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: An onboard system and a method for draining an aeroengine. The onboard system comprises a buffer tank having an admission passage for admitting under gravity fluid coming from the aeroengine, a primary tank situated above the buffer tank and having an emptying passage for emptying the fluid coming from the aeroengine, and a lift circuit connecting the buffer tank to the primary tank in order to transfer the fluid coming from the aeroengine from the buffer tank to the primary tank.

Abstract: Analysis device for detecting solid particles in suspension in a lubricant, the analysis device comprising one or more ferromagnetic solid particle sensors, one or more other sensors able to detect non-ferromagnetic solid particles, and one or more magnets. The ferromagnetic solid particle sensors are offset in a direction perpendicular to a main direction of flow of the lubricant in relation to the other sensors, and the magnets are arranged so as to attract ferromagnetic solid particles towards the sensors of ferromagnetic solid particles by drawing them away from the other sensors.

Abstract: The invention relates to the field of aeronautical propulsion, and more particularly an on-board drainage reservoir of an aircraft engine, the on-board reservoir including a first compartment with a first intake passage for receiving fluid drained from the engine, a first closeable emptying passage, and a first quality sensor assembly for detecting at least one quality parameter of the fluid drained from the engine.

Abstract: The invention relates to a glass-fiber textile structure, characterized in that it has a parylene (poly(para-xylylene)) coating with a thickness of between 5 ?m and 30 ?m, preferably between 6 ?m and 25 ?m, in particular between 7 and 20 ?m. The invention also relates to a method for reinforcing a solid material, which comprises introducing such a textile structure having a parylene coating into a fluid base material, preferably a base material comprising water and a hydraulic binder, and curing the base material.

Abstract: A modular and autonomous assembly for detecting the angular position of the blades of an impeller intended to be mounted on a turbine engine, the assembly comprises at least one electrical power source allowing the operation of the elements of the detection assembly independently of the turbine engine on which it is intended to be carried, at least one first sensor intended to be associated with the first impeller, at least one second sensor intended to be associated with the second impeller, and a main housing including a processing unit and storage means.

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 disclosure relates to a device and a method for managing a fleet of information communication devices with reversible attachment on aircraft turbomachines, having: an association of a device among the fleet of devices with a turbomachine among a fleet of turbomachines, an attachment, an acquisition of at least one turbomachine operating parameter, a development of at least one indicator that allows the update of a digital twin of the turbomachine based on the operating parameter acquired, a communication of the indicator that allows the update of the digital twin to a digital twin storage entity.

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 process for the manufacture of a colored laminated glazing including at least two glass sheets connected together by a thermoplastic interlayer, includes deposition, by the liquid route, on a first glass sheet, of a polymeric layer including a coloring agent and polymeric compounds, drying and optionally curing of the polymeric layer, assembling of the glass sheet, coated with the colored polymeric layer, with a colorless transparent thermoplastic interlayer and with the second glass sheet, so that the colored polymeric layer is in direct contact with the interlayer, degassing, during which the air trapped between the glass sheets and the thermoplastic interlayer is removed, and heat treatment under pressure and/or under vacuum of the laminated glass at a temperature of between 60 and 200° C., during which the coloring agent present in the polymeric layer migrates toward the thermoplastic interlayer and during which the laminated glazing is assembled.

Abstract: A method for monitoring a status of a reduction gear of a gas turbine includes the steps of: obtaining measurements of parameters accomplished during an operating phase of the gas turbine, these parameters including temperatures of a lubricating oil of the reduction gear at the inlet and at the outlet of the reduction gear, a parameter representing a speed of the gas turbine, as well as at least one context parameter; selecting measurements; normalizing temperatures of the lubricating oil using the measurements of the context parameter; evaluating a thermal efficiency of the reduction gear by using a physical model defining the thermal efficiency based on a difference between the temperature of the lubricating oil; and determining a status of the reduction gear depending on a step of comparing the evaluated thermal efficiency with respect to a reference signature.

Abstract: A method for detecting damage to one or more mobile blades of an impeller of an aircraft engine, includes measuring the speed of the engine, and for each blade acquiring, by a plurality of sensors, measurements of blade-tip passage times; calculating for each sensor, a deflection of the blade tip; extracting a dynamic component of deflection for each of the calculated deflections; detecting the number of functioning sensors; selecting the dynamic components to be processed based on the detecting step; determining, for at least one blade, a variation of the dynamic behavior of the blade for each functioning sensor; and, for each blade for which a variation of the dynamic behavior has been determined, identification of potential damage to the blade.

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: The invention relates to the field of aeronautical propulsion, and more specifically to an emptying and monitoring device and method for emptying and monitoring a fluid drained from an aircraft engine. The emptying and monitoring device comprises at least one first intake passage for receiving, directly from the aircraft, fluid drained from the engine, and a first quality sensor assembly for detecting at least one quality parameter of the fluid drained from the engine, having been admitted through the first intake passage.

Abstract: The invention relates to the field of aeronautical propulsion, and more particularly an on-board drainage reservoir of an aircraft engine, the on-board reservoir including a first compartment with a first intake passage for receiving fluid drained from the engine, a first closeable emptying passage, and a first quality sensor assembly for detecting at least one quality parameter of the fluid drained from the engine.

Abstract: A method for detecting damage to one or more mobile blades of an impeller of an aircraft engine, includes measuring the speed of the engine, and for each blade acquiring, by a plurality of sensors, measurements of blade-tip passage times; calculating for each sensor, a deflection of the blade tip; extracting a dynamic component of deflection for each of the calculated deflections; detecting the number of functioning sensors; selecting the dynamic components to be processed based on the detecting step; determining, for at least one blade, a variation of the dynamic behavior of the blade for each functioning sensor; and, for each blade for which a variation of the dynamic behavior has been determined, identification of potential damage to the blade.

Abstract: A process for the manufacture of a colored laminated glazing including at least two glass sheets connected together by a thermoplastic interlayer, includes deposition, by the liquid route, on a first glass sheet, of a polymeric layer including a coloring agent and polymeric compounds, drying and optionally curing of the polymeric layer, assembling of the glass sheet, coated with the colored polymeric layer, with a colorless transparent thermoplastic interlayer and with the second glass sheet, so that the colored polymeric layer is in direct contact with the interlayer, degassing, during which the air trapped between the glass sheets and the thermoplastic interlayer is removed, and heat treatment under pressure and/or under vacuum of the laminated glass at a temperature of between 60 and 200° C., during which the coloring agent present in the polymeric layer migrates toward the thermoplastic interlayer and during which the laminated glazing is assembled.

Abstract: A temperable tinted glass substrate has at least one of its faces that is partially coated with a layer of mineral paint obtained from an aqueous paint composition based on an alkali metal silicate solution including the mixing of a platy mineral filler with at least one other filler chosen from alumina, boron or germanium, and at least one black mineral pigment.

Abstract: An onboard system and a method for draining an aeroengine. The onboard system comprises a buffer tank having an admission passage for admitting under gravity fluid coming from the aeroengine, a primary tank situated above the buffer tank and having an emptying passage for emptying the fluid coming from the aeroengine, and a lift circuit connecting the buffer tank to the primary tank in order to transfer the fluid coming from the aeroengine from the buffer tank to the primary tank.

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.