the material flow during welding is studied. To represent the flow geometry and predict the thermal and mechanical fields in the steady state, CFD models are adopted in this thesis. Two thermomechanical models are developed: (1) first numerical model is used to study the thermomechanical behavior and flow during FSW. FLUENT is employed to solve the coupled thermal and fluid flow equations. A behavior law depending on temperature and strain rate is used and a discussion on the contact conditions between the tool and the workpieces is presented. The results of the flow are compared with those obtained experimentally in the followed case of trajectories copper particles. (2) A second original model based on iterative procedure is implemented to welding large plates. To take account the correctly thermal boundary conditions, a thermomechanical model built around the welding tool and coupled with a thermal model for the rest of the area studied. This model allows taking into account the transfer of heat in the tool and in the backing-bar. Thermal cycles and the viscosity range for two aluminum alloys (AA7020-T6 and AA6061-T3) are successfully analyzed and compared with experimental results. The loads and torque welding are calculated numerically and validated in the literature.

Le fluage est l'un des phénomènes qui influencent le comportement des conducteurs aériens de transport d'énergie électrique. Il s'agit d'une déformation irréversible qui apparaît dans les structures soumises à des charges mécaniques permanentes. Ce phénomène commence à l'instant où la charge est appliquée et continue, à un taux décroissant, aussi longtemps que la charge et la température sont maintenues. Dans les conducteurs en portée, le fluage se manifeste par l'augmentation de la flèche et la réduction des distances sécuritaires entre les lignes et le sol. D'autre part, la température moyenne des conducteurs, transportant en continue un courant électrique important, peut être largement supérieure à la température ambiante, ce qui influence le phénomène de fluage des câbles. Dans ce cadre, s'inscrit ce projet de maîtrise qui consiste à évaluer l'effet de la température sur le comportement en fluage des conducteurs en mesurant l'allongement des fils qui les constituent. Pour ce faire, un banc d'essai de fluage des câbles a été conçu pour étudier le fluage sur les conducteurs et un banc d'essai de fluage des brins a été utilisé pour déterminer le comportement en fluage des fils. Pour les conducteurs, un essai préliminaire de fluage, de 400 heures, a été effectué sur un conducteur de type AAC (Orchid) pour valider le montage expérimental et vérifier l'effet de la mise en place des brins sur le fluage. Le câble a été testé à 38°C et à 25% de sa résistance à la traction assignée (RTA). Pour les essais sur les brins, les fils d'aluminium 1350-H19 et d'almélec ont été testés en fluage pendant 1000 heures. Les fils ont été soumis à quatre niveaux de température d'opération : 20°C, 38°C, 55°C et 70°C et à quatre niveaux de contrainte : 15%, 25%, 35% et 47% RTA pour l'aluminium et 8%, 15%, 25% et 35% RTA pour les fils en almélec. De plus, des essais de traction sur des fils en aluminium et en alliage d'aluminium ont été effectués pour évaluer l'effet du fluage et de la température sur le comportement mécanique des fils isolés. Ces résultats ont permis d'étudier l'effet de la température et de la contrainte sur le fluage des conducteurs à travers le fluage des fils. À partir des données expérimentales, une loi d'évolution de fluage a été établie et tient compte du taux de chargement et de la température.

