Abstract: The invention relates to an assistance device for remote diagnostics during verification of the state of an aircraft engine, carried out in situ by at least one operator with an endoscope used to capture images of the engine and to take measurements intended to be transmitted to at least one remote terminal used by at least one remote expert, with the aim of performing a collaborative analysis of the images and the measurements. The device according to the invention further comprises a portable housing controlled by the operator and equipped with a software module intended for generating an operational context as a function of location data provided by a GPS, weather data from the endoscopy location, and data on the communications network.

Abstract: A turbomachine or a turbojet engine or a turboprop engine of an aircraft, including at least one oil circuit and a cooling mechanism including a refrigerant circuit including a first heat exchanger configured to exchange heat between the refrigerant and air and forming a condenser, a second heat exchanger configured to exchange heat between the refrigerant and the oil of the oil circuit and forming an evaporator, an expander mounted downstream from the first exchanger and upstream from the second exchanger, in a direction in which the refrigerant circulates, and a compressor mounted downstream from the second exchanger and upstream from the first exchanger.

Abstract: An aviation turbine blade extending in the radial direction and presenting a pressure side and a suction side, including a plurality of pressure side cavities extending radially at the pressure side of the blade, a plurality of suction side cavities extending radially at the suction side of the blade, and at least one central cavity located in the central portion of the blade and surrounded by pressure side cavities and by suction side cavities, the blade further including a plurality of cooling circuits, in which at least a first cooling circuit comprises: a first cavity and a second cavity, the first and second cavities communicating with each other at a radially inner end and at a radially outer end of the blade.

Abstract: An assembly including an accessory gearbox mechanically connected to an electricity generator having a support shaft that includes a calibrated breakable section designed to disconnect the electricity generator physically from the accessory gearbox when an incident is detected on the electricity generator, the protection device including an unlocking mechanism provided with a lock that, under the action of an external control unit, releases a cutting tool so as to cut said calibrated breakable section.

Abstract: A lubricated enclosure for an aircraft turbine engine, including a drained roller bearing provided with drainage orifices, as well as a lubricant ejector intended to limit the retention of lubricant in a critical zone of the enclosure, the ejector being intended to be passed through by a primary lubricant flow in order to drive a secondary lubricant flow located around a nozzle of the ejector housed in the critical zone of the enclosure. The enclosure includes a device for establishing communication between the drainage orifices and the ejector, such that the lubricant that escapes from the drainage orifices supplies the ejector in order to form the primary flow.

Abstract: Method for producing a thermal barrier system on a metal substrate (1) of a turbo engine part, such as a high-pressure turbine blade, the thermal barrier system comprising at least one columnar ceramic layer (31, . . . , 3i, . . . , 3n), characterised in that the method comprises a step of compressing at least one of said at least one columnar ceramic layer (31, . . . 3i, . . . , 3n).

Abstract: An electric actuator for inlet guide vanes of a gas turbine engine, the electric actuator including a fixed portion secured to a stationary portion of the engine and a movable portion that is mechanically connected to the inlet guide vanes, stationary electromagnets distributed at regular intervals around the periphery of the movable portion and fastened to the fixed portion, and movable electromagnets arranged between the stationary electromagnets, each movable electromagnet being secured on either side to first and second piezoelectric elements, the movable electromagnets and the first and second piezoelectric elements having a degree of freedom of movement relative to the movable portion and having inside faces forming a common line of contact that is tangential to the movable portion.

Abstract: A method for detecting a high temperature fluid leak in a turbomachine. The turbomachine includes a source of high temperature pressurized fluid, at least one fluid distribution line suitable for distributing said high temperature fluid, and a turbomachine compartment wherein the distribution line is at least partially housed. The method includes measuring at least two pressure parameters of the turbomachine compartment, including a measured pressure and a pressure variation over time; detecting a high temperature fluid leak when at least one of the two pressure parameters of the turbomachine compartment reaches a characteristic value of a high-temperature fluid leak in the compartment. A high-temperature fluid distribution system and a turbomachine comprising such a high temperature fluid distribution system.

Abstract: A device for cleaning, for example degritting or desanding, a turbomachine module comprising: (i) structure for isolating bearings of the module, by containment in a closed enclosure; (ii) structure for overpressurizing said enclosure; (iii) means for stripping material deposited in the walls of annular recesses of the module; and (iv) structure for sucking up the material thus stripped.

Abstract: A method of measuring the thickness of a fiber texture wound on an impregnation mandrel for fabricating an annular structural part of a turbine engine out of composite material, the method including, prior to winding the fiber texture, acquiring a reference distance between an outside surface of the impregnation mandrel and a distance sensor positioned facing the outside surface of the impregnation mandrel, while winding the fiber texture, acquiring at least one real distance between the distance sensor and the outside surface of the fiber texture wound on the impregnation mandrel, and calculating the real thickness of the fiber texture wound on the impregnation mandrel by subtracting the real distance from the reference distance.

