Abstract
Aero-engine components evolve through an iterative process involving the creation of the basic design to meet the performance requirements and the stress analyses and subsequent life evaluation of the individual components. A progressive increase in stage loading has resulted in more parts experiencing time as well as cycle dependent damage processes. The influence of cyclic softening in quantifying this effect is discussed. The implications of a fracture mechanics based damage tolerance approach in determining the lives of service discs is examined. The role of three-dimensional creep analysis, including the influence of transient thermal stress, in identifying critical areas in highly cooled rotor blades is discussed. Finally an approach for modelling anisotropic single crystal materials is illustrated.
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