Aircraft engine structures can contain small cracks, which have developed from defects induced during material processing. Advanced structural materials such as nickel-based superalloys undergo extensive plastic deformation prior to failure, therefore, these small cracks can be subjected to localized damage with significant amount of plasticity. We have conducted a combined computational/experimental study of fatigue crack growth at room temperature and at 260 degree C. The experimental results have been correlated with three-dimensional finite element calculations. Material constitutive equations and a computational procedure to calculate energy release rate along the crack front are developed. It is shown that the fatigue crack growth rate is related to a power function of Jmax.
Three-dimensional fatigue cracking under elastic-plastic deformation
International Journal of Fatigue ; 23 , SUPPL. 1 ; S65-S70
2001
6 Seiten, 10 Quellen
Aufsatz (Zeitschrift)
Englisch
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