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Os tratamentos de cementação, têmpera, revenimento e jateamento por granalhas são muito utilizados na produção seriada de peças da indústria automobilística, como engrenagens e eixos. Variações destes processos podem influenciar a vida em fadiga por flexão dos componentes descritos. O objetivo deste trabalho foi estudar a influência de variações no tempo de jateamento por granalhas, variações na temperatura de revenimento e de diferentes profundidades de oxidação intergranular, no crescimento de trincas curtas por fadiga na camada cementada do aço DIN 20MnCr5. Para isso foram feitos ensaios de fadiga por flexão em quatro pontos, utilizando corpos de prova de seção retangular e sem entalhe. Para o acompanhamento do crescimento de trincas curtas foi utilizado o método de réplicas de acetato. Foram estudados seis níveis de jateamento, quatro níveis de revenimento e dois níveis de oxidação intergranular. Como resultados principais, foram obtidas curvas de comprimento de trinca por número de ciclos e taxa de crescimento de trinca por tamanho médio da trinca. Amostras jateadas entre trinta minutos e uma hora, revenidas à 160&#176C e com oxidação intergranular por volta de dez mícrons, apresentaram os melhores resultados em relação à vida em fadiga. / Carburizing, quenching, tempering and shot peening treatments are often used in mass production of automotive parts, such as gears and shafts. Changes in these treatments can influence the bending fatigue life of these parts. The purpose of this study was to measure the influence of different shot peening times, different tempering temperature and different internal oxidation depths, on the short fatigue crack growth in case carburized DIN 20MnCr5 steel. Four-point-bend fatigue tests were carried out in rectangular section specimens without notch. The surface short crack growth was monitored by means of acetate replication technique. Six levels of shot peening, four levels of tempering temperatures and two levels of internal oxidation were studied in this work. Crack length versus number of cycles and crack growth rate versus mean crack length were obtained as principal results. Shot peening from 30 minutes to one hour, tempering at 160#176C and a lO~m depth of internal oxidation showed the best results in fatigue life.

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Orientadores: Sergio Tonini Button, Renato Pavanello / Tese (doutorado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecanica / Made available in DSpace on 2018-08-11T03:57:59Z (GMT). No. of bitstreams: 1 Silva_EvandroCardozoda_D.pdf: 7516310 bytes, checksum: e6a941fa7741a9dbf2fd38237d40195b (MD5) Previous issue date: 2008 / Resumo: O grande desafio do engenheiro no processo de jateamento de esferas, é obter o perfil da tensão residual e a deformação final da peça com precisão. Pois a solução analítica, os resultados experimentais e as simulações numéricas, que possam ser validados, ainda não são totalmente dominados, devido a complexidade do problema de contato dinâmico não linear do impacto que envolve várias disciplinas da elasticidade e plasticidade estática e dinâmica. É preciso reconhecer os vários parâmetros que influenciam o processo e obter um modelo de simulação numérica 3D de elementos finitos (EF) dinâmica e estática, utilizando ferramentas comerciais consagradas, que tenha relativa precisão e possa ser validado ao se caracterizar a tensão residual mecânica induzida e conseqüente deformação. O estudo de modelos estáticos de carregamento equivalente são limitados pela precisão da temperatura e pressão que da a forma final da peça. No modelo de EF elasto-plástico dinâmico 3D do impacto simples, identifica-se que a camada deformada plasticamente, a tensão residual superficial e sub-superficial são influenciados significativamente pelas características da esfera. Além disso, a separação entre as esferas no impacto simultâneo alteram o desenvolvimento da região plástica. Modelos de impactos múltiplos são implementados com base nestes resultados para a condição de impacto concentrado e disperso de forma semialeatória para modelos reduzidos da peça discretizada / Abstract: Shot peen forming presents a great challenge to engineers to get a precise residual stress and the correct final plastic strain distribution within the formed parts. Because there is not a complete knowledge on analytical solutions, experimental results and numerical simulations are commonly used due to the complex dynamic contact of nonlinear impact problems that involve many disciplines on static and dynamic elasticity and plasticity. Therefore, it is essential to know the parameters that affect the process to obtain a static and dynamic 3D finite element (FE) numerical model to simulate peen forming using powerful FE commercial codes that have relative precision and give results that can be validated and consequently induced