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Communication Dans Un Congrès Année : 2015

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.
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Dates et versions

hal-04088134 , version 1 (03-05-2023)

Identifiants

  • HAL Id : hal-04088134 , version 1

Citer

Farida Azzouz, A. Gaubert, P. Kanouté, C. Moriconi. Cyclic inelastic constitutive equations of the hot turboengine components. 4th International Conference on Materials Modeling (ICMM4), May 2015, Berkeley, United States. ⟨hal-04088134⟩
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