Abstract: A method for impregnating a fibrous preform by injection or infusion, the method including the steps of providing a mold having at least two portions, said mold presenting an inlet orifice and a vent orifice placed on opposite sides of the mold; placing a fibrous preform in a portion of the mold; placing a seal in a passage formed between an inside wall of the mold and the fibrous preform, said passage extending substantially along the direction extending between the opposite sides of the mold; closing the mold so that the two portions of the mold co-operate with the seal in such a manner as to shut off said passage; and impregnating the fibrous preform with an impregnation material.

Abstract: A turbomachine assembly and, in particular, a low-pressure compressor of an aircraft turbojet engine includes an annular row of upstream vanes with trailing edges extending radially from an upstream support; an annular row of downstream vanes with leading edges axially facing the trailing edges and extending radially from a downstream support; an annular passageway delimited by the upstream support and the downstream support. The downstream support has a profile with: an upstream portion delimiting the annular passageway forming an annular slide, a downstream portion axially at the level of downstream vanes, and a connecting arc connecting the upstream portion to the downstream portion. The connecting arc is arranged downstream of the leading edges.

Abstract: A reduction gear including an input shaft including an input gear, an output shaft including an output gear, and two intermediate transmission lines, each intermediate transmission line including an intermediate shaft including a first stage of teeth and a second stage of teeth, the stages rotating as one, and an additional gear for meshing respectively with the first stage of teeth and the input gear, or with the second stage of teeth and the output gear, and the reduction gear wherein the input gear or the output gear meshing with the additional gears is axially offset with respect to the stage of teeth of the intermediate shafts meshing with the additional gears.

Abstract: In a cowl for a nozzle, an internal wall has a cross-section with a determined abscissa on the axis defining a neck line on the internal wall. The cowl has, downstream of the determined abscissa, indentations in the trailing edge which delimit chevrons distributed in the circumferential direction. The internal wall of the cowl diverges radially towards the interior, in a second axial half-plane passing through the tip of a chevron, from the upstream tangent on the point of the neck line in the second axial half-plane, and the lines defining the internal wall of the cowl in any axial half-plane do not have a turning point downstream of the determined abscissa of the neck line.

Abstract: A device for regulating flow rate of a gas in a duct, the device including a valve member having an actuator, the valve member being configured in such a manner as to shut off the duct selectively, wherein movement of the valve member is controlled by the resultant firstly of pressure in the duct upstream from the valve member acting on a proximal surface of the valve member, and secondly of a control pressure applied to a distal surface of the valve member of area greater than that of the proximal surface of the valve member, the control pressure being established in an amplification chamber having a feed line and an emptying line, one of the feed and emptying lines presenting a flow rate that is constant and the other presenting a flow rate that is variable and that is controlled by an actuator.

Abstract: A method of controlling an aircraft electrical taxiing system, the method comprising the steps of: defining a target value (Ld_nmax) for an electrical parameter; generating a nominal force command (Cmd_nom) for the electrical taxiing system; in parallel with generating the nominal force command (Cmd_nom), using a processing system (2) to produce a maximum command force (Force_max) for the electrical taxiing system so that a real value of the electrical parameter reaches the target value (Ld_nmax), the processing system (2) comprising a regulator loop (4); and generating an optimized force command (Cmd_opt) for the electrical taxiing system equal to the smaller of the nominal force command and the maximum command force.

Abstract: A method of fabricating at least one metal part for a turbine engine, the method including the steps of casting a metal alloy by centrifuging into a permanent metal mold for making a blank; obtaining a cast blank of elongate shape and of section that is circular or polygonal; and machining the blank to make the part.

Abstract: A fiber preform is formed by a fiber structure woven by three-dimensional weaving with a plurality of layers of warp yarns interlinked by weft yarns of a plurality of layers of weft yarns, the fiber preform having a first portion and a second portion that extend one another in the weft direction and that are at an angle to each other. In the fold zone and in each weft plane of the fiber structure, two weft yarns situated in a region adjacent to an outside face of the fiber structure situated on the inside of the corner present paths that cross, so that less curvature is imposed on these yarns.

Abstract: The invention relates to a turbine engine module comprising a rotating device (1) having a cover (5), said cover (5) comprising radial through ports (8) for the passage of the oil escaping by centrifugation and means (10) for guiding the oil leaving said ports (8) radially outwards, and a casing (2) defining at least one portion of a lubrication enclosure of said device (1), said casing (2) comprising at least one gutter (13), arranged to recover the oil, characterized in that the gutter (13) comprises an annular bottom wall (12) having at least one discharge port, and in that the casing (2) comprises at least one other port located on the outside of the gutter (13), said at least one other port and said at least one discharge port being connected to common discharge means.

Abstract: A turbomachine subassembly has a radially inner shell and a radially outer shell of an annular gas flow path. A radial arm extends radially between the radially inner and outer shells and delimits an isolated volume which is connected to an inner volume of a chamber partly delimited by the radially inner shell. A segment of a conduit extends radially in the isolated volume, and a ventilation air supply source is connected to supply ventilation air to the isolated volume, whereby ventilation air may be supplied to the chamber through the isolated volume. An external radial end of the radial arm supports a first connection box that closes it off. The internal volume of the radial arm communicates with the ventilation air supply source. An external cylindrical wall of the first connection box fits inside an internal cylindrical wall of the external radial end of the radial arm.

