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 an impregnation mould for manufacturing a turbine engine part, made of composite material, obtained from a preform made of a weave of fibres, said mould having first and second portions provided with respective recesses that define a cavity capable of receiving the preform, in which at least one injection means of the mould allows a resin to be injected in order to impregnate said preform, wherein said at least one injection means has a plurality of tubular injection needles, which are capable of extending from at least one of the first and second recesses to penetrate at least the weave of the preform in order to allow resin to be injected.

Abstract: The invention relates to an assembly for a turbomachine with a longitudinal axis comprising a first annular wall (24), panels (38) being arranged around the longitudinal axis (A) and extending radially opposite said first annular wall (24) so as to form a flow surface for a flow of air, each panel (38) being secured to the first annular wall (24) by at least one fixing member (72) passing through an orifice in the panel (38) and secured to the first annular wall (24) by means of a sleeve and a stud forming a spacer.

Abstract: Method for using an air intake of a turbojet engine nacelle comprising at least one elastically deformable portion, at least one connecting member mounted in an annular cavity integrally with the elastically deformable portion, and at least one controllable displacement member, in which method: during a thrust phase of the turbojet engine, the controllable displacement member moves the connecting member into a first position in which the elastically deformable portion of the air intake lip has an aerodynamic profile, and during a thrust reversal phase of the turbojet engine the controllable displacement member moves the connecting member into a second position in which the elastically deformable portion of the air intake lip has an irregular profile so as to allow a release of the reverse air flow from the elastically deformable portion.

Abstract: An injection mold for the manufacture of an axisymmetric part of composite material including a mandrel supporting a fibrous preform and including an annular wall, and a plurality of counter-mold angular sectors assembled on the mandrel and intended to close the mold and to compact the fibrous preform wound on the mandrel. Each angular sector includes an annular base intended to come into contact with the fibrous preform. The annular base extends between the first and second lateral edges in a circumferential direction, the first lateral edge of the annular base of an angular sector being in contact with a second lateral edge of the annular base of an adjacent angular sector.

Abstract: A method of controlling a vehicle having wheels provided with tires resting on a surface, the method using a model of the physical behavior of each tire as a function of a sideslip angle (?ij) for each tire relative to the surface. The model is obtained by implementing an adaptive algorithm that selectively applies an affABREGEine model (Z1), a DUGOFF model (Z2), or a constant model (Z3).

Abstract: An airtight seal configured to be mounted on a first turbomachine member, such as a door of a bleed valve, and to bear against a second member of the turbomachine, such as a hub of an intermediate casing, the airtight seal including a retaining device for mounting the seal on the first member; a sealing lip ensuring airtightness through contact and intended to bear against the second member; an anti-return device for the sealing lip reinforcing the rigidity of the airtight seal at the base of the sealing lip.

Abstract: Electrical circuit for measuring a current flowing in a conductor comprising: a first pair of Rogowski-type coils connected in series, the Rogowski-type coils of the first pair being able to operate in a first frequency band; a second pair of Rogowski-type coils connected in series, the Rogowski-type coils of the second pair being able to operate in a second frequency band, the second frequency band comprising at least partly frequencies higher than the frequencies of the first frequency band; and a means for electrically shielding the first pair of coils, and wherein a core of the Rogowski-type coils of the first and second pairs has a relative permeability of less than 10 and wherein one coil of each pair comprises at least one multi-turn winding, the other coil of the pair comprising at least one multi-turn winding.

Abstract: Described are modular folding shelves configured for removably connecting with a passenger seat back to support small items. The modular folding shelves can include an attachment portion configured to removably connect with a passenger seat back, a platform portion, and a folding support element connected between the attachment portion and the platform portion. The folding support element can be configured to fold between the attachment portion and platform portion when the platform portion is stowed, and to extend when the platform portion is deployed such that the folding support element supports the platform portion and prevents it from extending beyond the deployed configuration. The platform portion is pivotally connected with the attachment portion to allow the platform portion to fold upward and rest against or proximate to the passenger seat back when the modular shelf is installed and in a stowed configuration, and to extend away from the passenger seat back in a deployed configuration.

Abstract: A method for extending a landing gear system for a vehicle is disclosed. The landing gear system includes a first landing gear assembly and a second landing gear assembly. The method includes the steps of sensing a first load on the first landing gear assembly after the first landing gear assembly has reached a wheels-on-ground state and comparing the first load to a first target value. The method further includes the step of controlling an extension speed of the first landing gear assembly according to a difference between the first load and the first target value.

