Fatigue crack growth behavior of AA7050 T7451 aluminum alloy under mode II loading condition in two orientations was investigated. Compact shear specimens were prepared in TL and LT directions. A loading frame for mode II type of loading was manufactured. Using the loading frame and the specimen, KIIC values and mode II fatigue crack growth rates were calculated. Fractographic analysis of the fracture surfaces of both mode II fracture toughness test specimens and mode II fatigue crack growth test specimens were done to examine the effects of mode II load. KIIC values were measured between 1.3 and 1.5 times the KIC values for this alloy. As for mode II fatigue crack growth rates, TL orientation shows the highest mode II fatigue crack growth resistance.

Hybrid Titanium Composite Laminates (HTCL) have vast potential for future commercial aircraft development. In order for this potential to be properly utilized the HTCLs material properties must first be well understood and obtained through experimentation. Crack initiation and crack growth characteristics of HTCLs are dependent on the heat treatment of the embedded constituent titanium foil. While high strength titanium foils may delay crack initiation, there may be an adverse effect of unsuitable crack growth rates in the HTCLs. Literature has indicated that when properly designed, cracks in HTCLs can arrest due to fiber bridging mechanisms and other crack closure mechanisms. Traditional surface inspection techniques employed on facesheet laminate evaluations will not be able to properly monitor the internal crack growth and damage progression for the internal plies. The main objective of the this joint Georgia Tech/Boeing research project was to determine and compare crack initiation and crack growth characteristics of different heat-treated -Ti 15-3 titanium foil embedded in HTCLs. Georgia Tech utilized a unique capability of x-raying the internal foils of the HTCL specimen in a servo-hydraulic test frame while under load. The titanium foil in this study represented four different heat treatments that result in four increasing levels of strength and decreasing levels of elongation. Specifically, open-hole HTCL coupons were tested at four stress load levels under constant amplitude fatigue cycles to determine a-N curves for the HTCL layups evaluated. The layup evaluated was [45/0/-45/0/Ti/0/-45/0/45]. Crack growth rates were determined once the initiated crack was detected via radiographic exposure. Radiographic delamination analysis and thermoelastic stress analysis techniques were employed to determine additional damage mechanisms in the laminate. Analytical and finite element methods were utilized to determine ply stresses. Additionally, titanium foil properties were determined via dog-bone coupons for each of the four heat treatment conditions.

The effect of different aging treatments on fatigue crack growth behavior of AA6013 aluminum alloy was investigated. C(T) (Compact Tension) specimens were prepared in L-T and T-L direction for fatigue crack growth tests. Samples were in T651 as received, T42 which is solution heat treated at 538 &ordm / C for 90 minutes, water quenched and aged in room temperature for 96 hours, and one group of samples were overaged at 245 &ordm / C for 12 hours after T42 condition was achieved. Hardness and conductivity measurements were achieved for all conditions after the heat treatments. Fatigue crack growth tests were performed at as received condition T651, T42 and 245 &ordm / C aged samples in laboratory air with sinusoidal loading of stress ratio R=0.1 and at a frequency of 1 Hz. The highest fatigue crack growth resistance is observed for T651 T-L and 245 &ordm / C overaged L-T condition.

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Die vorliegende Arbeit beschäftigt sich mit der zweidimensionalen Simulation der Rissausbreitung mit Hilfe der adaptiven Finite-Elemente-Methode. Das Ziel war die Entwicklung von Algorithmen zur effizienten und automatisierten Modellierung des Risswachstums. Das zugrunde liegende Konzept besteht in der vollständigen Integration aller Teilschritte der Risswachstumssimulation in ein einziges FE-Programm. Während der gesamten Simulation erfolgt durch den Einsatz eines fehlergesteuerten h-adaptiven Verfahrens die automatische Anpassung der FE-Diskretisierung an das gestellte Rissproblem. Die Simulation der spröden Rissausbreitung erfolgt auf Basis der linear-elastischen Bruchmechanik. Die dafür benötigten Spannungsintensitätsfaktoren werden mit Hilfe des J-Integrals in Form der Interaction-Integral-Technik ermittelt. Die Simulation des duktilen Versagens in der Prozesszone an der Rissspitze wird mit Hilfe des Schädigungsmodells von Rousselier beschrieben. Das Kriterium für duktiles Risswachstum basiert auf der Auswertung des akustischen Tensors an der Rissspitze und legt den Beginn der makroskopischen Rissausbreitung mit dem Einsetzen der Lokalisierung fest.

