Apresenta-se um estudo, por meio do método dos elementos finitos, de problemas quase-estáticos de trincas em materiais anisotrópicos. Os fatores de intensidade de tensão em modo misto de carregamento foram determinados utilizando-se as metodologias da integral Jk, da correlação dos deslocamentos e da integral de fechamento de trinca modificada. Para a integral Jk, foi desenvolvida uma formulação baseada nas leis da conservação da elasto-estática e das integrais independentes do percurso. Na expressão, para a integral J2 levou-se em consideração o termo não singular da representação analítica do campo de tensões. Desta forma, foi obtida uma expressão analítica para a descontinuidade na densidade de energia de deformação, presente na integral J2. Com os valores da integral Jk, os fatores de intensidade de tensão puderam ser determinados diretamente. Com a mesma sistemática, desenvolvida para a integral J2, determinou-se a integral J1 para problemas envolvendo carregamento nas faces da trinca. Os resultados obtidos estão de acordo com os resultados presentes na literatura considerando ortotropia de material, ainda que para algumas configurações o mesmo é tratado como um caso de anisotropia geral. Assim como a integral J1 a integral J2 mostrou-se independente do contorno envolvendo a ponta da trinca. / A study is proposed based on crack quasi-static problems in anisotropic materials by the finite element method. The mixed-mode stress intensity factors were determined by the Jk integral, displacement correlation and modified crack closure integral methodologies. The Jk integral was derived from a conservation law of linear elasticity theory. In the formulation to obtain the J2 integral the non-singular term in the stress fields was considered. An analytical expression was obtained to discontinuity of the strain energy density in the crack faces, presented by J2 integral. A similar approach was applied to determine J1 integral in crack surface traction problems. The results confer with the results present in the literature considering orthotropic materials. In some configurations the problem is treated from general anisotropy theory. In the same way that J1 integral the path-independence property was established to J2 integral.

This thesis is on fatigue crack growth experiments and assessments of fatigue crack growth rates. Both constant and variable amplitude loads in two different materials are considered; a nickel based super-alloy Inconel 718 and a stainless steel 316L. The considered load levels extend from small scale yielding (SSY) to large scale yielding (LSY) for both materials. The effect of different load schemes on the fatigue crack growth rates is investigated on Inconel 718 and compact tension specimens in Paper A. It is concluded that load decreasing schemes give a to high Paris law exponent compared to constant or increasing load amplitude schemes. Inconel 718 is further analyzed in Paper B where growth rates at variable amplitude loading in notched tensile specimens are assessed. The predictions are based on the fatigue crack growth parameters obtained in Paper A. The crack closure levels are taken into consideration and it is concluded that linear elastic fracture mechanics is incapable of predicting the growth rates in notches that experience large plastic cyclic strains. Even if crack closure free fatigue parameters are used and residual stresses due to plasticity are included. It is also concluded that crack closure free and nominal fatigue crack growth data predict the growth rates equally well. However, if the crack closure free parameters are used, then it is possible to make a statement in advance on the prediction in relation to the experimental outcome. This is not possible with nominal fatigue crack growth parameters. The last three papers consider fatigue crack growth in stainless steel 316L. Here the load is defined as the crack tip opening displacement parameter. Paper C constitutes an investigation on the effect of plastic deformation on the potential drop and consequently the measured crack length. It is concluded that the nominal calibration equation obtained in the undeformed geometry can be used at large plastic deformations. However, two conditions must be met: the reference potential must be taken in the deformed geometry and the reference potential needs to be adjusted at every major change of plastic deformation. The potential drop technique is further used in Paper D and Paper E for crack length measurements at monotonic LSY. Constant amplitude loads are considered in Paper D and two different variable amplitude block loads are investigated in Paper E. The crack tip opening displacement is concluded in Paper D to be an objective parameter able to characterize the load state in two different geometries and at the present load levels. Furthermore, if the crack tip opening displacement is controlled in an experiment and the local load ratio set to zero, then only monotonic LSY will appear due to extensive isotropic hardening, i.e. elastic shake-down. This is also the reason why the linear elastic stress-intensity factor successfully could merge all growth rates, extending from SSY to monotonic LSY along a single line in a Paris law type of diagram, even though the generally accepted criteria for SSY is never fulfilled. For the variable amplitude loads investigated in Paper E, the effect of plastic deformation on measured potential drop is more pronounced. However, also here both the crack tip opening displacement parameter and the linear elastic stress-intensity factor successfully characterized the load state. / <p>QC 20130108</p>

