Abstract
Cold expansion process is widely used to enhance fatigue life of fastener holes in aircraft industry. The benefit derived from cold expansion treatment is attributed to residual stresses induced around hole. This work is aimed at establishing a simple procedure for predicting Fatigue Crack Growth (FCG) life around cold expanded holes. Cold expansion process is simulated for uncracked and cracked holes using Finite Element method. The effect of residual stresses is accounted to predict FCG life using Willenborg's model. As a result of cold expansion, significant retardation in FCG rate and life improvement is achieved.
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