Turbine engine blades are subjected to extreme conditions characterized by significant and simultaneous excursions in both stress and temperature. These conditions promote thermo-mechanical fatigue (TMF) crack growth which can significantly reduce component design life beyond that which would be predicted from isothermal/constant load amplitude results. A thorough understanding of the thermo-mechanical fatigue crack behavior in single crystal superalloys is crucial to accurately evaluate component life to ensure reliable operations without blade fracture through the use of "retirement for cause" (RFC). This research was conducted on PWA1484, a single crystal superalloy used by Pratt & Whitney for turbine blades. Initially, an isothermal constant amplitude fatigue crack growth rate database was developed, filling a void that currently exists in published literature. Through additional experimental testing, fractography, and modeling, the effects of temperature interactions, load interactions, oxidation and secondary crystallographic orientation on the fatigue crack growth rate and the underlying mechanisms responsible were determined. As is typical in published literature, an R Ratio of 0.7 displays faster crack growth when compared to R = 0.1. The effect of temperature on crack growth rate becomes more pronounced as the crack driving force increases. In addition secondary orientation and R Ratio effects on crack growth rate were shown to increase with increasing temperature. Temperature interaction testing between 649°C and 982°C showed that for both R = 0.1 and 0.7, retardation is present at larger alternating cycle blocks and acceleration is present at smaller alternating cycle blocks. This transition from acceleration to retardation occurs between 10 and 20 alternating cycles for R = 0.1 and around 20 alternating cycles for R = 0.7. Load interaction testing showed that when the crack driving force is near KIC the overload size greatly influences whether acceleration or retardation will occur at 982°C. Semi-realistic spectrum testing demonstrated the extreme sensitivity that relative loading levels play on fatigue crack growth life while also calling into question the importance of dwell times. A crack trajectory modeling approach using blade primary and secondary orientations was used to determine whether crack propagation will occur on crystallographic planes or normal to the applied load. Crack plane determination using a scanning electron microscope enabled verification of the crack trajectory modeling approach. The isothermal constant amplitude fatigue crack growth results fills a much needed void in currently available data. While the temperature and load interaction fatigue crack growth results reveal the acceleration and retardation that is present in cracks growing in single crystal turbine blade materials under TMF conditions. This research also provides a deeper understanding of the failure and deformation mechanisms responsible for crack growth during thermo-mechanical fatigue. The crack path trajectory modeling will help enable "Retirement for Cause" to be used for critical turbine engine components, a drastic improvement over the standard "safe-life" calculations while also reducing the risk of catastrophic failure due to "chunk liberation" as a function of time. Leveraging off this work there exists the possibility of developing a "local approach" to define a crack growth forcing function in single crystal superalloys.

The objective of this study is to develop crack growth analysis methods for functionally graded materials under mode I cyclic loading by using finite element technique. The study starts with the analysis of test specimens which are given in ASTM standard E399. The material properties of specimens are assumed to be changing along the thickness direction according to a presumed variation function used for the modeling of functionally graded materials. The results of the study reveal the influence of different material variation functions on the crack growth behavior. In the second part, the growth of an elliptical crack which is a common case in engineering applications is analyzed. First, mode I cycling loading is applied perpendicular to the crack plane and crack growth profiles for a certain number of cycles are obtained for homogeneous materials. Then, the code is extended for the analysis functionally graded materials. The material properties are assumed to vary as an exponential function along the major or minor axis direction of the crack. The results can be used to examine the crack profile and material constants&rsquo / influence for a certain number of cyclic loading.

