Abstract: A part for a Joule-Thomson cooler, comprising a gas discharge pipe and a seal closing the gas discharge pipe, the seal being capable of breaking, at least partially, under the effect of gas expansion triggered by the cooler so as to allow the gas to be discharged out of the cooler through the gas discharge pipe. The part is obtained by an additive manufacturing method that comprises stacking layers of powder along a stacking axis in order to form the part, the stacking axis being parallel to a central axis of a second gas discharge pipe separate from the first discharge pipe.

Abstract: The present disclosure concerns a system for installing and removing a propulsion unit on a pylon of an aircraft, a propulsion unit of the type including a nacelle and a turbojet engine, the turbojet engine being linked on the pylon by at least one front suspension and one rear suspension. The system includes a supporting structure which is adapted to support a thrust reverser device, a front suspension of the turbojet engine, which carries a front part of the supporting structure, and which is removably fastened on a front part of the pylon, and a rear suspension of the turbojet engine which carries a rear part of the supporting structure, and which is removably fastened on a rear part of the pylon, and the disengagement of said suspensions of the pylon allowing removing the propulsion unit mounted on the pylon.

Abstract: A wheel blade for a turbomachine compressor. The blade comprises a body extending between the root of the blade in the direction of the height of the blade. The body extends from a leading-edge to a trailing edge in a direction of the camber line of the blade. The blade comprises a winglet located in the extension of the body in the direction of the height. The winglet is located at the tip of the blade and at the leading edge of the blade. The body has a curvature oriented in a first direction of rotation with respect to the direction of the camber line, the winglet having a curvature in a second direction of rotation counter to the first direction of rotation.

Abstract: A turbine vane including at least one inner cavity including a plurality of deflectors which are carried by an inner face of the lower surface wall and by an inner face of the upper surface wall, wherein each deflector extends mainly in a transverse direction from the inner face of the lower surface wall or from the inner face of the upper surface wall, in the direction of the other one of the lower surface wall or the upper surface wall, and wherein the length of each deflector in the transverse direction is greater than half the transverse distance between the inner face of the lower surface wall and the inner face of the upper surface wall, on either side of the deflector.

Abstract: A passenger seat voice communication system (100) for a passenger seat of a passenger vehicle includes a first communication device (102A) that supports voice communication. The first communication (102A) device includes a receiver (108) and a video monitor (110). The system includes a second communication device (102B) configured to support voice communication at a second passenger seat. The system also includes a controller (104) that receives from the first communication device (102A) a selection and request to establish voice communication with the second passenger seat, and sends the request to the second communication device (102B). If the request is accepted by the second communication device (102B), the controller (104) establishes voice communication between the first communication device (102A) and the second communication device (102B).

Abstract: A tool for removing an annular part mounted around a shaft of a turbomachine, includes a holder configured to cooperate with a lifting system, a system for coupling and holding the annular part, the coupling and holding system being secured to the holder, the system for coupling and holding having an opening designed to receive the shaft of the turbomachine during the removal of the annular part, the coupling and holding system being rotatable with respect to the holder between a first position and a second position by a rotation system for tilting the annular part with respect to the holder when the coupling and holding system is fastened to the annular part.

Abstract: A method is for fabricating a part by additive manufacturing while sparing certain particularly sensitive surfaces of the part, and in particular surfaces that have an influence on the aerodynamics of the final part. The method includes the following steps: providing a digital model of a part that is to be fabricated, the part that is to be fabricated including at least one surface that is to be spared, and orienting the digital model relative to a construction direction wherein the part is to be constructed in such a manner that the surface that is to be spared presents a construction angle greater than 30°, preferably greater than 50°.

Abstract: An energy absorbing assembly for a passenger seat that includes a crushable energy absorbing element for safely capturing kinetic energy during an impact event. The energy absorbing assembly comprises a linkage which is mechanically connected with moving parts of the seat back or seat pan by a first attachment element and a second attachment element, and the linkage includes an extended portion that extends beyond one of the attachment elements. A crushable energy absorbing element is mounted around the extended portion of the linkage and connected thereto, so that the crushable energy absorbing element receives and absorbs energy by deformation when the seat back is pushed forward with sufficiently high energy.

Abstract: An aircraft landing gear includes a strut leg, a bottom portion carrying at least one wheel and mounted to slide in the strut leg, and a plurality of elements such as power electric cables, signal-carrying electric cables, and hydraulic pipes extending toward the bottom portion along the strut leg and terminating at the bottom portion, all of the elements being flexible between a bottom end of the strut leg and the bottom portion of the landing gear. The landing gear includes a first movable support having a proximal end hinged to the bottom end of the strut leg, and a distal end carrying a rack for receiving and guiding the flexible elements. The landing gear also includes a second movable support having a distal end hinged to the bottom portion of the landing gear and a proximal end carrying a rack for receiving and guiding the flexible elements.

Abstract: A process for shaping a fibrous preform includes the insertion of each attachment tab of a fibrous texture into a corresponding aperture of an impregnation mandrel, the attachment by a removable retaining device of each tab inserted into each aperture against a surface of the impregnation mandrel, the winding under tension of the fibrous texture on the impregnation mandrel in order to obtain a fibrous preform.

