Method for treating fatigue crack of turbojet engine of aircraft, involves measuring temperature value in zone around propagation end of fatigue crack, and stopping compression of machine element when value corresponds to reference value

摘要

The method involves compressing a machine element perpendicular to a surface on a zone around a propagation end of a fatigue crack by hammering the element on the end by using a compression device (12). A value of parameter i.e. temperature, in the zone is measured by a measurement device (14). The measured value is compared with a reference value by a comparison module (16). Compression of the element is stopped by a stop module (18) when the measured value corresponds to the reference value, where the compression, measurement and comparison steps are performed in a simultaneous manner. An independent claim is also included for a system for treating fatigue crack of a mechanical element.