On the fretting fatigue crack nucleation of complete, almost complete and incomplete contacts using an asymptotic method

In this work, the fretting crack nucleation of an aeronautical Ti-10V-2Fe-3Al titanium alloy is investigated. The main difficulty when designing complex industrial systems, especially helicopters rotor parts, lies in prediction assembly interfaces behaviour. Those areas can be subjected to loading characterized by a very confined multiaxial high stress gradient, leading fatigue nucleation. This kind failure reduces parts potential lifetime and increases therefore security margin that considered. aim paper provide criterion prevent on contacts configurations. To reach objective, study focuses geometrical conditions, loadings material properties linked initiation. Two dedicated test campaigns are used initiation conditions with various contact shapes same material. compared mechanics representation based asymptotic methods. method allows field evaluation at hot spot location using problem’s eigenvalues. combination Goodman approach represent key parameters They include impacted volume, shear intensity bulk stress. A proposed. It classical ratio Rσ0 only applicable all sorts shapes. interests absence size effect for its efficiency, as it analytical formulations.