Cyclic inelastic constitutive equations of the hot turboengine components
Résumé
The hot section of aeronautical structures are subjected to complex thermal and mechanical
loads involving fatigue, creep and also creep-fatigue interaction and crack propagation.
In order to correctly estimate the life assessment of components, a 3D cyclic inelastic analysis is
necessary. To do so, inelastic constitutive equations that are able to account all or major material
experimental observations at different temperatures are used.
In this contribution elasto-viscoplastic constitutive equations used in cyclic inelastic analysis
are given. In particular, the recent progress of the crystal anisotropic law for the description of
single crystal superalloys (blades). Also, a new behavior model to better reflect the most frequent
experimental facts on combustion chambers materials under cyclic loading as very pronounced
hardening, dynamic strain aging, memory effect and static recovery at high temperature.