Abstract
The in-service fatigue fracture of the fan disk from the titanium alloy was considered and analyzed. Fatigue crack started from the cut which was produced during disk manufacturing and located along the slot for the blade. The crack path was performed by the mechanism of crack meso-tunneling with the facetted pattern relief and striation formation on the fracture surface. Based on the fractographic analysis, equivalent stress for various values of crack length was estimated. The inspection interval for reliable crack registration in the disk was provided. It was demonstrated that without cuts the disk in-service period will be not less than 15,000 flights.
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