mechanical residual stress and consequent deformation can be characterized. The study of equivalent static load models are limited by the precision of temperature and pressure to calculate the correct deformed shape. In the elastic-plastic 3D dynamic FE model with a single impact, the shot characteristics influence the thickness plasticity, and the superficial and under surface residual stress. Besides, the separation distance between adjacent shots changes the development of the plastic region. Multiple shot impacts models are implemented based in these results for concentrate and partial randomic dispersed impact conditions to reduce the models of the target / Doutorado / Materiais e Processos de Fabricação / Doutor em Engenharia Mecânica

O objetivo deste trabalho foi a avaliação do comportamento à fadiga de materiais compósitos de matriz metálica (CMM) obtidos pela rota da metalurgia do pó, tendo como variáveis a fração volumétrica de reforços e o tipo de tratamento superficial mecânico utilizado. Foram obtidos materiais compósitos com matriz de alumínio AA 1100 reforçados com partículas de carboneto de silício (SiC) nas frações volumétricas de 5, 10 e 15%. Uma quantidade de material de controle, constituído unicamente pelo material da matriz também foi produzida para fins de comparação. Os materiais obtidos foram caracterizados física, mecânica e microestruturalmente. Os resultados mostraram, de maneira geral, uma distribuição homogênea das partículas de reforço e melhoria do limite de resistência dos compósitos com relação ao material de controle. Entretanto, alguns defeitos como porosidades e veios de alumínio puro foram detectados esporadicamente. Em outra etapa, foram realizados ensaios de fadiga do tipo axial nos materiais em modo tensão-tensão, com razão de tensões R = 0,1 e frequência de 15 Hz. Os tipos de tratamentos superficiais utilizados na confecção dos corpos de prova de fadiga foram: usinagem e jateamento. As variáveis de usinagem foram: taxa de avanço e tipo de ferramenta. Os materiais jateados não apresentaram melhorias significativas de vida à fadiga com relação ao material de controle. Os usinados grosseiramente apresentaram a pior vida em fadiga e as marcas de usinagem, nestes casos, funcionaram como fortes concentradores de tensão. Os reforçados com 5% de SiC, diferentemente daqueles reforçados com 10 e 15%, apresentaram vida à fadiga inferior à do material de controle, ou por causa do menor limite de escoamento ou devido à menor fração volumétrica de reforços. Os materiais usinados com metal duro (MD) não apresentaram diferenças de vida à fadiga com relação aos usinados com PCD, provavelmente devido à classe do metal duro utilizado. Os materiais reforçados com 5% de SiC e jateados apresentaram resultados de fadiga com os maiores desvios padrões. Os materiais reforçados com 5% de SiC apresentaram as menores sensibilidades à fadiga com a variação da carga. / The objective of this work was the evaluation of the fatigue behaviour of aluminium metal matrix composites (MMC) obtained by powder metallurgy. The testing variables were the volumetric fraction of reinforcements and the type of mechanical surface treatment used. Initially, the composite materials were obtained from aluminium AA 1100 matrix, reinforced with silicon carbide (SiC) particles in the volumetric fraction of 5, 10 and 15%. An amount of control material (unreinforced) was produced for comparison purposes. The obtained materials were physically, mechanically and microstructurally characterised. The results showed a homogeneous distribution of the reinforcement particles and an improvement of the ultimate tensile strength of the composites with relation to the control material. However, some defects such as porosity and streaks of pure aluminium were detected. In a second stage, the fatigue tests of the composites were accomplished. The types of surface treatments used in the fabrication of the fatigue test specimens were machining and shot peening. For machining the variables were feed rate and tool type. The shot peened materials did not present a significant fatigue life improvement when compared to the control material. The coarse machined materials presented the worst fatigue life and the machining marks worked as strong stress concentrators. The material reinforced with 5% of SiC, differently of those reinforced with 10 and 15% showed inferior fatigue life when compared to the control material, probably because of a lower yielding strength, or lower reinforcement volumetric fraction. The material machined with hard metal (MD) did not present differences of fatigue life with relation to the machined with PCD, probably due to the class of the hard metal used. The material reinforced with 5% of SiC and shot peened, presented fatigue results with the largest standard deviations. The materials reinforced with 5% of SiC presented the smallest fatigue sensibility with the load variation.

