Snecma

Safran Aircraft Engines

Snecma Moteurs

Sciete National D'etude Et De Construction De Moteurs D'aviation 'snecma'

Valerio Gerez

Edouard Joseph Jadczak

Geoffroy Nicq

Julien Christian Pascal Griffaton

Baptiste Benoit Colotte

William Bense

Gilles Claude Gabriel Massot

David Tourin

Wouter Balk

Pierre Ferdinand

Jerome Henri Noel Lacaille

Jérôme Lacaille

Jérôme Henri Noël Lacaille

Aurelie Gouby

Julien Alexis Louis Ricordeau

Andre Leroux

Serge Blanchard

Julien Griffaton

Florian Poinsot-Berthelot

Francois Prost

Gilles Massot

Serge Christian Joel Blanchard

Gregory Guillemand

Claude Alain Mazur

Aurélie Gouby

Jerome Henri Lacaille

Baptiste Colotte

André Leroux

Grégory Guillemand

A method for monitoring an aircraft engine vane wheel (), which includes: acquiring at least one time signal relative to moments when the vane wheel blades () pass in front of a sensor (); determining a common flight phase of the aircraft; for each flight in a series of flights of the aircraft, correlating at least part of each time signal with a predetermined flight phase; and for each blade (), each flight, and each predetermined flight phase, measuring the mean position (C), the so-called 'balance position', of the top of the blade. The invention also relates to a device for implementing such a method. One advantage of the invention is providing a diagnosis of the blades using a small number of sensors and low computing power.

Method and device for monitoring an aircraft engine vane wheel via balance position measurement

A method of identifying the balancing configuration installed on a turbine engine rotor using a plurality of screws forming balance weights that are mounted on the rotor at different angular positions of the rotor is provided. Each screw possesses a predetermined weight and each screw is associated with an element for identifying its weight and for identifying its angular position on the rotor. The method includes contactless scanning of all of the screws mounted on the rotor by an identification appliance capable of recognizing the elements for identifying the weight and the angular position associated with each screw.

Method of identifying the balancing configuration installed on a turbine engine rotor

A method for the acoustic analysis of a machine (M) including the acquisition of at least one acoustic signal supplied by at least one microphone () positioned in the machine, characterized in that it comprises the following steps: separation of at least one acoustic signal into a plurality of sound sources, the signal being modelled as a mixture of components, each one corresponding to a sound source; for at least one separated sound source, determination of a characteristic acoustic signature; comparison of at least one characteristic acoustic signature with at least one reference acoustic signature recorded in a reference database ().

Method, system and computer program for the acoustic analysis of a machine

A method and a system for monitoring an ephemeral event on a vane impeller of an aircraft engine are provided. The method includes: acquiring a time signal relating to movable vanes of the vane impeller; and detecting a disturbance in the time signal with respect to a reference time signal corresponding to a same flight phase, the disturbed time signal being indicative of an ephemeral event on said vane impeller. A system is provided to carry out this method.

System for detecting an ephemeral event on a vane impeller of an aircraft engine

A monitoring method and system for a test bench for at least one engine component, including: an acquisition mechanism to acquire time signal packets corresponding to measurements of endogenic and exogenic parameters specific to the combination of the test bench and the engine component, at successive instants; and a processor to construct an endogenic indicator vector and an associated exogenic indicator factor at each instant of the successive instants, using time signal packets earlier than the instant, to identify a context class for the exogenic indicator vector, and to calculate a risk probability of the endogenic indicator vector conditioned by the identified context class for the associated exogenic indicator vector using at least one anomaly detector, to produce a diagnostic of a state of the test bench and engine component combination.

Monitoring system for an engine test bench

A method and a device for detection of initiating failures in a mechanical system. The device includes an acquisition circuit to acquire packets of endogenic and exogenic time signals corresponding to measurements of endogenic and exogenic parameters specific to the mechanical system respectively, at successive instants, and a chopping circuit to chop a passband of the endogenic signal packets into a determined set of frequency sub-bands, at each instant in the successive instants. The device further includes a calculation circuit to determine a corresponding estimating signal for each frequency sub-band at each instant in the successive instants; and a detection circuit to receive each estimating signal and the corresponding exogenic signal packets during the successive instants, and to detect any deviation in each estimating signal representing initiating failures of the machine in iso-context.

