Safran

Safran Aircraft Engines

Institut National De Recherche En Informatique Et En Automatique

Institut National Des Sciences Appliquees Lyon

Dany Abboud

Nicolas Paul Tableau

Julien Christian Pascal Griffaton

Mohammed El Badaoui

Mohamed El Badaoui

Yosra Marnissi

Axel Barrau

Christian Courrech-Nielsen

José-Luis Gomez Chirinos

Maxime Leiber

Yasmine Hawwari

A method for monitoring a rotating machine in order to detect a fault in a bearing, the method including acquiring, from the rotating machine, a vibration signal measured by a vibration sensor; determining a first-order spectrogram by first-order cyclostationary analysis of the vibration signal using a delta transform and spectral standardisation; determining a second-order spectrogram by second-order cyclostationary analysis of the vibration signal using averaged cyclic coherence, a delta transform and spectral standardisation; and detecting a vibration signature of the fault in the bearing on the basis of the first-order spectrogram and the second-order spectrogram.

Method for monitoring a rotating machine in order to detect a fault in an aircraft bearing

Method for monitoring a turbomachine comprising a stator and a rotor, device, system, aircraft and computer program product. The method comprises a step of acquiring an input signal which represents a deformation of the stator or rotor of the turbomachine. The input signal has been acquired by a deformation gauge which is attached to the stator or rotor. The input signal comprises a first component which represents deformations of the stator or rotor which are caused by rotation of the rotor vanes in relation to the stator, and a second component which represents deformations which are caused by different elements of the rotor vanes. The method comprises a step of re-sampling the input signal in order to obtain a re-sampled input signal comprising a predefined whole number of samples per revolution of the turbomachine rotor. The method also comprises a step of processing the re-sampled input signal, comprising: filtering the re-sampled input signal, making it possible to acquire a filtered input signal in which the second component is attenuated, and separating the filtered input signal into a plurality of third components, each third component representing a contribution to the deformation caused by a respective associated vane. The method also comprises a step of detecting, in a third component, contact between the vane associated with the third component and the stator.

Method for monitoring a turbomachine, device, system, aircraft and computer program product

The invention concerns a method for monitoring a gear system () comprising at least two wheels, each wheel having a characteristic frequency (f, f), a vibratory or acoustic signal representative of these vibrations having been acquired by a sensor (), a vibratory or acoustic digital signal x(t) having been obtained, the method comprising, for each characteristic frequency of the system (), the steps of filtering (E) the digital signal by means of a filter in such a way as to obtain an image monitoring signal of at least one vibratory component of at least one defect; determining (E) the square envelope of said monitoring signal, defined by the square absolute value of the Hilbert transform of the monitoring signal so as to extract an image of the modulating signals associated with the rotation of the wheels from the monitoring signal; determining (E) the synchronous average of said square envelope relative to the period of rotation of a wheel of interest chosen from the wheels of the gear, said average helping attenuate spurious components in the envelope originating from other mechanical sources; determining (E) a monitoring indicator dependent on said synchronous average, said monitoring indicator being defined by the square root of the synchronous average normalised by the median value of the synchronous average.

Method and device for monitoring a gear system

The invention relates to a method () for monitoring a rotating machine () of an aircraft, wherein a measurement signal is acquired from the rotating machine. According to the invention, instantaneous frequencies (f(t)) of sinusoidal components of the measurement signal are estimated, and, using a computing module (), a plurality of successive iterations are carried out in each of which: complex envelopes of the components are updated (C), parameters of a model of a noise of the signal are updated (C) on the basis of the envelopes, whether the model has converged from the preceding iteration to the present iteration is tested (C), with a view to: o if not, carrying out a new iteration, o if so, performing a computation (D) of the complex envelopes on the basis of the iterations that have been carried out.

Method, device and computer program for monitoring a rotating machine of an aircraft

A method detects a defect in a vibration sensor including the whitening of the vibratory signal delivered by the vibration sensor, and the calculation of an indicator of asymmetry of the whitened vibratory signal. The whitening may be a cepstral whitening implemented simply by dividing the Fourier transform of the signal by its modulus. The asymmetry indicator is a counter of aberrant points in the whitened vibratory signal.

Method for detecting a defect in a vibration sensor, associated device and computer program

A method includes obtaining a vibration signal acquired by an accelerometer sensor; eliminating a deterministic component of the vibration signal; obtaining, for a determined defect, a characteristic theoretical frequency of this defect and a determined maximum deviation around this theoretical frequency; computing, as a function of a cyclic frequency, an integrated cyclic coherence of the processed vibration signal; estimating an actual frequency of the defect on the basis of the integrated cyclic coherence, of the theoretical frequency of the defect and of the maximum deviation; computing a diagnostic indicator of the defect by summing M integrated cyclic coherences of the vibration signal evaluated as M cyclic frequencies respectively equal to M harmonics of the estimated actual frequency of the defect; comparing the diagnostic indicator of the defect with a predetermined threshold, and in the event of it being exceeded, detecting the defect on the bearing.

Method and device for monitoring a bearing equipping a rotary device

The invention relates to an acquisition module for a monitoring system of a rotating machine, in particular of an aircraft engine, the acquisition module comprising at least one measurement sensor for measuring an analogue signal x(t) of a physical quantity of a member of the rotating machine, at least one sample-and-hold device configured to collect a sample of the analogue signal x(t) at sampling times t n and to maintain it constant between two sampling times t n, and at least one memory for storing samples, the sample-and-hold device being configured to collect a sample of the analogue signal x(t) at sampling times t n defined in a random manner, the sampling times t n being defined according to the following law t n=n&#x394; t+&#x3c4; n, the samples and the sampling times t n being stored in the memory.

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Moissy-Cramayel, France

Dany Abboud