Abstract: Method for controlling a turbomachine equipped with a gas generator, the turbomachine including at least one electric machine forming a device for the injection/take-off of power onto/from one of the low-pressure/high-pressure rotating shafts of the gas generator. Said method has steps included in a loop which include determining, for at least one shaft and according to a speed setpoint, of a variation dU in a power command; determining, for all of the electric machines as a whole and according to an injection/take-off setpoint, of a variation dPelec in a power injection/take-off command; and determining a command including components pertaining to fuel flow rate and to power injection/take-off for each electric machine, according to the variations dU dPelec, and according to the operational limits of the turbomachine.

Abstract: A turbojet engine, having a primary duct and a secondary duct surrounding the primary duct, a row of guide vanes extending in the secondary duct downstream of a fan, at least one conduit extending in the secondary duct downstream of the guide vanes and housed in a profiled casing, and at least one air sampling scoop located in the region of the casing and equipped with a control valve. Where at least one guide vane located in the vicinity of the casing has a variable geometry zone, the geometry of which can be adjusted during operation.

Abstract: Movable ring assembly for a turbomachine rotor, the movable ring including an outer peripheral toothing, each tooth of the outer peripheral toothing having an inner face intended to be positioned facing a blade root of the rotor, and an outer face opposite to the inner face and intended to be positioned facing an axial retaining hook arranged on the blade root. Furthermore, the movable ring assembly includes at least one protective element arranged on the outer face of at least one tooth of the outer peripheral toothing.

Abstract: A method for producing casing for an aircraft turbine engine includes a first step of manufacturing an annular shell having an axis A made of a composite material in a mold that includes an annular cavity that receives the preform. A resin is injected into the cavity and subsequently polymerized. During a second step, at least one axial abutment means is arranged inside the shell, and during a third step, the annular cartridge made of an abradable material is arranged inside the annular shell in contact with the axial abutment means. A fourth step includes bonding the annular cartridge to the first inner annular surface. The first and second steps are simultaneous, and the at least one axial abutment means is molded with the preform in the mold.

Abstract: A double-flow turbomachine has an exhaust casing through which a hot primary flow passes and surrounded by a cold secondary flow, and a cone carried by the exhaust casing. The exhaust casing has a hollow radial arm passing through the primary flow to convey air into the cone in order to form a cooling flow for components located in the cone. The cone has an outer wall and an inner wall which runs alongside the outer wall and is radially spaced therefrom to delimit a thermal insulation space through which the cooling flow passes from upstream to downstream before it is discharged through an outlet opening at the end of the conc. It has an inner cover surrounding a component to channel the cooling flow so that it runs along the component to cool it before passing through the thermal insulation space to be discharged there.

Abstract: The invention proposes an aeronautical turbine engine assembly comprising an upstream casing (55) to which guide blading (48a) is fastened, and a downstream casing (58) to which a sealing element (62) provided with an abradable material for rotor blading is fastened. This assembly further comprises a shroud ring (66) placed between the upstream casing and the downstream casing and fastening means (68) for detachably fastening the shroud ring. In order to be fastened to the upstream casing, the guide blading (48a) of the turbine engine is mounted on a downstream hook (480b) of the upstream casing, without being hooked onto the shroud ring (66), and the downstream casing (58) has an upstream hook with which the sealing element (62) is engaged in order to be fastened to the downstream casing, or the shroud ring has an upstream hook on which the sealing element (62) is mounted so as to be fastened to the downstream casing.

Abstract: A turbomachine part of an annular assembly includes a structural body and a connecting edge integral with the structural body. Each connecting edge includes at least one groove intended to receive a sealing tab. Each connecting edge is made of composite material including a fibrous reinforcement consisting of randomly-oriented short fibres, the reinforcement being densified by a ceramic matrix.

Abstract: An electrical machine for use in an aircraft. The electrical machine includes a rotor that includes a plurality of rotor poles, and a stator including a plurality of phases. Each respective phase occupies at least one elementary block. The at least one elementary block of each phase includes a set of conductors of the respective phase wound around a plurality of slots of the respective elementary block in a concentrated winding configuration. The stator further includes at least one sensor located between two elementary block. The at least one sensor being configured to measure at least one parameter of the rotor.

Abstract: A smart motor having an electromechanical converter endowed with a rotating portion defining an axial direction and a radial direction, an electronic control unit, an electrical filter and a housing having a cooling device, the electromechanical converter, the electronic control unit and the filter being accommodated inside the housing, and the electronic control unit comprising an electrical converter configured to power the electromechanical converter. The housing is cylindrical and the electrical converter includes one or more electronic board(s) forming a hollow cylinder.

