<p dir="ltr">Carbon-Carbon (C/C) composites have been shown to be a preferred material for high temperature applications as they retain their properties and performance at temperatures in excess of 2000°C. This study shows that High Temperature Treatment (HTT) at 2400°C for 4 hrs followed by two subsequent Polymer Infiltration and Pyrolysis (PIP) cycles using SC1008 phenolic resin changes the failure mechanism of 2D C/C which has been subject to directional ablation prior to flexural testing. The study observes that prior directional ablation of the non-HTT C/C condition decreases flexural strength by 50.2%, whereas negligible change for the HTT C/C condition was observed (6.6%). This is attributed to the significant degradation of the tensile surface of the non-HTT C/C during ablation corresponding to an average linear thickness loss of 0.321mm (Std Dev = 0.223mm) and average mass loss of 0.364g (Std Dev = 0.196g) while the HTT recorded 0.033mm (Std Dev = 0.005mm) and 0.032g (Std Dev = 0.008g) respectively. The difference in degradation is attributed to the microstructure which was characterised through X-Ray Diffraction and Scanning Electron Microscopy. It is shown that HTT transformed the carbon matrix from a glassy/amorphous matrix to a layered matrix with an indicative increased degree of graphitisation (from 0.52 to 0.69). This not only increased the average density from 1.511 g/cm³ (Std Dev = 0.002 g/cm³) to 1.652 g/cm³ (Std Dev = 0.003 g/cm³) but also increased the average thermal conductivity from 9.1 W/mK (Std Dev = 1.06 W/mK) to 13.3 W/mK (Std Dev = 1.32 W/mK). This ultimately contributed to a reduction in available sites for the oxidation reaction to occur, while also allowing for thermal energy to be conducted away from the ablation surface reducing the amount of heat related damage. For conditions without and with prior ablation damage, the non-HTT C/C is found to fail in matrix dominated tension with the fibres and matrix breaking in a single plane originating at the tensile surface and propagating towards the neutral axis whereas the HTT C/C is found to fail in shear at the neutral axis with the fibres-matrix debonding being the primary failure mechanism. The non-HTT C/C is found to have an average flexural strength of 88.8 MPa (Std Dev = 13.7 MPa) and flexural modulus 81.0 GPa (Std Dev = 10.5 GPa), where the HTT C/C has 196.7 MPa (Std Dev = 31.4 MPa) and 115.2 GPa (Std Dev = 3.3 GPa) respectively. Lastly, this study found that a square notch in the non-HTT C/C condition resulted in a 23.9% and 26.4% reduction in flexural strength for conditions without and with prior ablation damage, respectively. No change in the failure mechanism was observed for notched specimens compared to un-notched specimens, and the debit in strength was attributed to broken fibers created by the notch.</p>

Made available in DSpace on 2014-12-17T14:58:09Z (GMT). No. of bitstreams: 1 HallyjusADB_DISSERT.pdf: 2542860 bytes, checksum: a76cbfa6200b38f0f8ff5811d0315d59 (MD5) Previous issue date: 2011-02-18 / Composite materials have a wide application in various sectors, such as the medical field in the manufacture of prostheses, in automotive and aerospace. Thus it is essential to the development of new composite and a better understanding in the face of various loading conditions and service. Several structural elements are manufactured in the presence of geometric discontinuity (notch, hole, etc ) in their longitudinal sections and/or cross-cutting, and these affect the mechanical response of these elements. The objective is to study the mechanical response of laminated polymer matrix hybrid composites reinforced with glass fiber/jute in a uniaxial tensile test. The mechanical response takes in account both the influence of the presence of a geometric discontinuity (semicircular notches) and the orientation of fibers in the layers (anisotropy). The semicircular notches are located in longitudinal section (with a reduction in cross section) of the same. In this analysis, the anisotropy is characterized by types of configurations (with different orientations of fibers in the outer layers). A comparative study of mechanical properties with and without the presence of notches is developed. Both configurations consist of four layers of woven jute fiber bidirectional and a central layer of bidirectional woven glass fibers. In addition to the mechanical properties was also studied the characteristics of the fracture developed in each composite laminate. The results showed that in the comparative study, the anisotropy and the presence of semicircular notches directly influences the mechanical behavior of laminates composites, mainly in reducing the tensile strength, and well as the final characteristics of the fracture / Os materiais comp?sitos t?m uma ampla aplica??o nos mais variados setores, como por exemplo, na ?rea m?dica na confec??o de pr?teses, na ind?stria automotiva e no setor aeroespacial. Assim ? essencial o desenvolvimento de novos comp?sitos e uma melhor compreens?o frente ?s mais diversas condi??es de carga e servi?o. V?rios elementos estruturais s?o fabricados na presen?a de descontinuidade geom?trica (entalhe, furo etc.) em suas se??es longitudinais e/ou transversais, e essas prejudicam a resposta mec?nica desses elementos. O objetivo do trabalho ? estudar a resposta mec?nica de laminados comp?sitos h?bridos de matriz polim?rica refor?ado com fibras de vidro/juta em um ensaio de tra??o uniaxial. A resposta mec?nica leva em conta tanto a influ?ncia da presen?a de uma descontinuidade geom?trica (entalhes semicirculares) quanto da orienta??o das fibras nas camadas (anisotropia). Os entalhes semicirculares est?o localizados na se??o longitudinal (com redu??o da se??o transversal) dos mesmos. Nessa an?lise, a anisotropia ? caracterizada por dois tipos de configura??es (com diferentes orienta??es das fibras nas camadas externas). Um estudo comparativo das propriedades mec?nicas com e sem a presen?a dos entalhes ? desenvolvido. As duas configura??es consistem de quatro camadas de tecidos bidirecionais de fibras de juta e uma camada central de tecido bidirecional de fibras de vidro. Al?m das propriedades mec?nicas, tamb?m foi estudada as caracter?sticas da fratura desenvolvidas em cada laminado comp?sito. Os resultados mostraram que, no estudo comparativo, a anisotropia e a presen?a dos entalhes semicirculares influi diretamente no comportamento mec?nico dos laminados comp?sitos, principalmente na redu??o da resist?ncia ? tra??o, e bem como na caracter?stica final da fratura