[Truncated abstract] The fracture of brittle materials in uniaxial compression is a complex process with the development of cracks generated from initial defects. The fracture mechanism and pattern of crack growth can be altered considerably by the presence of a free surface. In proximity of a free surface, initially stable cracks that require an increase in the load to maintain the crack growth can become unstable such that the crack growth maintains itself without requiring further increase in the load. This leads to a sudden relief of accumulated energy and, in some cases, to catastrophic failures. In the cases of rock and rock mass fracturing, this mechanism manifests itself as skin rockbursts and borehole breakouts or as various non-catastrophic forms of failure, e.g. spalling. Hence, the study of crack-boundary interaction is important in further understanding of such failures especially for the purpose of applications to resource engineering. Two major factors control the effect of the free boundary: the distance from the crack and the boundary shape. Both these factors as well as the effect of the initial defect and the material structure are investigated in this thesis. Three types of boundary shapes - rectilinear, convex and concave - are considered. Two types of initial defects - a circular pore and inclined shear cracks are investigated in homogeneous casting resin, microheterogeneous cement mixes and specially fabricated granulate material. The preexisting defects are artificially introduced in the physical model by the method of inclusion and are found to successfully replicate the feature of pre-existing defects in terms of load-deformation response to the applied external load. It is observed that the possibility of crack growth and the onset of unstable crack growth are affected by the type of initial defect, inclination of the initial crack, the boundary shape and the location of the initial defect with respect to the boundary. The initial defects are located at either the centre or edge of the sample. The stresses required for the wing crack initiation and the onset of unstable crack growth is highest for the initial cracks inclined at 35° to the compression axis, lowest at 45° and subsequently increases towards 60° for all the boundary shapes and crack locations. In the case of convex boundary, the stress of wing crack initiation and the stress of unstable crack growth are lower than for the case of rectilinear and concave boundary for all the crack inclinations and crack locations. The crack growth from a pre-existing crack in a sample with concave boundary is stable, requiring stress increase for each increment of crack growth. The stress of unstable crack growth for the crack situated at the edge of the boundary is lower than the crack located at the centre of the sample for all the crack inclinations and boundary shapes.

Les céramiques sont sensibles à la fissuration lente qui résulte de l'effet conjoint entre un chargement mécanique et l'environnement (taux d'humidité et température). A partir d'études atomistiques disponibles dans la littérature, un modèle cohésif représentant localement la rupture assistée par l'environnement est proposé dans le cadre d'une formulation thermiquement activée. Nous montrons que cette description est capable de rendre compte de la fissuration lente en fatigue statique de monocristaux de céramiques, ainsi que la fissuration lente intergranulaire de polycristaux. Nous soulignons qu'une représentation de la fissuration lente avec la vitesse de propagation V en fonction du taux de restitutions d'énergie G rend compte des caractéristiques intrinsèques de la cinétique de rupture et est préférable à une présentation V-K. Le modèle cohésif permettant d'incorporer une longueur caractéristique dans la description, des effets de taille de grains sont explorés. La prise en compte des contraintes initiales d'origine thermique liées à l'élaboration est nécessaire pour prédire de manière réaliste l'accroissement du seuil de chargement en-dessous duquel aucune propagation n'a lieu ainsi que la résistance à la fissuration lente avec la taille de grains augmentant. La vitesse fissuration lente et le seuil de chargement K0 sont sensibles à l'environnement et notamment à la température et à la concentration d'eau. En augmentant la concentration d'eau et/ou la température, le seuil K0 diminue et la vitesse de fissuration lente augmente. Pour rendre compte de l'influence du taux d'humidité sur la fissuration lente, il est nécessaire de considérer une énergie d'activation ainsi qu'un seuil d'amorçage du mécanisme de réaction-rupture diminuant avec la concentration locale en eau. L'effet de la température est prédit de manière réaliste avec le modèle cohésif proposé et en tenant compte des contraintes initiales thermiques. Nous avons comparé les réponses en fissuration lente de l'alumine et de la zircone et montré qu'intrinsèquement et en l'absence de transformation de phase, la zircone résiste mieux à la fissuration lente que l'alumine. A partir de ces résultats, nous avons abordé l'étude de la fissuration lente de céramiques élaborées par projection plasma. Un endommagement initial de la microstructure à l'échelle des splats est observé sans qu'il n'influence la fissuration lente intra-splats en termes V-G. / Ceramic materials are prone to slow crack growth (SCG)due to the combined effect of the mechanical loading and the environment (moisture and temperature).Based on atomistic studies available in the literature,a thermally activated cohesive model is proposed to represent the reaction-rupture mechanism underlying slow crack growth. The description is shown able to capture SCG under static fatigue on ceramic single crystals as well as intergranular SCG in polycrystals.We emphasize that the representation of SCG with the crack velocity versus the energy release rate G accounts for the intrinsic characteristics of SCG, which is preferable than a usual plot with V-K curves.The cohesive model incorporates a characteristic length scale, so that size effects can be investigated. SCG is grain size dependent with the decrease of the crack velocity at a given load level and improvement of the load threshold with the grain size. To capture this observation, account for the initial thermal stresses related to the processing is mandatory. SCG is also dependent on the concentration of water with an increase of the crack velocity and a decrease of the load threshold with the relative humidity increasing. To predict this effect, the cohesive description needs to account for activation energy and a threshold to trigger the reaction-rupture that depends on the concentration of water. The influence of the temperature on SCG shows an increase in the crack velocity and a decrease of the load threshold for SCG due to the reduction in the initial thermal stresses. The SCG behavior of the alumina and zirconia is compared. Zirconia exhibits a better resistance to SCG compared to that of alumina, in the absence of any phase transformation due to lower kinetics of its reaction-rupture. Based on these results, SCG is investigated in plasma sprayed ceramic. An initial damage at the scale of the splats is observed without effect on load threshold G0 for SCG in V-G plots.

