Snecma

Safran Aircraft Engines

Hutchinson

Geoffroy Nicq

Valerio Gerez

Jean-Pierre Ciolczyk

David Tourin

Cristina Gonzalez-Bayon

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

The present invention relates to a method for acoustically detecting at least one malfunction (DYS) of a motor, the motor generating a primary noise Po that is treated by an active noise control system emitting, at the noise reduction targets, an acoustic signal Pc produced by at least one actuator and connected by a transfer function H to a signal Y produced by said active noise control system, said malfunction (DYS) having an acoustic signature identifiable in the primary noise Po at the noise reduction targets, characterized in that it comprises the following steps: acquisition of said signal Y produced by the active control system; identification of the appearance, if any, of a malfunction by a monitoring means that uses the knowledge of Y and H and emits an alert message if warranted.

Method and device for acoustically detecting a malfunction of a motor having an active noise control

The present description relates to a remote connection system suitable for being incorporated in an aircraft (A,B,C) comprising at least one engine propeller (A,B,C) having a plurality of blades (A,B,C) suitable for rotating relative to a stationary module (A,B,C) of the aircraft about an engine axis (X). The remote connection system comprises: a light emitter device configured, when the remote connection system is incorporated in the aircraft (A,B,C), to emit a light beam that emerges to the outside of the propeller (A,B,C), from at least one emission surface (A,B,C) of said propeller (A,B,C).

Remote connection system for an aircraft

A method and a system for acquiring a vibratory signal for troubleshooting a rotary motor, including: an input receiving a temporal vibratory signal of the motor and at least one current rotational speed of at least one shaft of the motor, and a sampling mechanism sampling the temporal vibratory signal in real time with at least one sampling signal synchronised with the at least one current rotational speed thus generating a corresponding synchronous vibratory signal.

System for acquiring a vibratory signal of a rotary motor

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.

System for detecting defects on an aircraft engine impeller wheel

A method and a system for detecting an impact on an impeller wheel of an aircraft engine. A device acquires a revolutions per minute of the engine and a series of deflection signals representative of the deflections on the blades of the impeller wheel at the revolutions per minute. A device constructs signals for detecting impact on the impeller wheel by correlating each of the deflection signals with a predetermined signature of a shock on a blade at the revolutions per minute.

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Thomery, France

Geoffroy Nicq