Hot sections of gas engine turbines require specialized materials to withstand extreme conditions present during engine operation. Nickel-base superalloys are typically used as blades and disks in the high pressure turbine section because they possess excellent fatigue strength, creep strength and corrosion resistance at elevated temperatures. Components undergo thermomechanical fatigue conditions as a result of transient engine operation. Sharp geometric features, such as cooling holes in blades or fir-tree connections in disks, act as local stress raisers. The material surrounding these features are potential sites of localized inelastic deformation and crack formation. To reduce customer costs associated with unnecessary overhauls or engine down-time, gas turbine manufacturers require accurate prediction methods to determine component endurances. The influence of stress concentration severity on thermomechanical fatigue crack formation is of particular importance as cracks often initiate in these hot spots. Circumferentially notched specimens were utilized to perform thermomechanical fatigue experiments on blade material CM247LC DS and disk material PM IN100. A parametric study on CM247LC DS was performed utilizing four notched specimens. Experimental results were coupled with finite element simulations utilizing continuum based constitutive models. The effects of applied boundary conditions on crack initiation life was studied in both alloys by performing experiments under remotely applied force and displacement boundary conditions. Finite element results were utilized to develop a life prediction method for notched components under thermomechanical fatigue conditions.

As novas ligas de alumínio que contém lítio são atraentes devido à sua baixa densidade, alto módulo elástico, elevada resistência mecânica e por terem boa resistência à corrosão em comparação com ligas similares que não contém lítio. A degradação do material devido à fadiga e corrosão são os dois principais fatores que contribuem para o envelhecimento de uma aeronave. O objetivo deste trabalho é estudar a resistência à fadiga de uma nova liga de Al-Li, denominada de AA 2050-T84, considerando os estágios de nucleação e de propagação. No primeiro caso são avaliados o efeito da variação do concentrador de tensão (kt) e o efeito da razão de tensões (R), enquanto que no segundo caso são estudados os efeitos da direção de laminação e da razão de tensões (R) na taxa de propagação da trinca por fadiga. Para o estágio de iniciação é possível observar que quanto maior o valor de R, menor é a vida em fadiga. Para um R constante, o concentrador de tensão reduz significantemente a vida em fadiga. Considerando a vida de propagação de trinca por fadiga, observa-se que, independente da direção de laminação, quanto maior o valor de R, para um mesmo &Delta;K, maior foi a taxa de propagação de trinca. Para um mesmo R, o expoente m da equação de Paris é maior na direção TL indicando maior velocidade de crescimento de trinca. Independentemente da direção tomada, quanto maior o valor de R maior o valor de m. O modelo matemático utilizado previu muito bem o efeito de R na taxa de propagação de trinca. A liga AA 2050 apresenta resistência à fadiga similar ligas das famílias 2XXX e 7XXX e similar a da liga Al-Li AA 2198 T8. / The new Al-Li alloys are very attractive due to its low density, high elastic modulus, increased mechanical strength, as well as good corrosion resistance in comparison with similar alloys that don\'t contain lithium. The material\'s degradation due to fatigue and corrosion are the main factors of aircrafts aging, and it is quite important to take them in account to guarantee the aircraft structural integrity. The aim of this work is to study the fatigue strength of a new Al-Li alloy, denominated as AA 2050 T84, considering both nucleation and propagation fatigue lives. In the first case were evaluated the effect of the variation of the stress concentrator (kt) and the effect of the stress ratio (R), while in the propagation life were considered the effect of the rolling direction and the stress ratio (R). From the initiation life results, it is possible to observe that as higher was R, lower is fatigue life and that the intensity of the stress concentrator reduces fatigue life significantly, independent of the R value. The results from the propagation life shows that in both LT e TL directions and for a constant &Delta;K, higher R induces larger fatigue crack propagation rates. Considering a constant R, the TL direction presents a larger exponent m of Paris equation, which is an indicative of higher larger crack propagation rate. Also, larger R causes larger m, independently of the rolling direction. The mathematical model used was able to take in account the R effect on the crack propagation rate. Considering the more traditional Al alloys from 2XXX and 7XXX families, and the Ali-Li alloys AA 2198 T8, the AA 2050 presented a quite similar fatigue behavior.

