An integrated micro/macro mechanical procedure for structural analysis of unidirectional metal matrix composites is proposed. The micromechanical analysis is performed via the Composite Cylinder Assemblage model (CCA) or the Representative Volume Element approach (RVE). The macroscopic stress-strain relation is based on a modification of the Vanishing Fiber Diameter theory (VFD), and the concept of “smeared” finite element. The fibers are considered to be linear elastic, and the matrix viscoplastic behavior is described by the Bodner and Partom model. The overall composite behavior is assumed to be elastic-viscoplastic.
Two types of material systems are employed, namely, SCS-6/Ti-15-3 and SCS-6/Tiβ21-S. Both set of material systems exhibit isotropic and/or kinematic hardening under specific conditions of temperature and loading. The proposed methodology is validated with experimental and analytical results available in the literature. After the validation process, this methodology is applied to a 3-D finite element model of a [0/90]2s SCS-6/Tiβ21-S turbine blade tip. Aerodynamic and centrifugal loading are considered acting at the same time. The turbine blade tip inelastic strain field is presented.