Abstract: A method for producing an aerodynamic element for an aircraft, including a wall which is covered, at least partially, by a printed film including a plurality of ribs and/or grooves, the method including: providing a raw film made of a deformable material which is devoid of grooves and ribs; providing a pressure plate which includes a face provided with ribs and/or grooves complementary to the ribs and/or grooves of the printed film; placing said raw film on the wall of the element; positioning the pressure plate on the raw film, the printed side of the pressure plate facing the raw film; and a forming step during which the raw film is bonded with the wall of the component and during which the raw film is shaped by cooperation with the pressure plate to obtain the printed film including the ribs and/or the grooves.

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: The invention provides a cover for an aircraft passenger using a bed surface of an aircraft passenger seat, comprising an attachment mechanism for attaching the cover to the seat, an inflatable bladder, and a trigger mechanism for triggering inflation of the bladder, the bladder being configured to cover a knee region of the bed surface. The invention also provides a harness for the aircraft passenger, comprising an attachment mechanism for attaching the harness to the seat, a number of straps for extending around the passenger, and a fastening mechanism for fastening one or more of the straps in place around the passenger, wherein the number of straps includes at least one of a crotch strap and a torso strap. The invention also provides an aircraft passenger seat unit comprising a seat convertible to a bed, the bed being provided with a cover or harness.

Abstract: Process for protecting a part comprising an aluminum-based alloy having a copper content greater than or equal to 0.5% by mass, the process comprising depositing a non-conductive protective layer over the entire part, laser pickling by means of a laser beam of an area of the non-conductive protective layer so as to form an unprotected area, chemical conversion, with trivalent chromium, of the unprotected area so as to form a conductive protective layer, and drying of the part.

Abstract: A module including a device for changing the pitch of the vanes about the pitch axes thereof, the device including a hydraulic actuator capable of rotating about the longitudinal axis and configured to rotate the vanes about their pitch axes, a pump for supplying fluid to the hydraulic actuator, including a transmission shaft and a placed around the transmission shaft and rotating as one with the drive shaft, and an electric machine including a rotor rotating as one with the transmission shaft and a stator rotationally fixed relative to the longitudinal axis. The stator can be connected to a power supply cable passing through a passage provided in the third element of the speed reducing gear.

Abstract: The present invention relates to an assembly (12) for a turbomachine, comprising: —an outer casing (15) made of half-shells; —an inner casing (14); —a plurality of guide vanes (13) mounted between the outer casing (15) and the inner casing (14), —a structural casing comprising a flange (23) which is radially inside the inner casing (14); and—a system (24) for blocking the inner casing (14) on the structural casing, comprising a generally annular tab (25) fixed to one of the inner casing (14) and the structural casing and a complementary chute (26) fixed to the other of the inner casing (14) and the structural casing, the chute (26) being configured to receive the tab (25) and to block it along the axis (X) with respect to the structural casing.

Abstract: System for controlling a device provided with at least one equipment item, the control system comprising at least one sensor capable of measuring operating quantities of the device, and two specific channels for measuring a redundant sensor for each equipment item, at least one embedded control means configured to determine a command intended for at least one equipment item as a function of the at least one measurement of the operating quantity of the device and a selected measurement of the controlled equipment item, the control system further comprising a calculating means configured to determine the selected measurement of the at least one controlled equipment item, by means of a Kalman filter observer, as a function of the at least one measurement of the operating quantity of the device and the measurements of the two specific channels for measuring a redundant sensor for the controlled equipment item.

Abstract: A contactor including a first electrical contact, a second electrical contact, and a movable bridge displaceable between a closed position and an open position, the contactor further including: a lower arc guide including a first portion connected to the first electrical contact, and a second portion connected to the second electrical contact, an upper arc guide including a first portion facing the first portion of the lower arc guide, a second portion facing the second portion of the lower arc guide, and a fuse connecting the first portion and the second portion of the upper arc guide.

Abstract: A defrosting and acoustic treatment device for an air intake lip of a turbojet engine nacelle includes an embossed acoustic structure that delimits a plurality of acoustic cells, each acoustic cell being delimited by an independent peripheral wall that allows a flow of de-icing air to flow around each acoustic cell.

Abstract: Discharge valve of an aircraft turbomachine, including a discharge gate intended to be mounted pivotably about an axis between a position for closing an air passage orifice and an open position of said orifice, the orifice being formed in an intermediate casing of the turbomachine, the discharge valve including a sealing device having a seal configured to be movably mounted on the intermediate casing and a movement system configured to move the seal between a first position in which the seal is intended to bear against the discharge gate when the gate is in a closure position, and a second position in which the seal is retracted with respect to the air passage orifice when the discharge gate is in an open position.

Abstract: A method of harmonizing a first inertial measurement unit and a second inertial measurement unit with each other includes the steps of: causing a control unit to compare the vectors measured by the inertial measurement units in order to determine a specific force difference and a rotation difference while taking account of the lever arms between the two measurement units; and causing the control unit to determine a harmonization value from the specific force difference and the rotation difference while taking account of the lever arms between the two measurement units. Navigation apparatus performs the method.