Detection device for initiating failures of a mechanical system

A method for assessing whether or not the character of a value, measured by a sensor, of a physical parameter of a device is normal. The method includes implementing steps of calculating, on the basis of a regression model associated with the plurality of pairs, an estimated value of the physical parameter; calculating a related remainder calculating, on the basis of a variance model related to the plurality of pairs, an estimated value of a variance in the physical parameter; calculating an anomaly score of the measured value on the basis of the remainder, calculating the estimated value of the variance, and calculating a mean remainder value for the plurality of pairs; comparing the anomaly score of the measured value with a standard deviation threshold; and if the anomaly score is greater than the threshold, identifying the measurement as abnormal on the interface.

Method for assessing whether or not a measured value of a physical parameter of an aircraft engine is normal

A system and method for detecting defects on an object including forming an image representing the object from signals relating to the object, constructing subdivisions of the image according to auto-adaptive resolutions, and calculating differentials between various subdivisions in order to detect an abnormal subdivision indicating incipient failure.

System for detecting defects on an object

A system for detecting deformation of a fan for an aeroengine, the fan including a rotor including plural blades made of composite material including woven fibers. At least one of the fibers in each of the blades is an optical fiber including at least one portion defining a Bragg grating. The system further includes a transceiver connected to the optical fiber and configured to send an optical signal into the optical fiber and to receive an optical signal in response from the optical fiber, and a detector module connected to the transceiver to detect deformation of the fan when the received optical signal presents correlation with a predetermined signature of a damped impact on a blade at a determined speed of rotation. This deformation may be the result of a foreign object impacting against a blade of the fan or may follow from variation in an internal defect.

Detecting and tracking damage to an aeroengine fan or an impact of a foreign object thereagainst

A method of detecting clogging of a fluid filter is disclosed. The method includes measuring, at successive sampling instants, the pressure difference &#x394;P from upstream to downstream across the filter, calculating the first time derivative {&#x394;P}' of the pressure difference &#x394;P at different instants, and then sending a clogging signal Srepresentative of the filter being clogged when the first derivative {&#x394;P}&#x2032; is equal to zero.

Detecting the clogging of a fluid filter

A method of characterizing a turbine engine, the method comprising:

Avionics method and device for monitoring a turbomachine at startup

A method of detecting clogging of a fluid filter is disclosed. The method includes measuring, at successive sampling instants, the pressure difference &#x394;P from upstream to downstream across the filter, calculating the first time derivative {&#x394;P}' of the pressure difference &#x394;P at different instants, and sending a clogging signal Srepresentative of the filter being clogged when the first derivative {&#x394;P}&#x2032; is equal to zero.

A gas turbine engine including: a casing in which is mounted at least one shaft for driving a fan solidly connected to a driving drum including blades to compress an airflow moving from upstream to downstream in the engine; and an axial retention mechanism, on standby, solidly connected to the casing and arranged to come into contact with the driving drum such as to prevent axial movement of the drum in event of breakage of the driving shaft.

Gas turbine engine comprising means for axially retaining a fan of the engine

A method of monitoring twisting vibration of a rotary shaft of a turbine engine includes obtaining a vibratory acceleration signal from a sensor located on a stationary component of the turbine engine. This vibratory signal is characterized by a carrier frequency. The method also includes evaluating a frequency spectrum of the vibratory signal and searching for a pair of spectral lines of amplitudes greater than at least a first threshold. The lines are distributed in the spectrum on either side of the carrier frequency of the vibratory signal, and spaced apart therefrom by a twisting frequency of the shaft. Where appropriate, the method includes issuing a warning message.

Method and device for monitoring torsional vibrations of a rotary shaft of a turbine engine

A method and an on-board system for detecting impact on an impeller wheel of an aircraft engine. Deflection signals representative of the deflections on the blades of the impeller wheel are acquired. Each of the deflection signals is correlated with a pulse signal typical of an impact on a sound blade at the rotation frequency of the engine, in order to identify impacts on the impeller wheel. The impact signals are extracted from among the deflection signals. The impact signals are transmitted to the ground in order that the signals are analyzed to detect defects on the blades of the impeller wheel.

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Yerres, France

Valerio Gerez