Residual life prediction of aero engine turbine disks based on calculation of low cycle fatigue crack stable growth

Аuthors

Tumanov N. V., Lavrentyeva M. A., Cherkasova S. A.

Central Institute of Aviation Motors named after P.I. Baranov, CIAM, 2, Aviamotornaya str., Moscow, 111116, Russia

Abstract

Technique for predicting residual life of aero engine turbine disks and determination of non-destructive inspection intervals has been developed which is based on the theory of low cycle fatigue crack stable growth. Results of verification and application of the technique are presented.

Keywords:

low cycle fatigue, fatigue crack kinetic, electron fractography, finite element crack modeling, fatigue striations.