Made available in DSpace on 2016-03-15T19:36:36Z (GMT). No. of bitstreams: 1 Carolina Sayuri Hattori.pdf: 7042218 bytes, checksum: 0bc43ea853ac897f08d717277994e267 (MD5) Previous issue date: 2012-02-10 / IPEN - Instituto de Pesquisas Energéticas e Nucleares / The fatigue and toughness resistance are properties that exerts a strong influence on the spring suspension performance in the vehicles. The choice of SAE 9254 steel is due to the wide utilization in the springs fabrication and to have fatigue and toughness properties. The manufacture of SAE 9254 spring steel has been made by hot rolling process and submitted to heat treatment of quenching and tempering by conventional process or by cold process with induction heat treatment. Therefore, it is important to study the performance of this steel in these two processes. This study investigated the effect of the two production process and compared hardness and fatigue mechanical properties. The hardness is compatible with the heat treatment and the microstructure present in each condition. The shot peening induced a compressive residual stress which increased the fatigue life of SAE 9254 steel. The residual stress profile from the surface of springs showed a peak in the values of compressive stress for both manufacturing processes. The maximum residual stress in the cold processed spring was higher than the hot processed spring and maintained much higher values along the thickness of the spring from the surface, resulting from manufacturing processes. The fatigue cracking of the springs, produced by both process without shot peening, started by torsional fatigue process, with typical macroscopic propagation, showing stretch marks with high plastic deformation depending on the request type that accentuates the shear stresses. / A resistência à fadiga e a tenacidade são propriedades que exercem uma grande influência no desempenho das molas de suspensão dos veículos. A escolha do aço SAE 9254 ocorreu devido à sua ampla utilização na fabricação dessas molas e por possuir propriedades de fadiga e tenacidade. A fabricação de molas do aço SAE 9254 tem sido feita pelo processo de enrolamento a quente e submetido a tratamentos térmicos de têmpera e revenimento convencional ou pelo processo a frio e têmpera e revenimento por indução. Portanto, torna-se importante estudar o desempenho desse aço nesses dois processos. Esse trabalho investigou o efeito dos dois processos de produção e comparou as propriedades mecânicas em fadiga e dureza. Os valores de dureza das molas nas diversas condições investigadas estão compatíveis com o tratamento térmico e com a microestrutura presente em cada condição. O jateamento das molas induziu a uma tensão residual compressiva que aumentou consideravelmente a resistência à fadiga do aço SAE 9254. O perfil de tensão residual a partir da superfície das molas jateadas apresentou um pico nos valores de tensão de compressão para ambos os processos de fabricação. A tensão residual máxima na mola processada a frio e jateada foi superior à da mola processada a quente e mantiveram valores bem mais elevados ao longo da espessura da mola a partir da superfície, decorrentes dos processos de fabricação. As trincas por fadiga das molas fabricadas por ambos os processos sem jateamento tiveram seu início pelo processo de fadiga torcional, com propagação macroscópica típica, apresentando sinais de estrias com elevada deformação plástica em função do tipo de solicitação que acentua as tensões de cisalhamento.

