METHOD AND SYSTEM FOR CONTROL OF VIBRATION PHENOMENONS APPEARING IN A GAS-TURBINE ENGINE OF THE AIRCRAFT DURING OPERATION

摘要

1. A method for controlling vibration phenomena that occur in a gas turbine engine of an aircraft during operation, characterized in that a) during a predetermined period of engine operation, an (E10) vibration signal characteristic of the state of operation of the engine and its components is received; b) set (E30) the frequency spectrum of the vibrational signal over a predetermined period; c) a plurality of vibrational signatures are used, each of which corresponds to a vibrational phenomenon that occurs during operation of aircraft engines of the same type as the controlled one, and the cause of which is a defect or abnormal operation of at least one of the engine components, each vibration signature being determined using a separate mathematical function, the coefficients of which are predetermined depending on the engine operation parameters; d) in the frequency spectrum identifies (E40) the points of the curves that correspond to the mathematical functions, each of which determines the vibration signature in order to detect the presence of defects or abnormal operation of the component nt of the motor; e) for each curve identified in the frequency spectrum and the corresponding vibration signature caused by a defect in the engine components, analyze (E50) the amplitude associated with the points of the curve with respect to the predetermined amplitude values, each of which corresponds to the severity of the defect ; and f) when one or more amplitude values is exceeded or if abnormal operation of the engine component is detected, a message (E60) corresponding to the vibration signature is transmitted, in which