METHOD AND SYSTEM FOR MONITORING VIBRATORY PHENOMENA OCCURRING IN AN AIRCRAFT'S GAS TURBINE ENGINE IN OPERATION

摘要

The invention relates to a method and a system for monitoring vibratory phenomena occurring in an aircraft's gas turbine engine in operation. The method consists in establishing (E30) a frequency spectrum of a vibratory signal representative of the state of operation of the engine and its components, in using a plurality of vibratory signals each corresponding to a vibratory phenomenon occurring during operation of the aircraft's engines of the same type as that to be monitored and having as origin a defect or abnormal operation of a component of the engines, in identifying (E40) in the spectrum the points on curves that satisfy mathematical functions each defining a vibratory signature, for each identified curve corresponding to an engine component defect, in analyzing (E50) the amplitude associated with the points on the curve relative to predefined amplitude values corresponding to a degree of severity of the defect and, when an amplitude value is exceeded or when an abnormal operation is detected, in transmitting (E60) a message associated with the vibratory signature.