[pt] A técnica de correlação digital de imagens (Digital Image Correlation, DIC) é uma técnica óptica de campo global que consiste na análise de imagens da superfície de um espécime antes e após seu carregamento para determinação de campos de deslocamentos e deformações. Neste trabalho foram usados um sistema DIC estereoscópico convencional 3D, para aplicações em campos de visão (macro) da ordem de 200mmx200mm, e um sistema DIC estereomicroscópico 3D, para aplicações em áreas tão pequenas quanto 1mm quadrado. Para a análise de deformações em campos com dimensões tão diferentes precisou-se desenvolver uma metodologia para controlar parâmetros da técnica DIC, tais como dimensões de pontos (speckles) impressos no espécime e tamanhos de subsets e steps usados para a correlação das imagens captadas. A seleção dos problemas estruturais para aplicação da técnica levou em conta não só a diversidade destes, como também o pioneirismo das aplicações de DIC a problemas nos quais podem ser gerados resultados que melhor ajudem na compreensão de suas facetas específicas. Assim, a técnica foi aplicada à medição de deformações em tubos com defeitos por suas vantagens de medição de grandes deformações e de visualização de regiões de interesse, sob a forma de campos globais de deformações. Na área de determinações de propriedades mecânicas de materiais compósitos, foram realizadas medições em espécimes não convencionais de resina epóxi reforçados por fibras de carbono ou fibras de vidro para determinação de suas propriedades elásticas. Por fim, foram realizadas medições em um espécime Compact Tension Specimen CTS de aço grau API 5LX60 contendo uma trinca e em espécimes com entalhes profundos (concentrações de tensões) constituídos por materiais distintos (policarbonato e alumínio), para obtenção de campos de deslocamentos e de deformações elastoplásticas. Nestas aplicações os resultados obtidos com a técnica DIC foram comparados com aqueles obtidos com modelos de elementos finitos (EF), com medições com extensômetros de resistência elétrica (strain gages) e com resultados analíticos publicados na literatura. Levando-se em conta as comparações feitas, a grande maioria dos experimentos realizados pode ser considerada satisfatória. Ao longo da tese foram descritas as adaptações, considerações e boas práticas consideradas necessárias para obtenção de bons resultados nas diferentes medições e para os diferentes aparatos experimentais utilizados. Estas recomendações serão bastante úteis para medições futuras ou mesmo para auxiliar na avaliação de confiabilidade de alguns resultados apresentados na literatura especializada. / [en] The digital image correlation (DIC) technique is a global field optical technique that consists in the analysis of images taken from the surface of a specimen before and after being subjected to a load, in order to determine displacement and strain fields. In the current work, both conventional 3D stereoscopic and micro-stereoscopic DIC systems were used, the former for applications in macroscopic fields of view (of the order of 200mm x 200mm), and the latter for applications in surface areas as small as 1mm square. For strain analysis in fields with such varied dimensions, the development of a methodology to control some parameters of the technique was required. Among the parameters to be controlled were dimensions of speckles printed on the specimen and size of the subsets and steps used in the image correlation procedure. The selection of structural problems to be analyzed by the DIC technique took into account not only diversity, but also the pioneering aspect in terms of DIC application to problems which can generate results that lead to a better comprehension of its specific issues. Hence, the technique was applied to the measurement of global strain fields in defective tubes, due to the advantages in measuring large strains and visualizing the regions of interest in such cases. For determination of the mechanical properties of composite materials, measurements were performed in non-conventional specimens made of epoxy resin and reinforced by carbon or glass fibers for evaluation of its elastic properties. Finally, measurements in a cracked Compact Tension Specimen (CTS) with degree of steel API 5LX60 and in specimens with deep notches (stress concentration) consisting of different materials (polycarbonate and aluminum) were carried out for estimation of displacement fields and elastoplastic strains. For those applications, the results were compared with those obtained from finite element models, from strain gages, and also with analytical results from the literature. Taking into account such comparisons, it can be said that the great majority of the experimental measurements was satisfactory. Throughout the current manuscript, the required adaptations, good practices needed to achieve reliable results from the different types of measurement and experimental apparatus, as well as other considerations, were carefully described. These recommendations will be quite useful for future measurements, or even to assist in the evaluation of the reliability of certain results presented in the specialized literature.