Deux problèmes surviennent lorsque nous étudions les effets du grenaillage de précontrainte sur le processus de la fatigue. Le premier est la caractérisation des contraintes résiduelles (CR) et de l’écrouissage. Le second est l’évolution de CR et de l’écrouissage pendant le cyclage.Pour résoudre le premier problème, cette thèse propose une méthode pour mesurer les contraintes et l’écrouissage par nanoindentation. Ici, l’écrouissage est représenté par la déformation plastique cumulée (PP). A l’aide d’une série de simulations par éléments finis (MEF) en supposant le comportement du matériau connu, les réponses obtenues par indentation permettent d’obtenir simultanément contrainte et déformation plastique. Bien que satisfaisante d’un point vue numérique, les performances expérimentales obtenues sur un alliage de titane temps T40 restent insuffisantes. Cependant, si le profil de contrainte est connu, on peut toutefois obtenir le profil de déformation plastique. Les biais induits par la préparation de la surface ont été analysés en détail. Pour le second problème, une série d'essais de fatigue ont été effectués sur un alliage Ti-18. Quatre traitements ont été testés sur 100 cycles sous 3 amplitudes différentes de déformation. Des mesures par diffraction des rayons X ont montré que la relaxation des contraintes et l’adoucissement cyclique augmentent avec l'amplitude de déformation. Les essais d’indentation ont montré un adoucissement de la couche grenaillée / There are two problems when investigating the effects of shot-peening on fatigue process. The first one is characterizing residual stresses (RS) and strain hardening (WH) on the sample surface. The second one is the evolution of RS and WH during fatigue. In order to solve the first problem, this thesis proposes a “simultaneous function method” to measure RS and WH with nanoindentation. Accumulated plastic strain (PP) is used to represent WH. Then, by establishing functions of normalized indentation responses through a series of finite element method (FEM) simulations, normalized indentation responses obtained from nanoindentation experiments can be used to extract RS and PP values, assuming that the constitutive behavior is known. Although the simultaneous function method shows fairly high accuracy from a pure numerical view point, experiments performed on T40 commercial pure titanium are not completely satisfying. However, if the residual stress profile is known, the method can be used to derive the work hardening profile.In order to study the second problem, a series of strain-controlled fatigue tests are performed on Ti-18 alloy. Fatigue specimens of 4 material states, including raw, shot-peened, prestrained and prestrained + shot-peened, were tested under 3 different strain amplitudes over 100 cycles. X-ray diffraction tests on the sample surfaces showed that the RS relaxation and the cyclic softening increase together with the strain amplitude. IIT tests showed that shot-peening may induce a softening of the surface of Ti-18 alloy samples

Cette étude fait partie du projet ANR DEFISURF, avec pour objectif d'identifier et de modéliser les divers effets de la surface sur la tenue en fatigue de composants forgés. Deux composants sont étudiés: une éprouvette extrudée à froid et une bielle estampée à chaud et nettoyée de sa calamine par grenaillage (shot-blasting). Pour chaque composant, différents lots sont étudiés afin de quantifier l'effet des procédés sur les caractéristiques mécaniques et sur le comportement en fatigue. Deux taux de corroyage différents sont utilisés pour l'extrusion à froid. Pour les bielles, différents grenaillages sont réalisés pour obtenir divers états de surface.Les différents lots sont caractérisés de façon approfondie et des essais de fatigue sont effectués. Des essais de fatigue en traction, torsion et flexion plane sont réalisés sur les éprouvettes extrudées. Des éprouvettes de fatigue sont prélevées dans l'âme des bielles et sollicitées en flexion plane.En extrusion à froid, les aspects les plus influents en fatigue sont la prédéformation subie lors de la mise en forme (taux de corroyage) et les contraintes résiduelles. En forgeage à chaud, ce sont les défauts de forgeage en surface et les contraintes résiduelles introduites par le grenaillage qui ont le plus d'influence.Une modélisation en fatigue est proposée pour chaque composant. Pour l'extrusion, un critère de fatigue multiaxial permet de prendre en compte les différents types de chargement ainsi que l'effet des contraintes résiduelles. Pour les bielles deux approches sont utilisées. La première est une analyse de la géométrie des défauts qui utilise un demi-ellipsoïde pour approximer leur forme. La deuxième approche est une simulation numérique par éléments finis des défauts critiques. Les contraintes résiduelles sont intégrées dans les simulations avec un critère multiaxial. Les simulations permettent de retrouver les résultats expérimentaux avec une erreur d'environ 15%. / This study is part of the DEFISURF project, with the goal of analysing and modelling the various effects of the surface on the fatigue strength of forged components. Two components are studied: a cold-extruded specimen and a connecting rod which is hot-forged and then cleaned by shot-blasting. For each component, different batches are studied in order to quantify the effects of the process on the mechanical characteristics and the fatigue behaviour. Two different reduction of sections are used for the cold-extruded specimens and shot-peening is used to obtain various surface states for the connecting rods.The various batches are thoroughly characterised and fatigue tests are performed. Traction, torsion and