Abstract: Disclosed is a rotating electrical machine with axial air gap, comprising two rotors, each provided with superconducting axial magnetic flux barrier elements around an axis of rotation and having, between them, axial magnetic flux passage areas, at least one armature, comprising windings and a superconducting field coil surrounding the elements and the armature and capable of inducing an axial magnetic field. Each armature is positioned between two of the rotors. The superconducting elements of the rotors are coaxial with one another and also the flux passage areas. A first annular cryogenic enclosure encloses the field coil and a second cryogenic enclosure encloses the two rotors and the armature or only one rotor, with a third cryogenic enclosure around the other rotor without the armature.

Abstract: A servovalve having a pilot stage includes two hydraulic elements that are movable relative to each other so as to move a power-directing member, the pilot stage including a linear actuator having a main pusher arranged to modify the relative position of the hydraulic elements. The pilot stage has a position feedback lever.

Abstract: A turbomachine blade is made of composite material formed of woven fibers and embedded in a polymerized resin. The blade includes a root connected by a stilt to a vane which comprises a pressure side and a suction side. At least one anti-wear strip of fabric is located on a surface of the root and/or the stilt. At least one anti-wear strip is secured to the root surface in a unitary manner by the resin.

Abstract: The present invention relates to a fan rotor with variable pitch blades, comprising a rotor disc, equipped at its periphery with a plurality of rotary fasteners (16), each fastener (16) comprising a cell (17) for receiving the root (150) of a blade (15).

Abstract: The method for monitoring the electrical network comprises the identification of critical element(s) of the network, for at least one source-load pair that are connected to the network; the parametric estimation of a value of the electrical characteristic of each critical element, by using a numerical model modelling an electrical behavior of the network as a function of said electrical characteristic and of electrical measurements performed by means of sensors positioned in the network, a sensor being positioned in the network for each critical element on at least one network element or on at least one network path formed by a plurality of network elements affected by a disturbance in the electrical characteristic of this critical element; the evaluation, for said at least one source-load pair and the determination of a state of the electrical network by taking into account the operational criterion.

Abstract: A turbine assembly (1) comprising: —a plurality of turbine ring sectors (20) made of ceramic-matrix composite material, —a ring support structure (3), comprising an annular shroud (6), and in addition ?a plurality of angular spacer sectors (70) together forming an annular spacer (7), said annular spacer (7) being, on the one hand, fixed to the turbine ring (2) and, on the other hand, fixed to said annular shroud (6), characterized in that said turbine assembly (1) comprises at least one air diffuser (8), which is configured to diffuse cooling air onto the radially outer face (212) of at least one of said turbine ring sectors (20), and in that said at least one air diffuser (8) is mounted by being nested on one of said angular spacer sectors (70), in a nested position.

Abstract: A propulsion system for an aircraft includes a rotor and a nacelle fairing that extends around the rotor in relation to an axis. The nacelle fairing includes an upstream portion forming an inlet section of the nacelle fairing as well as a downstream portion, a downstream end of which forms an outlet section of the nacelle fairing. The downstream portion includes radially inner and outer walls, both of which are made of a deformable shape memory material. The wall has independently actuatable piston actuator mechanisms, each actuator mechanism being actuatable independently of the others and being designed to cooperate with means built into an inner surface of the wall to deform the wall in a radial direction in relation to the axis under the effect of a predetermined displacement command.

Abstract: Aircraft turbomachine comprising a casing, a fan, a compressor and a turbine and an epicyclic gear train comprising an input driven in rotation by the turbine, a first output stage configured to drive in rotation the compressor and a second output stage coupled to the first output stage and configured to drive in rotation the fan, the compressor being driven in rotation by the ring gear of the first output stage.

Abstract: A method of unclogging ducts in a part made by additive manufacturing, the ducts running from at least one well that opens out into the surface of the part, the method comprising the steps of: fabricating a guide with a body that is designed to fit in the well, the guide having internal channels that extend from a base of the guide that is accessible by a user to an outside wall of the body; cleaning the well and inserting the body of the guide in the well so that channels in the guide open out in register with inlets of ducts that are to be unclogged; and inserting a thin flexible tool, e.g. a metal cable, through the base of the guide into at least one channel therein and causing the tool to penetrate into the duct in register in the part so as to unclog it.

Abstract: A turbine stator blade made of ceramic matrix composite material includes a hollow blade profile and has a trailing edge and a leading edge, the blade including a first portion including an extrados face and a second portion distinct from the first portion including an intrados face, the first and second portions being connected to one another by a connection interface present at least on the trailing edge or leading edge, the connecting interface including a region of overlap between the first and second portions present on at least one longitudinal end of the blade profile and intended to be present outside a flow path of a gas stream of the turbine, the blade also including a platform present at a longitudinal end of the blade profile and that includes a first portion integral with the extrados face and a second part integral with the intrados face.