As novas ligas de alumínio que contém lítio são atraentes devido à sua baixa densidade, alto módulo elástico, elevada resistência mecânica e por terem boa resistência à corrosão em comparação com ligas similares que não contém lítio. A degradação do material devido à fadiga e corrosão são os dois principais fatores que contribuem para o envelhecimento de uma aeronave. O objetivo deste trabalho é estudar a resistência à fadiga de uma nova liga de Al-Li, denominada de AA 2050-T84, considerando os estágios de nucleação e de propagação. No primeiro caso são avaliados o efeito da variação do concentrador de tensão (kt) e o efeito da razão de tensões (R), enquanto que no segundo caso são estudados os efeitos da direção de laminação e da razão de tensões (R) na taxa de propagação da trinca por fadiga. Para o estágio de iniciação é possível observar que quanto maior o valor de R, menor é a vida em fadiga. Para um R constante, o concentrador de tensão reduz significantemente a vida em fadiga. Considerando a vida de propagação de trinca por fadiga, observa-se que, independente da direção de laminação, quanto maior o valor de R, para um mesmo &Delta;K, maior foi a taxa de propagação de trinca. Para um mesmo R, o expoente m da equação de Paris é maior na direção TL indicando maior velocidade de crescimento de trinca. Independentemente da direção tomada, quanto maior o valor de R maior o valor de m. O modelo matemático utilizado previu muito bem o efeito de R na taxa de propagação de trinca. A liga AA 2050 apresenta resistência à fadiga similar ligas das famílias 2XXX e 7XXX e similar a da liga Al-Li AA 2198 T8. / The new Al-Li alloys are very attractive due to its low density, high elastic modulus, increased mechanical strength, as well as good corrosion resistance in comparison with similar alloys that don\'t contain lithium. The material\'s degradation due to fatigue and corrosion are the main factors of aircrafts aging, and it is quite important to take them in account to guarantee the aircraft structural integrity. The aim of this work is to study the fatigue strength of a new Al-Li alloy, denominated as AA 2050 T84, considering both nucleation and propagation fatigue lives. In the first case were evaluated the effect of the variation of the stress concentrator (kt) and the effect of the stress ratio (R), while in the propagation life were considered the effect of the rolling direction and the stress ratio (R). From the initiation life results, it is possible to observe that as higher was R, lower is fatigue life and that the intensity of the stress concentrator reduces fatigue life significantly, independent of the R value. The results from the propagation life shows that in both LT e TL directions and for a constant &Delta;K, higher R induces larger fatigue crack propagation rates. Considering a constant R, the TL direction presents a larger exponent m of Paris equation, which is an indicative of higher larger crack propagation rate. Also, larger R causes larger m, independently of the rolling direction. The mathematical model used was able to take in account the R effect on the crack propagation rate. Considering the more traditional Al alloys from 2XXX and 7XXX families, and the Ali-Li alloys AA 2198 T8, the AA 2050 presented a quite similar fatigue behavior.

The diploma thesis deals with the evaluation of the lifetimes of smooth and notched specimens. The comparison of their lifetimes is focused on the case of high-frequency cyclic loading in the area of high-cycle and gigacycle fatigue of materials. The theory of critical distances is used to evaluate and recalculate the life curves of the notched specimens. The effect of the notch is quantified using the Line method. The critical length parameter is determined so that the life curve of the notched specimens corresponds to the curve measured on smooth specimens. The result is the dependence of the critical length parameter on the number of cycles to fracture. Knowledge of critical length parameters can be used to determine the lifetime of notched specimens as well as real notched components using the results of fatigue tests of smooth specimens.

Neuromorphic computing applications could be made faster and more power efficient by emulating the function of a biological synapse. Non-conventional spintronic devices have been proposed that demonstrate synaptic behavior through domain wall (DW) driving. In this work, current induced domain wall motion has been studied through micromagnetic simulations. We investigate the synaptic behavior of a head to head domain wall driven by a spin polarized current in permalloy (Py) nanostrips with shape anisotropy, where triangular notches have been modeled to account for edge roughness and provide pinning sites for the domain wall. We seek optimal material parameters to keep the critical current density for driving the domain wall at order 1011 A/m2.