plane-bending tests are conducted on the cold-extruded specimens. Fatigue specimens are machined from the central part of the connecting rods and loaded in plane-bending.For cold-extrusion, the parameters with the most influence in fatigue are the prestrain induced during forging and the residual stresses. In hot-forging, the surface defects produced during forging and the residual stresses induced by the shot-blasting have the most influence.For each component, a fatigue model is suggested. For the cold-extruded specimens, a multiaxial fatigue criterion is used to take into account the various fatigue loadings and the effect of the residual stresses. Two approaches are used for the connecting rods. The first is a geometrical analysis of the defect which approximates them with an ellipsoid. The second approach uses finite element simulations of the critical defects. The shot-peening residual stresses are integrated in the simulations with a multiaxial criterion. These simulations predict the fatigue limit of the specimens with an error of around 15%.

Lors de la réparation d’un défaut, le processus consiste à éliminer la matière dans la zone englobant le défaut, puis à recharger cet affouillement par un dépôt de cordons de soudure, afin de remettre en conformité la pièce en vérifiant les critères de conception. Pourtant la zone rechargée constitue en elle-même un site sensible où le niveau des contraintes résiduelles peut être préjudiciable de par son importance, notamment localement, s’il porte des contraintes de traction. Les risques de récidive d’endommagement pourraient être réduits par certains procédés de parachèvement. Ces procédés permettent de générer une zone de compression en peau externe et en sous couche de la pièce traitée. Par conséquent, la durée de vie d’une pièce ainsi parachevée pourrait être augmentée. Parmi les procédés existants, nous nous intéresserons dans cette étude à la mise en compression par billage ultrasonore. L’objectif de cette contribution est de prédire le niveau des contraintes résiduelles induites par le billage sur une pièce rechargée par soudage multi-passes. Pour mener à bien cet objectif, une étude expérimentale du billage a été réalisée sur des éprouvettes minces et épaisses afin d’identifier les paramètres influents et de disposer d’une base de résultats expérimentaux – comme par exemple la répartition quantitative des contraintes résiduelles dans la matière traitée – à confronter à la simulation. L’originalité de ce travail est de mettre en œuvre, en termes d’évaluation, une modélisation tridimensionnelle représentant correctement les phénomènes locaux et basée sur un modèle semi-analytique. Ce modèle numérique présente l’avantage de temps de calcul considérablement réduits par rapport aux méthodes éléments finis plus conventionnelles, sans pour autant sacrifier à la qualité des résultats. Pour cette application, ce modèle semi-analytique a été validé par des benchmarks aux éléments finis dans le cas de mono et multi impacts. Puis cette approche prédictive a été validée par l’expérience. Enfin, une simulation numérique du soudage a été réalisée afin de disposer d’un champ de contraintes résiduelles de soudage. Les résultats des calculs, obtenus par chaînage de simulations numériques des procédés de soudage puis de billage, ont ensuite été confrontés aux grandeurs mesurées sur des éprouvettes initialement précontraintes par flexions alternées puis billées selon des paramètres du processus identifiés antérieurement. L’état précontraint (qu’il provienne de la thermique du soudage ou de l’écrouissage de flexion alternée) a été introduit en données d’entrée, en tant que pré-chargement, dans le modèle numérique simulant les impacts. / During a repair welding process, the first step is to remove the material in the defected area, then refill this chamfer by welding rods. Since, the nickel based alloy, such as IN600, is sensitive to the phenomenon of stress-corrosion cracking, it must be ensured that the level of residual stress after welding is lower than the triggering threshold of stress-corrosion cracking. At this stage, the ultrasonic shot peening (USP) process can be used as the final finishing step. The aim is to introduce compressive residual stresses on the surface of the welded area in order to prevent occurrence of cracking. The objective of this study is to predict the level of residual stresses, induced by the ultrasonic shot peening, on structure made of IN600 repaired by multipass welding. To achieve this objective, an experimental study of the ultrasonic shot peening was carried out. Experiments similar to the “Almen” test were performed on thin and thick specimens. Influential parameters were identified. Experimental results, such as the level of residual stresses, were obtained. The originality of this work is that a three-dimensional modeling of multiple impacts, based on a Semi-Analytical Method (SAM), was implemented. This method can reduce significantly the computing time compared to finite element method, without sacrificing the quality of results. This was first validated by benchmarks for both single and multiple impacts, then proved by experiments. Moreover, a numerical simulation of welding was performed. The field of welding residual stresses should be used as the input data for the impact model. In fact, in this study，the residual state，was generated by alternatif bending test. These specimens were then treated by USP process with the parameters identified previously. As the final step, numerical results in terms of distortions and residual stresses were compared with the experimental data in order to validate the chaining of welding and peening simulation.

