Numerical stress and crack initiation analysis of the compressor blades after foreign object damage subjected to high-cycle fatigue

摘要: Abstract This paper presents results of the complex stress and crack initiation analysis PZL-10 W turbo-engine compressor blade subjected to high cycle fatigue (HCF). A nonlinear finite element method was utilized determine state during first mode transverse vibration. In this analysis, numerical models without defects also with V-notches were defined. The quality solution checked by convergence analysis. Obtained next used as an input data into ( e – N ) analyzes performed for load time history equivalent one different methods such as: Neuber elastic–plastic strain correction, linear damage summation Palmgreen–Miner rule utilized. As a result number cycles appearing in blades obtained. Moreover, influence vibration amplitude on analyzed. Values properties material according Baumel–Seeger Muralidharan calculated. both notch radius values UTS behavior structure considered. last part work, compared experimental HCF tests blades.