Method and system for monitoring a turbojet engine

Details Method and system for monitoring a turbojet engine Method and system for monitoring a turbojet engine

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 21/00 (2006.01) G01H 1/00 (2006.01)

Patent

CA 2738893

The invention relates to a method and a system for monitoring a turbojet engine. The method consists of acquiring (E10) a signal representative of the vibratory level of an operating rotor of the turbojet engine, acquiring (E20) a rotation speed of the rotor during operation, comparing (E40) the amplitude of the signal with at least one predetermined threshold based on the rotor rotation speed and, in the event an amplitude peak exceeds said threshold, analysing (E50) the signal over a time slot defined around the amplitude peak in order to determine (E60) if the phenomenon at the origin of the amplitude peak is a mechanical shock undergone by the rotor of the turbojet engine or an electronic interference of the signal.

L'invention concerne un procédé et un système de surveillance d'un turboréacteur. Le procédé consiste à acquérir (E10) un signal représentatif d'un niveau vibratoire d'un rotor en fonctionnement du turboréacteur, acquérir (E20) un régime de rotation du rotor en fonctionnement, comparer (E40) l'amplitude du signal à au moins un seuil vibratoire prédéterminé en fonction du régime de rotation du rotor, et, en cas de dépassement du seuil par un pie d'amplitude, à analyser (E50) le signal sur une fenêtre temporelle définie autour du pie d'amplitude pour déterminer (E60) si le phénomène à l'origine du pic d'amplitude est un choc mécanique subi par le rotor du turboréacteur ou une perturbation électronique du signal.

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