Cette thèse vise à déterminer l’influence de deux traitements mécaniques, le grenaillage SMAT effectué avec plusieurs types de billes (en WC, en alumine et en verre) et le choc laser, sur la résistance à l’oxydation haute température de deux alliages de titane : un alliage alpha commercialement « pur » (Grade 1) et un alliage aéronautique béta métastable (TIMETAL-21S).Une fois traitées, les pièces sont oxydées avec différentes conditions : de durée (entre 5 heures pour étudier les premier instants de l’oxydation et 3000h pour se rapprocher d’un essai type en aéronautique), de température (600°C à 700°C) et d’atmosphère (air sec et oxygène).Les pièces sont analysées avant et après oxydation à l’aide de plusieurs techniques d’analyses : mécaniques (dureté, mesures de contraintes), chimiques (DRX, microsonde nucléaire, …) ou structurales (EBSD, texture).Les résultats obtenus montrent que les traitements perturbent fortement les pièces avant leur exposition à haute température d’un point de vue morphologique, structural, mécanique et chimique. Ces traitements mécaniques amènent une réduction de l’oxydation des pièces étudiées. Il semble qu’ils modifient la vitesse de diffusion des espèces (azote, oxygène, aluminium, molybdène) mais aussi la microstructure (recristallisation, morphologie de grain ou texturation) au cours de la mise en température. L’azote joue un rôle essentiel dans les phénomènes observés.Néanmoins, la détermination des conséquences de ces traitements sur la résistance à l’oxydation reste encore complexe de par les observations de ce travail, qui révèlent une contribution simultanée de plusieurs facteurs : chimiques, mécaniques et structuraux. / The aim of this thesis is to determine the influence of two mechanical surface treatments, the shot- peening performed with several type of balls (WC, alumina and glass) and the laser shock peening, on the high temperature oxidation resistance of two titanium alloys : alpha alloy with commercially purity (Grade 1) and aeronautical beta metastable alloy (TIMETAL-21S).After different treatments, the pieces are oxidized with different conditions: of time (between 5 hours to study the firsts times of oxidation and 3000 hours to compare with a classical aeronautical test), of temperature (600°C to 700°C) and atmosphere (dry air or oxygen).The pieces are analyzed before and after oxidation exposure with several mechanical (micro-hardness, strain measurements), chemicals (XRD, nuclear microprobe) and structural (EBSD, texture) techniques. The results show a large surface perturbation before the high temperature exposure in term of morphological, mechanical, structural and chemical point of view.This mechanical treatments lead up to an oxidation rate reduction for all the different titanium alloys. This treatments modified the diffusion rate of several elements (nitrogen, oxygen, molybdenum or aluminum) but also the microstructure (recrystallization, grain morphology or texturing) during high temperature exposure. Nitrogen element plays an important role in the observed phenomena.However, the determination of consequences after mechanical treatment on the titanium oxidation resistance is again difficult with the observations noted in this work. Actually, there is a simultaneous contributions of several factors: chemical, mechanical and structural.