Abstract: The invention proposes a de-icing splitter nose at the inlet of the low-pressure compressor of a double-flow turbine engine. The splitter nose comprises an annular separation surface with a circular leading edge, the surface being adapted to separate an upstream flow into a primary flow and a secondary flow. The nose further comprises an electric de-icing device with a heating element having a series of parallel, electric, heating strips. The strips are inserted between two strata of dielectric material and are able to prevent the formation of ice on the annular surface, as close as possible to the leading edge.

Abstract: A method for generating a three-dimensional (3D) computer model of an assembly that includes wiring routing, which includes creating a part data structure that defines a part in a virtual product management system. The part data structure includes a plurality of nodes that define at least 3D part design data, 3D wiring routing design data and wiring routing annotation data of the part. The method includes importing at least the 3D part design data, the 3D wiring routing design data and the wiring routing annotation data to the part data structure from a computer-aided design (CAD) model system and generating a 3D computer model of the assembly. The method also includes transmitting the 3D computer model of the assembly to an electronic end user device.

Abstract: An aircraft landing gear assembly includes a lock link and a rotary electromechanical actuator which includes motor and gearbox unit arranged to move a pawl into contact with the lock link to break the lock link. A release mechanism is provided to enable the lock link to be made in the event of the motor and gearbox unit jamming.

Abstract: Propulsion unit for an aircraft, comprising a turbine, at least one propeller offset with respect to the turbine, and a power transmission disposed between the turbine and the propeller, the transmission comprising in series two constant velocity joints with a slide connection.

Abstract: The invention relates to the field of turbomachines, and more specifically to an annular element (13) for a turbomachine casing, which has at least one inside face (14) defining a flow passage for a working fluid of the turbomachine, an outside face (15), and a damper (18), comprising at least one resilient coil turn (18a, 18b, 18c) fitted tightly around a surface of revolution (15a) of the outside face (15), in such a manner as to exert pressure on said surface of revolution (15a). The present invention also relates to damping a rotating wave of distortion of such an annular element (13) for a turbomachine casing, wherein said rotating wave is damped by friction between said surface of revolution (15a) and the at least one coil turn (18a, 18b, 18c) of the damper (18).

Abstract: A method of fabricating a low alloy steel ingot, the method including a) melting all or part of an electrode by a vacuum arc remelting method, the electrode, before melting, including iron and carbon, the melted portion of the electrode being collected in a crucible, thus forming a melt pool within the crucible; and b) solidifying the melt pool by heat exchange between the melt pool and a cooling fluid, the heat exchange applied serving to impose a mean solidification speed during step b) that is less than or equal to 45 ?m/s and to obtain an ingot of low alloy steel.

Abstract: A variable section nozzle includes an ejection casing and a plurality of internal flaps arranged in a ring downstream from the ejection casing. Each internal flap is connected to the ejection casing by a movable lever pivotally mounted to the downstream end of the ejection casing. Each lever is movable between a first position in which the internal flaps are in a high position and a second position in which the internal flaps are in a folded-down position. The nozzle includes a plurality of rigid movement transmission parts distributed circumferentially around the ejection casing. Each rigid movement transmission part is connected to two adjacent levers by connecting rods, and to a control actuator. Each rigid movement transmission part can move in a direction corresponding to the axial direction of the nozzle under the action of the control actuator to move the adjacent levers between the first and second positions.

Abstract: A method of electrically powering an electrical load in an aircraft, the method including electrically powering the electrical load with a main source that generates electricity; measuring an instantaneous parameter characterizing the main source; determining a level of use of the main source from the measured instantaneous parameter; adjusting the voltage of the main source as a function of the level of use; measuring an output voltage from the main source; comparing the measured voltage or the level of use with a predetermined threshold value; and whenever the measured voltage is less than the predetermined threshold value, electrically powering the electrical load from an auxiliary source that stores electricity so as to supply additional electric power to the electrical load.

Abstract: A brake rod assembly for an aircraft landing gear. The brake rod assembly includes a support member, a first brake rod having a first pivot point and a second pivot point, and a second brake rod. The support member is coupled to the first pivot point, the second brake rod is coupled to the second pivot point, and the first and second pivot points are longitudinally spaced apart along a first portion of the first brake rod.

Abstract: A sealing system for at least one floatingly mounted ring in a support for a rotary shaft rotatable about an axis directed along a longitudinal direction provides dynamic sealing between the shaft and the support. The system includes a coupling part interposed between the ring and the support, whereby the ring is secured to the support. A first cylindrical type joint directed with respect to a first transverse direction provides a joint between the support and the coupling part. A second cylindrical type joint directed with respect to a second transverse direction perpendicular to the first transverse direction provides a joint between the ring and the coupling part. A turbopump includes such rotary shafts and sealing systems.