Abstract: The present disclosure is generally directed to a core configured for the manufacturing of a turbine engine blade by lost-wax casting. The core includes a first convex curved outer face and a second concave curved outer face. The first and second faces have a plurality of recesses, each recess including a spherical portion.

Abstract: An aircraft undercarriage having a leg for mounting to move on an aircraft structure between a deployed position and a retracted position is provided. The undercarriage generally includes a brace member arranged between the structure of the aircraft and the leg in order to stabilize the leg in the deployed position, and a drive actuator for moving the leg from the deployed position to the retracted position. The brace member includes a strut arm having a proximal end that is designed to be hinged on the structure of the aircraft. The arm presents a longitudinal slot extending until the slot reaches a distal end in order to terminate in a bend and having slidably engaged therein a finger that is secured to the leg, the drive actuator being coupled to the strut arm.

Abstract: A communication method for communication between communication modules interconnected over an electricity network by a wired connection using power line communication conveyed over the wired connection, the method including prior to a communication module transmitting a data signal, a step of frequency modulating the data signal for transmission; after or during the step of modulating the data signal, a step of direct-sequence spreading of the spectrum of the data signal for transmission; and after a communication module receives a data signal, a step of frequency demodulation of the received data signal and a step of direct-sequence unspreading of the spectrum of the received data signal.

Abstract: A structural casing for an axial turbine engine includes an outer ring, an inner hub, and a plurality of struts extending radially from the hub to the ring, wherein the ring is made of a plurality of angular segments welded together. The segments extend circumferentially of different angles, some segments being larger angularly than others. The structural casing is adapted to be an intermediate casing between two compressors of a turbine engine.

Abstract: A process for obtaining borazane (NH3—BH3) includes introducing anhydrous liquid ammonia (NH3(l)) into a reactor thermostatically regulated to between a temperature ?1 and 40° C.; introducing, with stirring, into the reactor an amine borane complex (Am.BH3), the corresponding amine (Am) of which is soluble in anhydrous liquid ammonia only to a proportion of less than 10 g in 100 g of ammonia at 20° C., being introduced in an amount such that the mole ratio R=(NH3(l))/(Am.BH3) is greater than or equal to 5; stirring the mixture; stopping the stirring to obtain two demixed phases: a light phase constituted essentially of a solution of anhydrous liquid ammonia (NH3(l)) containing borazane; and a heavy phase constituted essentially of the amine corresponding to the amine borane complex introduced; isolating the borazane and drying under vacuum thereof; the temperature ?1 being greater than or equal to the melting point of the amine borane complex.

Abstract: An assembly includes an injection system and an injector for an aircraft turbomachine combustion chamber. The system includes an aerodynamic bowl including a first end widening toward the downstream end and centered on a central axis of the injection system, this also including a central body along which a film of fuel is intended to flow in the downstream direction. The central body includes a second end widening toward the downstream end, the first and second widening ends between them delimiting an air through duct and the system includes motion inducing a device allowing a relative movement between the first widening end which is stationary and the second widening end, along the central axis of the injection system, by moving the central body relative to the injector.

Abstract: A method for testing a turbojet engine for an aircraft in a U-shaped or open-air test bench includes: (a) visual inspection of the test bench and of the turbojet engine; and (b) testing of the turbojet engine in the test bench. During the test, the turbojet engine bears test equipment with sensors, other sensors being housed in the test bench. The test bench includes an augmented-reality system performing the step of (a) visual inspection in the test bench in order to detect a possible major anomaly in the test bench. The step of (a) visual inspection is intended to check the conformity of the test conditions, and especially those of the test equipment or that of the test bench as a whole. The method performs the step of (b) testing only in the absence of an anomaly.

Abstract: An assembly comprising a duct (1) for passing a flow of cryogenic fluid, and a valve (2); the assembly being characterized in that the duct (1) includes an interface for inserting the valve, the interface forming an internal abutment (51) and an external abutment (52); the valve (2) being configured in such a manner as to be inserted into said insertion interface by sliding, the valve (2) comprising a valve body (3) presenting a first end (31) and a second end (32), the valve body (3) being adapted to be bolted in said insertion interface in such a manner that the first end (31) and the second end (32) come into abutment respectively against the internal abutment (51) and against the external abutment (52), the assembly including an internal sealing element (61) arranged between the internal abutment (51) and the first end (31), and an external sealing element (62) arranged between the external abutment (52) and the second end (32).

Abstract: The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator (5), characterized in that it comprises a device (20) for spontaneously mechanically coupling said gas generator (5) and said free turbine (6) that is capable of mechanically and spontaneously connecting said gas generator (5) and said free turbine (6) as soon as the ratio of the rotational speed (NGG) of said gas generator to the rotational speed (NTL) of said free turbine reaches a predetermined threshold value.

Abstract: The present invention concerns a backplane electronic board (20) having on inner face (142) suitable for being connected to electronic board connectors (12) and an outer face (143) suitable for being connected to an outer connector (15), the backplane board (20) being characterized in that it has blind holes opening on the inner face (142) of same, and holes opening on the outer face (143) of same, the holes being suitable for receiving press-fit connection elements and forming therewith an electrical connection point.

Abstract: A blade for a turbine engine propeller, in particular a propfan engine, comprising a protruding part on the leading edge thereof, wherein said blade comprises means for controlling the position of the protruding part along the leading edge thereof.

Abstract: The invention relates to a turbomachine casing (1) comprising: a hub (2), an outer shroud (3), and yokes (11) projecting from the outer shroud (3), for attaching the housing (1), characterized in that it comprises at least one stiffener (10) extending between pairs of yokes (11) facing each other, and comprising a central part (18) and side arms (19) projecting from the central part (18).

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 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: 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: The present invention relates to a cooling mixture comprising a fluorinated compound and a non-fluorinated compound, wherein the fluorinated compound is a hydrofluoroether and the non-fluorinated compound includes a carbonyl function, which has a flash point no lower than 23° C. and which is characterised by having low relative volatility. The present invention likewise relates to the use of such a mixture as a coolant in a heat-exchange device.

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: 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: 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: 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).