Patent ID: 8560272

Claim:
A method of monitoring a turbojet, the method comprising: acquiring a signal representative of a vibratory level of a rotor during operation of the turbojet from a vibration sensor which is connected to an engine monitoring unit; acquiring a speed of rotation of the rotor in operation from a tachometer probe mounted on the rotor and connected to the engine monitoring unit; comparing, using the engine monitoring unit, an amplitude of the vibratory level signal acquired from the vibration sensor with at least one vibratory threshold that is predetermined as a function of the speed of rotation of the rotor; and in event of the threshold being crossed by an amplitude peak, analyzing, using the engine monitoring unit, the vibratory level signal acquired from the vibration sensor over a defined time window on either side of the amplitude peak to determine whether a phenomenon giving rise to the amplitude peak is a mechanical impact against the turbojet rotor or an electronic disturbance of the vibratory level signal acquired from the vibration sensor by analyzing symmetry of the vibratory level signal or by determining whether the vibratory level signal presents damping following the amplitude peak, wherein the phenomenon is the mechanical impact if at least one of the amplitude peak being substantially symmetrical or the vibratory level signal presenting damping following the amplitude peak is satisfied, and wherein the phenomenon is the electronic disturbance if at least one of the amplitude peak being not symmetrical or the vibratory level signal does not present damping following the amplitude peak is satisfied.