Abstract
The in-service fatigue fracture of the fan disk made of titanium alloy is analyzed by complex metallophysical research. The crack path consists of the formation of facetted pattern relief and striations on the fracture surface. From the results of striation spacing measurements, the equivalent stress for various crack sizes is estimated. The number of damaging-loading cycles per one flight is discussed and established by the analysis of the schematized flight loading cycle of the aero-engine. The inspection interval for reliable crack detection in the disk is evaluated. It is demonstrated that, without fan disk damage, its in-service durability can exceed 15,000 flights.
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