En aéronautique, les structures en alliage d’aluminium 2024 sont protégées par un primaire anticorrosion fonctionnalisé par des pigments inhibiteurs permettant une cicatrisation rapide de la surface de l’alliage exposée à l’environnement extérieur lors d’un endommagement mécanique superficiel. Compte tenu de la perte de fonctionnalité des primaires par lessivage, il semble nécessaire d’évaluer les risques d’amorçage de la corrosion. En pratique, il a été envisagé de mettre en place des capteurs dits de « corrosion ».L’objectif de ce travail était de comprendre le fonctionnement d’un capteur censé représenter l’endommagement d’une peinture, dont le concept repose sur la compétition entre l’amorçage de la corrosion d’une surface d’un alliage d’aluminium mis à nu et le relâchement d’inhibiteurs (provenant de la peinture). Le comportement de l’alliage 2024 et de solutions solides (constituant le capteur) a été étudié en milieu chloruré en présence ou non d’inhibiteurs à différentes concentrations. En variant la taille d’électrodes peintes exposées sur leur tranche, on a pu quantifier l’efficacité des inhibiteurs sur ces deux types de matériaux, en détectant l’amorçage de la corrosion ou son inhibition, par mesure de pH de surface. Cette analyse chimique couplée à des observations in situ, a permis de déterminer les étapes limitantes qui définissent la compétition entre corrosion et passivation dans le cas de l’alliage 2024. Ces différentes analyses ont montré que, pour quantifier cette compétition, la cinétique d’amorçage de la corrosion microstructurale constitue un élément clé qui ne peut pas être représenté par la réponse des électrodes du capteur constituées d’une solution solide. L’existence d’une distance maximale entre la source d’inhibiteurs et la zone pouvant être passivée a pu être confirmée par la simulation du transport des espèces inhibitrices qui dépend principalement du régime de lessivage du primaire. / The conventional aircraft paint scheme for corrosion protection of aluminum structures is partly based on application of a primer containing inhibitors. In such coatings, release of the inhibiting species enables fast healing of a bare metal surface after a mechanical damage of the protective layers. Nevertheless, considering possible depletion of inhibitors by uncontrolled leaching, it appears important to estimate the corrosion risk integrating “corrosion” sensors in the structure. The objective of this work was to understand the operating mode of a sensor simulating a damaged paint coating whose concept is based on the competition between the triggering of localized corrosion and the passivation of a bare 2024 alloy. The behavior of this massive alloy and Al-Cu solid solutions (the active metallic slots of the sensor) was studied in chloride solution in presence or not of inhibitor ions at different concentrations.Varying the size of a cut-edge electrode coated on both sides, the effectiveness of these inhibitors was demonstrated detecting the microstructural corrosion triggering or its inhibition, by mapping surface pH. Combining these chemical probing with in situ observations it was possible to confirm the nature of the limiting steps controlling the competition between corrosion and passivation. These analyzes highlighted that to quantify this competition, the triggering of the microstructural corrosion represents a key factor which is not possible to mimic by the response of the solid solutions.The existence of a threshold value for the distance between the inhibitor source and the area to be passivated has been confirmed by simulating the mass transport of inhibiting species which appear to be dependent of the release rate of inhibitors.

Aluminum alloy 6061-T6 is a common engineering material used in aerospace, automotive, structural applications. Despite its wide use, little has been published about the effects of damage from surface corrosion on its fatigue life. An investigation was performed where 6061-T6 extrusions were exposed to a 3.5% NaCl solution at pH 2 for 2 days and 24 days. The length of time and pH were chosen in order to create distinct surface flaws. The effect of these flaws on the fatigue life was then investigated and analyzed using scanning electron microscopy (SEM) and Weibull statistics. It was determined that samples corroded for both 2-days and 24-days exhibit fatigue lives that can be described using a 3-parameter Weibull distribution. The result of which was the determination of a threshold value for fatigue as well a general understanding of flaw geometry.

No description available.

This thesis deals with problems with manufacturing of high frequency elliptic and hyperbolic optic mirrors, which makes one of the most important functional parts of parabolic satellites made for biggest and highest placed international astronomical radio-telescope in the world - ALMA, which is built on Chajnantor plateau in Chille in South America. Individual chapters are designed in the flow of technological process of manufacturing, containing theoretical and practical analysis of the problems. Content of the thesis leads especially to description and clarification of individual causes of problems during manufacturing.

The master’s thesis deals with the influence of the exothermic risers on the solidification of aluminum alloys. The work is divided into three parts. The first theoretical part describes the differences of properties of cast aluminum alloys compared to other based metals, especially iron alloys. It also describes the methodology of designing risers, composition of exothermic mixtures and finally gives an overview on the simulation programs on the market, their application in foundry practice and briefly explains how to define the material in the simulation program ProCAST. The second part describes the experimental measurement of the solidification time of aluminum alloy AlSi7Mg0,3 in the sand form with exothermic riser. The final section describes the simulation of experimental measurements. Further with help of simulation software it is tried to find the general principles that have an influence on feed module rate of exothermic riser.