Les pales d’hélicoptère sont des structures composites soumises à un chargement cyclique multiaxial, et leur criticité impose de porter une attention particulière à la tolérance aux dommages. Leur revêtement peut potentiellement présenter des criques suite à certains évènements (impact, défaut, foudre). Ces travaux se focalisent sur un matériau de revêtement donné (tissu de verre) et concernent l’étude de la propagation de coupure (crique) sous chargement cyclique. Les sollicitations de service ont amené à considérer la traction et le cisaillement plan. Une étude expérimentale a été menée afin d’étudier les modes d’endommagement du matériau et sa résistance à la propagation de coupure pour différentes sollicitations (en traction et en cisaillement) et pour les drapages les plus courants. Elle a permis de dégager les mécanismes d’endommagement mis en jeu, et a fourni un ensemble important de propriétés matériau et de données quantitatives de vitesse de propagation. Elle a par ailleurs guidé vers une modélisation par éléments finis adaptée à l’architecture du matériau, et la manière dont il se dégrade en fatigue. Ce modèle repose sur un maillage à l’échelle de la mèche, et la prédiction de la propagation est obtenue par l’utilisation d’une courbe de fatigue S-N. La simulation a été évaluée par comparaison des faciès de rupture, des vitesses de propagation et de l’étendue des zones d’endommagement avec les essais réalisés sur éprouvettes. / Helicopter blades consist of composite structures which have to sustain multi-axial cyclic loading. Because of their criticality, damage tolerance has to be considered carefully. Their skin is subjected to environmental events like impact, flaw, lightning which can cause through-thethickness cracks. The present work focuses on one given skin material (woven glass fabric) and concerns the study of the through-the-thickness crack growth under cyclic loading. In-flight loading lead to consider tension and shear. An experimental study has been carried out to study damage in the material and its crackgrowth resistance under different loadings (tension and shear) and for usual stacking sequences. It highlighted damage mechanisms and provided an important set of material data and crack growth speeds. Besides, this led to a finite element approach adapted to the woven fabric architecture, anddamage feature under fatigue loading. This modeling is based on a bundle scale mesh, a semidiscrete damage modeling and an S-N curve to predict fiber failure. Numerical simulations of crack growth tests were carried out, and results were compared with experiments in terms of crack direction, crack growth speed, and size of damaged area.