Abstract: A method for monitoring an aircraft engine vane wheel (22), which includes: acquiring at least one time signal relative to moments when the vane wheel blades (23) pass in front of a sensor (21); 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 (23), each flight, and each predetermined flight phase, measuring the mean position (24C), 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.

Abstract: 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.

Abstract: A method for monitoring an aircraft engine vane wheel (22), which includes: acquiring at least one time signal relative to moments when the vane wheel blades (23) pass in front of a sensor (21); 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 (23), each flight, and each predetermined flight phase, measuring the mean position (24C), 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.

Abstract: The present description relates to a remote connection system suitable for being incorporated in an aircraft (1A, 1B, 1C) comprising at least one engine propeller (50A, 50B, 50C) having a plurality of blades (52A, 52B, 52C) suitable for rotating relative to a stationary module (10A, 10B, 10C) 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 (1A, 1B, 1C), to emit a light beam that emerges to the outside of the propeller (50A, 50B, 50C), from at least one emission surface (54A, 54B, 54C) of said propeller (50A, 50B, 50C).

Abstract: 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.

Abstract: The present description relates to a remote connection system suitable for being incorporated in an aircraft (1A, 1B, 1C) comprising at least one engine propeller (50A, 50B, 50C) having a plurality of blades (52A, 52B, 52C) suitable for rotating relative to a stationary module (10A, 10B, 10C) 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 (1A, 1B, 1C), to emit a light beam that emerges to the outside of the propeller (50A, 50B, 50C), from at least one emission surface (54A, 54B, 54C) of said propeller (50A, 50B, 50C).

Abstract: A method of balancing a turbine engine rotor, the method including mounting screws forming balance weights on the rotor in order to form a balance configuration, each screw possessing a predetermined weight and a screw head having a visual characteristic previously associated with its weight. A rotor balanced by such a method is also disclosed.

Abstract: 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, characterised 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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 analysed to detect defects on the blades of the impeller wheel.

Abstract: The invention relates to a vibration isolator comprising a canister which ends are closed by end caps and a shaft able to move inside the canister, wherein the shaft comprises a piston-like shaped part for separating the canister in two parts: the first part being defined between the piston-like shaped part of the shaft and the first end cap, and comprising at least one resilient and damping element able to be compressed by a compression movement of the shaft on a first nominal stroke; the second part being defined between the piston-like shaped part of the shaft and the second end cap, and comprising at least one resilient and damping element able to be compressed by a tension movement of the shaft on a second nominal stroke; the tangential stiffness of the vibration isolator being, on at least one part of the first nominal stroke of the shaft, at least twice as lower as its tangential stiffness on the entire second nominal stroke of the shaft.

Abstract: The invention relates to a vibration isolator comprising a canister which ends are closed by end caps and a shaft able to move inside the canister, wherein the shaft comprises a piston-like shaped part for separating the canister in two parts: the first part being defined between the piston-like shaped part of the shaft and the first end cap, and comprising at least one resilient and damping element able to be compressed by a compression movement of the shaft on a first nominal stroke; the second part being defined between the piston-like shaped part of the shaft and the second end cap, and comprising at least one resilient and damping element able to be compressed by a tension movement of the shaft on a second nominal stroke; the tangential stiffness of the vibration isolator being, on at least one part of the first nominal stroke of the shaft, at least twice as lower as its tangential stiffness on the entire second nominal stroke of the shaft.