科学研究費補助金 研究種目:基盤研究(B)(2) 課題番号:09450047 研究代表者:田中 啓介 研究期間:1997-1999年度

The ability to predict fatigue crack growth rates is essential in safety critical systems. The discovery of fatigue crack closure in 1970 caused a flourish of research in attempts to simulate this behaviour, which crucially affects crack growth rates. Historically, crack tip plasticity models have been based on one-dimensional rays of plasticity emanating from the crack tip, either co-linear with the crack (for the case of plane stress), or at a chosen angle in the plane of analysis (for plane strain). In this thesis, one such model for plane stress, developed to predict fatigue crack closure, has been refined. It is applied to a study of the relationship between the apparent stress intensity range (easily calculated using linear elastic fracture mechanics), and the true stress intensity range, which includes the effects of plasticity induced fatigue crack closure. Results are presented for all load cases for a finite crack in an infinite plane, and a method is demonstrated which allows the calculation of the true stress intensity range for a growing crack, based only on the apparent stress intensity range for a static crack. Although the yield criterion is satisfied along the plastic ray, these one-dimensional plasticity models violate the yield criterion in the area immediately surrounding the plasticity ray. An area plasticity model is therefore required in order to model the plasticity more accurately. This thesis develops such a model by distributing dislocations over an area. Use of the model reveals that current methods for incremental plasticity algorithms using distributed dislocations produce an over-constrained system, due to misleading assumptions concerning the normality condition. A method is presented which allows the system an extra degree of freedom; this requires the introduction of a parameter, derived using the Prandtl-Reuss flow rule, which relates the magnitude of slip on complementary shear planes. The method is applied to two problems, confirming its validity.

En raison de la gravité des accidents liés au phénomène de fatigue-propagation de fissure, les préoccupations de l’industrie aéronautique à assurer l’intégrité des structures soumises à ce mode de sollicitation revêtent un caractère tout à fait essentiel. Les travaux de thèse présentés dans ce mémoire visent à appréhender le problème de sûreté des structures aéronautiques dimensionnées en tolérance aux dommages sous l’angle probabiliste. La formulation et l’application d’une approche fiabiliste menant à des processus de conception et de maintenance fiables des structures aéronautiques en contexte industriel nécessitent cependant de lever un nombre important de verrous scientifiques. Les efforts ont été concentrés au niveau de trois domaines dans ce travail. Une méthodologie a tout d’abord été développée afin de capturer et de retranscrire fidèlement l’aléa du chargement de fatigue à partir de séquences de chargement observées sur des structures en service et monitorées, ce qui constitue une réelle avancée scientifique. Un deuxième axe de recherche a porté sur la sélection d’un modèle mécanique apte à prédire l’évolution de fissure sous chargement d’amplitude variable à coût de calcul modéré. Les travaux se sont ainsi appuyés sur le modèle PREFFAS pour lequel des évolutions ont également été proposées afin de lever l’hypothèse restrictive de périodicité de chargement. Enfin, les analyses probabilistes, produits du couplage entre le modèle mécanique et les modélisations stochastiques préalablement établies, ont entre autre permis de conclure que le chargement est un paramètre qui influe notablement sur la dispersion du phénomène de propagation de fissure. Le dernier objectif de ces travaux a ainsi porté sur la formulation et la résolution du problème de fiabilité en tolérance aux dommages à partir des modèles stochastiques retenus pour le chargement, constituant un réel enjeu scientifique. Une méthode de résolution spécifique du problème de fiabilité a été mise en place afin de répondre aux objectifs fixés et appliquée à des structures jugées représentatives de problèmes réels. / Ensuring the integrity of structural components subjected to fatigue loads remains an increasing concern in the aerospace industry due to the detrimental accidents that might result from fatigue and fracture processes. The research works presented here aim at addressing the question of aircraft safety in the framework of probabilistic fracture mechanics. It should be noticed that a large number of scientific challenges requires to be solved before performing comprehensive probabilistic analyses and assessing the mechanical reliability of components or structures in an industrial context. The contributions made during the PhD are reported here. Efforts are provided on each step of the global probabilistic methodology. The modeling of random fatigue load sequences based on real measured loads, which represents a key and original step in stochastic damage tolerance, is first addressed. The second task consists in choosing a model able to predict the crack growth under variable amplitude loads, i.e. which accounts for load interactions and retardation/acceleration effects, at a moderate computational cost. The PREFFAS crack closure model is selected for this purpose. Modifications are brought in order to circumvent the restrictive assumption of stationary load sequences. Finally, probabilistic analyses resulting from the coupling between the PREFFAS model and the stochastic modeling are carried out. The following conclusion can especially be drawn. Scatter in fatigue loads considerably affects the dispersion of the crack growth phenomenon. Then, it must be taken into account in reliability analyses. The last part of this work focuses on phrasing and solving the reliability problem in damage tolerance according to the selected stochastic loading models, which is a scientific challenge. A dedicated method is established to meet the required objectives and applied to structures representative of real problems.