Modélisation de la propagation de fissure en fatigue par une approche locale de la rupture

International audienceIn the aeronautical field, fatigue crack propagation analysis is commonly performed at the macroscopic level through a global energetic approach that considers the material in its elastic domain. Within this framework, the plastic zone is assumed to be confined at the crack tip, in the singularity area. However, recent observations on specimens made of Nickel-based superalloys at 550◦C [1] tend to highlight nonlinear phenomena occurring in the process zone, ahead of the crack tip. This plasticity leads to deterioration mechanisms, and to a disturbed crack front, with flat to slant fracture in mode I loading or “tunneling effect” under holding-times. To deal with such complex fracture problems, elastic fracture mechanics is not anymore adapted. To model fatigue crack propagation in a Ni-based superalloy used in the high-pressure stages of aeroengines [2], the present study proposes to use a local approach to fracture. It consists in estimating more accurately the stress and strain fields in the crack tip area where plasticity occurs. The knowledge of these mechanical fields offers the possibility to characterize the fracture processes by the use of either a damage criterion in post-processing or a fully coupled damage model. This last one can be phenomenological and established within the Thermodynamics of Irreversible Processes and the Continuum Damage Theory frameworks [3, 4], by fully coupling the elasto-viscoplastic behavior and damage. This damage is the combination of different deterioration mechanisms. The most relevant one is fatigue damage which represents persistent slip bands that appear after several reversal loadings. In addition, creep damage also needs to be taken into account, representing holding-period degradation processes at the grain boundaries. Finally, ductile damage can have a contribution for the highly loaded plastic zone in the vicinity of the crack tip. Fatigue damage is, most of the time, cyclically estimated by the use of a damage law written in terms of loading parameters such as the loading ratio or the stress amplitude. The innovative aspect of the present study is to model fatigue damage in an incremental manner to avoid using cycle-counting algorithms. The main issue with incremental fatigue damage is to describe properly the mean-stress effect. As part of the solution, this study proposes to take into account, in the constitutive equations, the microcracks’ closure effect [3]. Another issue is associated with the fact that there is a full coupling between damage and the elastoviscoplastic behavior. In this case, the structure will progressively exhibit a softening behavior. Then, the well-posedness of the equilibrium problem is not verified anymore and the constitutive equations lose their ellipticity. When performing Finite Element calculations, this leads to spurious localization problems. To obtain mesh-independent results, non-local methods [4, 5] are thus considered.Cette étude concerne l’analyse de la fissuration dans les superalliages base Nickel employés dans les zones chaudes des turbines aéronautiques. Dans ce but, un modèle de propagation de fissure en fatigue incrémental en temps, via des endommagements couplés au comportement élasto-viscoplastique du matériau, est développé à l’aide d’une approche locale de la rupture. Afin de rendre compte à la fois des phénomènes complexes présents en pointe de fissure, des éventuelles instabilités de fissuration, et du type de chargement ; des endommagements induits par le fluage, la ductilité et l’oxydation peuvent interagir avec la fatigue. Une régularisation du modèle via une approche non-locale garantira sa robustesse lors de calculs de structures par éléments finis