Abstract: A blade for a turbomachine fan, the blade being made from a composite material containing a plurality of longitudinal conductive fibres embedded in an electrically non-conductive matrix, the blade having at least one fastening region to which an identification medium for identifying the blade is fastened, the fastening region containing longitudinal fibres oriented along a preferred fibre axis, the identification medium contains an item of identification data for identifying the blade and at least one radio antenna having at least one communication lobe configured so as to receive a read request and transmit the item of identification data in return, the communication lobe being oriented along a radio axis that is angularly offset from the preferred fibre axis by less than 45°, preferably by less than 22.5°.

Abstract: Blower vane for an aircraft turbine engine, the vane comprising a blade connected to a root, the vane being made of a woven fibre-based composite material embedded in a polymeric resin, the vane further comprising a medium for identifying the vane, which is a radio-identification medium, the blower vane being characterised in that it comprises at least a first portion the fibres of which are only electrically conductive fibres, and at least a second portion the fibres of which are formed by a mixture of electrically conductive fibres and non-electrically conductive fibres, and in that the identification medium is located in or on the second portion.

Abstract: A part made of composite material, in particular for an aircraft turbine engine, includes a body produced from fibers woven in three dimensions and immersed in a resin, in particular an organic or polymer resin. The part has at least one crack sensor capable of detecting a crack in the part, at least one link element connected to the sensor and configured to transmit a signal (S), in particular to a member outside of the part, when a crack in the part is detected. The crack sensor has at least one conductive wire woven with the fibers of the body, and the link element is configured to measure the resistance of the conductive wire and to wirelessly transmit the signal.

Abstract: A method for monitoring the torsion of a rotary shaft on an aircraft turbomachine based on the measurements from at least three sensors distributed along the rotary shaft to divide the shaft into at least two shaft segments, the method comprising: a step of measuring, for each sensor, a parameter dependent on the rotation of the shaft, a step of calculating, for each achievable pair of sensors, a parameter related to the torsion of the shaft, a step of comparing the different calculated parameters related to the torsion of the shaft with references, a step of detecting damage on a shaft segment at the end of the comparison step, and a step of indicating the localization of the damage on the shaft from the shaft segment for which damage has been detected.

Abstract: A method for monitoring the torsion of a rotary shaft on an aircraft turbomachine based on the measurements from at least three sensors distributed along the rotary shaft to divide the shaft into at least two shaft segments, the method comprising: a step of measuring, for each sensor, a parameter dependent on the rotation of the shaft, a step of calculating, for each achievable pair of sensors, a parameter related to the torsion of the shaft, a step of comparing the different calculated parameters related to the torsion of the shaft with references, a step of detecting damage on a shaft segment at the end of the comparison step, and a step of indicating the localization of the damage on the shaft from the shaft segment for which damage has been detected.

Abstract: The invention relates to a device for connecting parts of an aircraft engine. The connection device comprises connectors suitable for connecting a first and a second part so as to establish a physical transfer link between these parts and means which enable it to monitor the state of the connection in particular by means of an impedance measurement carried out in a circuit formed by components integrated into said connectors.

Abstract: A blade for a turbomachine fan, the blade being made from a composite material containing a plurality of longitudinal conductive fibres embedded in an electrically non-conductive matrix, the blade having at least one fastening region to which an identification medium for identifying the blade is fastened, the fastening region containing longitudinal fibres oriented along a preferred fibre axis, the identification medium contains an item of identification data for identifying the blade and at least one radio antenna having at least one communication lobe configured so as to receive a read request and transmit the item of identification data in return, the communication lobe being oriented along a radio axis that is angularly offset from the preferred fibre axis by less than 45°, preferably by less than 22.5°.

Abstract: A system and a method for inspecting components of a turbojet engine using RFID tags and an associated interrogator device. The inspection system includes at least one RFID tag associated with a component of the turbojet engine and an interrogator device arranged so as to be able to communicate with the RFID tag, the interrogator device being equipped with an RFID antenna arranged so as to be able to be inserted into a nacelle compartment of the turbojet engine through an inspection opening intended for the passage of an endoscope probe.

Abstract: A method of detecting the angular positions of blades of a rotor wheel of a turbine engine, in which the turbine engine has first and second rotor wheels including respective first and second numbers of blades regularly distributed around their circumferences, includes: detecting the passage of each blade of the first wheel past a first sensor; detecting the passage of each blade of the second wheel past a second sensor; calculating the time intervals between the passage of a blade of the first wheel and the passages of each of the blades of the second wheel; and determining the relative angular position of each blade of the first wheel relative to the angular positions of the blades of the second wheel, the first number and the second number being distinct and mutually prime.

Abstract: A system for aircraft maintenance is disclosed, such as for monitoring parts mounted in a turbojet engine, the turbojet engine being accommodated in a nacelle compartment delimited by a nacelle wall. The system can verify parts, each of the parts being equipped with an RFID tag. The verification system includes an inner antenna accommodated in the nacelle compartment, the inner antenna being arranged to allow the exchange of radio frequency signals with each RFID tag, an interface device including an access point located outside the nacelle compartment, the interface device being arranged to be able to be connected to an interrogator device arranged to communicate with the RFID tag, and a transmission line connecting the interface device to the inner antenna.

Abstract: A system and a method for inspecting components of a turbojet engine using RFID tags and an associated interrogator device. The inspection system includes at least one RFID tag associated with a component of the turbojet engine and an interrogator device arranged so as to be able to communicate with the RFID tag, the interrogator device being equipped with an RFID antenna arranged so as to be able to be inserted into a nacelle compartment of the turbojet engine through an inspection opening intended for the passage of an endoscope probe.

Abstract: A method of detecting the angular positions of blades of a rotor wheel of a turbine engine, the turbine engine having at least two rotor wheels driven by a common shaft, the first and second wheels comprising respective first and second numbers of blades regularly distributed around their circumferences. The method comprises detecting (200) the passage of each blade of the first wheel past a first sensor, detecting (210) the passage of each blade of the second wheel past a second sensor, calculating the time intervals between the passage of a blade of the first wheel and the passages of each of the blades of the second wheel, and determining (230) the relative angular position of each blade of the first wheel relative to the angular positions of the blades of the second wheel, the first number and the second number being distinct and mutually prime.