Abstract: The present invention relates to a turbomachine component (1) or collection of components comprising at least a first and a second blade (3I, 3E) and a platform (2) from which the blades (3I, 3E) extend, characterized in that the platform (2) has a non-axisymmetric surface (S) bounded by a first and a second end plane (PS, PR) and defined by at least two class C construction curves each one representing the value of a radius of said surface (S) as a function of a position between the pressure face of the first blade (3I) and the suction face of the second blade (3E) in a plane substantially parallel to the end planes (PS, PR), these including at least one upstream curve and one downstream curve; each construction curve being defined by at least one pressure face control end point and one suction face control end point such that: —the tangent to the downstream curve at the suction face control end point 20 is inclined by at most 5°; —any other tangent to a construction curve at a control end point is inclined

Abstract: 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.

Abstract: A turbomachine module, comprising a mobile wheel rotatably mounted inside a housing of the module and surrounded by a sectorised sealing ring (18) that comprises an annular row of sectors, each ring sector comprising at least one circumferential hook that is configured to engage with an annular hooking rail of the housing, the module further comprising a sectorised protective annular shim (50) that is interposed between the hooks of the ring sectors and the rail of the housing and that comprises an annular row of sectors of shim, characterised in that the edges (60) of the circumferential ends of the sectors of shim are not aligned with the edges (58) of the circumferential ends of the ring sectors along the longitudinal axis of the module.

Abstract: A pressure regulation servo-valve comprising a body having a utilization port, a feed port, and a return port, a spool mounted as a sliding fit in the body, the spool co-operating with the body to define a pilot chamber connected to the utilization port. The spool and the body together further define a priming chamber connected to the feed port via a second constriction and connected to the nozzle via a third constriction, and in which there exists a priming pressure acting on the spool in the first direction.

Abstract: The invention concerns a device (1) for hoop reinforcing of restrictors inside at least two hydraulic supply standby systems of a journal bearing. Said device is remarkable in that it comprises: a frame (2) for receiving said hearing, a syringe (3) for introducing said restrictors and a torque pick-off spindle (4), and in that said frame (2) comprises: a cradle (21), a guide plate (23) pierced with two guide openings (231), inclined at the same angle as those of said backup systems of the bearing, so as to be located in the extension of same when the bearing is in the frame, said guide openings (231) being shaped to receive said syringe (3) or said torque pick-off spindle (4).

Abstract: A method for tracking the navigation of a mobile carrier, in which an extended Kalman filter estimates, over successive iterations, a navigation state of the carrier. Each iteration propagates a previous navigation state of the carrier into a propagated state, updates the propagated state according to measurements acquired by at least one navigation sensor. The updating includes: calculating a linear correction term from an innovation representative of a difference between the measurements acquired by the navigation sensor and the propagated state, calculating an exponential of the linear correction in terms of a Lie group, calculating a first correction term expressed in a reference frame that is fixed relative to the carrier, calculating a second correction term expressed in an inertial reference frame in which the carrier is mobile, and adding the second correction term to the value of the variable contained in the propagated state.

Abstract: A mould for obtaining an element is provided. The mould includes an outer face and a plurality of parallel ribs and/or grooves formed on the outer face. One of the walls of the mould includes ribs and/or grooves of which at least a portion of the ribs and/or grooves can be retracted, at least temporarily, such that at least a portion of the surface of the wall is smooth.

Abstract: Adjustable-length connecting rod for an aircraft turbomachine, connecting rod having a generally elongate shape and having first and second longitudinal opposite ends for attachment to elements to be connected. The first longitudinal end is connected to a first threaded shaft screwed into a first tubular portion of an adjustment sleeve. The second longitudinal end is connected to a second threaded shaft screwed into a second tubular portion of the adjustment sleeve. The connecting rod further includes a housing in which at least a portion of the first shaft is configured to slide.

Abstract: The present invention relates to an assembly (10) comprising: an annular nozzle (4) of a turbine of a turbine engine, a structural annular element (6) of the turbine engine, the nozzle (4) and the structural annular element (6) each comprising a radial flange (16, 18), the flanges being applied axially onto one another, and at least one member (12) for axially retaining the flange (16) of the nozzle (4) with the flange (18) of the structural annular element (6), with the member being applied to one of the flanges and being able to axially retain the two flanges one on top of the other.

Abstract: The method of non-destructive inspection is carried out on an aviation part by a digital imaging system including a source of electromagnetic rays and a detector, and the method includes a prior step of estimating settings for the digital imaging system, which step includes: obtaining a digital model characterizing the digital imaging system and including models characterizing the source and the detector; obtaining a digital model characterizing the aviation part; evaluating a contrast-to-noise ratio for the digital imaging system and the aviation part for a plurality of distinct values of the settings, by making use of the digital models that have been obtained characterizing the digital imaging system and the aviation part; and determining optimum values for the settings that optimize the contrast-to-noise ratio and that are applied to the digital imaging system during a setting up step.