Abstract: The present invention relates to an oil transfer device (1) for lubricating a planet carrier, movable in rotation, of an epicyclic gear train for a turbomachine, the device (1) extending around an axis (A) and having: an annular casing (11) which extends around the axis (A), the casing (11) comprising a plurality of oil feed grooves (14), axially juxtaposed, each having an oil ejection opening configured to lead radially to a lubrication circuit of the planet carrier to be lubricated, the device (1) being characterized in that one of the oil feed grooves (14) is a high-pressure oil feed groove (14), called a high-pressure groove (14a), and another of the other oil feed grooves (14) is a low-pressure oil feed groove (14), called a low-pressure groove (14b), axially juxtaposed to the high-pressure groove (14a), the grooves (14) being arranged axially along the axis (X) so that the oil is able to be transferred axially from the high-pressure groove (14a) to the low-pressure groove (14b).

Abstract: The aircraft motor architecture comprises two reversible electric machines (3, 4), the rotors (10) of which are linked both to the low pressure shaft (1) and to the high pressure shaft (2) by transmissions (11, 12, 13, 14) alternately disengaged depending on the direction of rotation of the rotor (10), the transmissions comprising passive one-way clutches (15, 16, 17, 18), the engagement directions of which are opposed. Independent modes of operation of the machines, as a starter or as an electric generator of each of the shafts, are thus provided.

Abstract: An extraction tool for extracting a shim located in a turbomachine and provided with a through-hole, includes an extractor pin configured to be inserted into the through-hole of the shim; a first gripping member with a first distal end intended to be positioned opposite the through-hole on a first side of the shim and arranged to retain a first end of the extractor pin; and a second gripping member including a second distal end intended to be positioned opposite the through-hole on a second, opposite side of the shim, and arranged to retain a second, opposite end of the extractor pin, after the extractor pin has been inserted into the through-hole of the shim.

Abstract: A method of fabricating a composite material casing of varying thickness for a gas turbine includes using three-dimensional or multilayer weaving to make a fiber texture in the form of a strip; winding the fiber texture as a plurality of superposed layers onto a mandrel of profile corresponding to the profile of the casing to be fabricated, so as to obtain a fiber preform of shape corresponding to the shape of the casing to be fabricated; and densifying the fiber preform with a matrix. During winding of the fiber texture on the mandrel, a textile strip is interposed between the adjacent turns of the fiber texture, the textile strip presenting a width that is less than the width of the fiber texture and defining a retention zone of the casing.

Abstract: An actuator includes a screw mounted on a body to pivot, a nut connected to an element for moving, and that is engaged on the screw to be moved between an over-retracted first position and a deployed second position on either side of a retracted third position that is spaced apart from the over-retracted position by a distance corresponding to the screw rotating through a first angular sector and an anti-extension device comprising a friction disk having at least one smooth surface and an obstacle both for co-operating with at least one pawl, thereby defining both at least one second angular sector of free rotation for the friction disk and also a position for blocking the friction disk.

Abstract: An assembly for a turbomachine including an annular channel designed to form a flow duct for a flow of gas between two turbine stages of the turbomachine. The channel is bounded by a radially inner annular wall and a radially outer annular wall. The walls are connected by hollow arms that extend radially, a support having a radially outer annular part that is located radially outside the outer annular wall of the annular channel, and a radially inner annular part that is located radially inside the inner annular wall of the annular channel. The outer and inner parts of the support are connected by connecting parts that extend radially and pass through one of the hollow arms of the annular channel. The connecting parts may be connected by a connecting partition having a frangible part that ruptures when the mechanical stresses in the connecting partition are above a threshold.

Abstract: Systems for determining a flight stage of an aircraft are described in which a vibration sensor and a sensor for determining a pitch of the aircraft are utilized. A server receives signals from the vibration sensor and pitch sensor, and determines the flight stage using a set of algorithms. Depending on the flight stage determined, a command signal can be generated and transmitted to cause one or more components of the aircraft to change in function or power on or off.

Abstract: A turbine engine heat exchanger for exchanging heat between a first fluid and a second fluid includes a reference axis, a network of tubular meshes having a plurality of meshes each of which is formed, successively in a reference direction, of at least two curvilinear branches, called anterior branches, of a junction where the two anterior branches meet, and of at least two curvilinear branches, called posterior branches, diverging from the junction, wherein the meshes are stacked in staggered rows.

Abstract: A rotor disc for a turbomachine, the disc extending circumferentially about an axis and including a plurality of cavities configured to receive blade roots, each cavity including a downstream radial wall configured to axially block the blade root in the cavity, each downstream radial wall including a channel of ventilation of the cavity, including an inlet orifice which opens into the cavity and an outlet orifice which opens onto a downstream surface of the disc. An assembly for a turbomachine including such a disc and an upstream retention ring and a turbomachine including such an assembly.

Abstract: An aircraft turbine engine includes a gas generator and a fan arranged upstream from the gas generator and configured to generate a main gas flow, one portion of which flows in a flow path of the gas generator to form a primary flow, and another portion of which flows in a flow path around the gas generator to form a secondary flow. The gas generator includes a low-pressure compressor that includes a rotor driving the fan. The turbine engine further includes an electric machine. The electric machine includes a rotor rotated by the rotor of the low-pressure compressor, and a stator extending around the rotor of the electric machine and configured to be cooled by the primary flow.