Patent ID: 8831860
Filing Date: 2014-09-09
Classification: F02C,F05D,G01H,G01M

Abstract:
1. A method of monitoring vibratory phenomena that occur in an aircraft gas turbine engine in operation, the method comprising: a) during a predefined period of operation of the engine, acquiring a vibratory signal representative of an operating state of the engine and of components of the engine; b) over the predefined period, establishing a frequency spectrum of the vibratory signal; c) providing a database including a plurality of preprogrammed vibratory signatures, each vibratory signal corresponding to a vibratory phenomenon occurring during the operation of aircraft engines of a same type as the engine being monitored and originating from a defect in or abnormal operation of at least one of the components of the engines, each vibratory signature being defined by a mathematical function of operating parameters of the engine, and coefficients of each mathematical function corresponding to one of the plurality of vibratory signatures being predetermined and preprogrammed in the database based on at least one of a theoretical calculation for or previous data acquired from an engine of the same type as the engine being monitored; d) calculating, using a processor, curves corresponding to mathematical functions in the database that defines the plurality of preprogrammed vibratory signatures, and, in the frequency spectrum, identifying, using the processor, a set of points of the frequency spectrum that fits one of the calculated curves corresponding to one of the plurality of preprogrammed vibratory signatures, in order to detect at least one of a presence of a defect in or abnormal operation of the least one component of the engine; e) for each curve identified using the processor that fits the set of points in the frequency spectrum corresponding to a preprogrammed vibratory signature in the database originating from a defect in the at least one component of the engine, analyzing, using the processor, an amplitude of the points of the curve relative to predefined amplitude values, each predefined amplitude value corresponding to a degree of severity of the defect in the at least one component of the engine associated with the vibratory signature; and f) as a result of at least one amplitude value being exceeded or of abnormal operation of the at least one component of the engine being detected, issuing a message associated with the vibratory signature for which the at least one amplitude value has been exceeded or for which the abnormal operation has been detected.