Abstract: A method of preparing a substrate to receive a metal coating deposited by thermal spraying, the method including the following steps: a) depositing a layer of adhesive on the zone to be coated, the layer having a uniform thickness greater than 10 ?m and less than 100 ?m; b) before the adhesive dries, cold spraying a metal powder onto the zone to be coated, so that powder particles become embedded at least in part in the layer of adhesive; and c) drying the adhesive in which the powder particles remain held captive, thereby forming an undercoat suitable for receiving a metal coating deposited by thermal spraying. The method is applicable to protecting the leading edges of fan blades.

Abstract: A rotor disc (1) for a turbomachine, including a radial flange (2) that includes a plurality of fastening holes (3), and a plurality of scallops (4) forming notches in the flange (2), and being separated by inter-scallop flange portions (7). The flange alternatively has, in its circumferential direction: a fastening hole (3) and an inter-scallop flange portion (7) arranged in the radial extension of the fastening hole (3), and a scallop (4), in such a way that one or more of the scallops (47, 48, 49; 42, 45-47, 48-411, 414) has a volume greater than the volume of each of the other scallops (41-46, 410-414; 41, 43, 44, 412, 413), and one or more of the inter-scallop flange portions (73) has a volume less than the volume of each of the other inter-scallop flange portions (71, 72, 74), in order to balance said disc (1). A turbomachine including that rotor disc and a method for balancing a turbomachine rotor disc are also disclosed.

Abstract: A method of disassembling reinforcement from a part, the method including: fastening at least one metal stud on one side wall of the reinforcement and at least one other metal stud on the other side wall of the reinforcement, the studs extending substantially perpendicularly to the side walls on which they are fastened; moving the studs apart from each other to space apart the side walls of reinforcement and disengage snap-fastener mechanisms thereof from complementary mechanisms of the part; and removing the reinforcement from the part.

Abstract: A method for forming a preform for a hollow turbomachine component is provided. The method includes positioning a sheet made of woven fibers on a base equipped with a longitudinal impression; positioning a mandrel in the longitudinal impression to clamp the sheet between the base and the mandrel, the mandrel having a thickness that increases between a proximal end and a distal end; locking the distal end of the mandrel into position; placing a proximal block resting on the base; forming two flaps of the sheet around the flanks of the mandrel; resting two lateral blocks on the base on either side of the mandrel; locking the lateral blocks into position to form an assembly; drying the assembly to form a preform including a flat base, from which two flaps extend perpendicularly; and adjusting the flaps to the dimensions of the mandrel by trimming excess material.

Abstract: A gas turbine casing made of organic matrix composite material includes reinforcement densified by an organic matrix defines an inside volume. On its inside face the casing has a structural part with a first face facing the inside face of the casing, and an opposite second face defining a flow passage portion. Recesses opening out into the inside volume of the casing are present between the inside face of the casing and the first face of the structural part facing the inside face of the casing. In the event of a fire, the recesses allow gas coming from degradation of the resin of the casing to be discharged into the flow passage.

Abstract: A turbine or compressor stage for a turbine engine is provided. The stage includes a disk including a metal material configured to be coupled to a shaft of the turbine engine, an airfoil including a ceramic matrix composite material, and an interface part that is distinct from the airfoil and that is configured to be fastened to the disk and to fasten the airfoil. The interface part includes a ceramic or a ceramic matrix composite material.

Abstract: The invention relates to an extension (30) of an intermediate frame for an aircraft turbine engine, that will project downstream from an outer ring of the intermediate frame, this extension comprising a downstream annular connecting part (64) preferably forming an annular groove (66) open radially outwards, into which the nacelle cowls will fit (38), the end (64) comprising at least one first angular sector (76b). According to the invention, the extension comprises a body (77) made from a single piece comprising a junction ring (74) and at least one second angular sector (76a) of said downstream annular connecting part (64), the first angular sector being added onto the extension body (77).

Abstract: An aeronautic engine including: a housing made of electrically insulating material and including at least one metallic piece; a structural piece of the engine including metallic material and connected to the housing; and an equipment fixed to the housing, is provided. The equipment is connected to the structural piece by the metallic piece by an electrically conductive connecting path.

Abstract: A moving blade of a low pressure turbine includes a foot and a vane having an upper surface and a lower surface, the foot having a stilt linking the vane to the foot, wherein the stilt is formed such that the transverse section of the stilt has: a first straight portion, a second curved portion and a third straight portion, the curved portion having an outer face matching the profile of the upper surface of the vane and an inner face matching the profile of the lower surface of the vane.

Abstract: An air supply device for an aircraft engine turbine, in which device the air is conveyed to at least one aircraft engine turbine after being conveyed through at least one connecting sleeve from a low pressure distributor to a space defined by at least one upstream side and one downstream side, the upstream side having at least one opening and each pierced opening receiving one end of one of the connecting sleeves, wherein the upstream side and the downstream side are secured by at least one fastener. A retaining plate is used for each fastener in order to position a securing element of the fastener, the retaining plate having a supporting surface that blocks each connecting sleeve axially in one direction.

Abstract: A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of annular shape defining upstream and downstream portions of the cowl and which is traversed by the suspension mast. The downstream portion of the cowl of the main nozzle includes a first part extending downstream from the upstream portion of the cowl to a trailing edge of the main nozzle, on either side of the suspension mast along two predefined angular sectors; and a second part formed from an internal contour of the slot and having a trailing edge with a diameter smaller than that of the trailing edge associated with the first part of the downstream portion of the cowl. Connecting walls laterally connect the first and second parts of the downstream portion.

Abstract: The invention relates to the field of aerial propellers, in particular the field of variable-pitch propellers, specifically for unducted fans. More specifically, the invention relates to a pivot (15) for a blade (14) of a propeller (3a, 3b), the pivot including at least a proximal portion (15a) made of metal and suitable for being retained in a radial orifice of a propeller hub, while being capable of turning in said orifice about a longitudinal axis (Z) of the pivot (15), and a distal portion (15b) including a receptacle (20) suitable for retaining a blade root, and at least one arm (17) of organic matrix composite material extending laterally relative to said longitudinal axis (Z) and supporting a flyweight (16).

Abstract: A capacitive sensor for measuring the clearance between the apex of the vanes of a rotor and the inner surface of an abradable coating covering the inner surface of a turbomachine casing, the clearance measuring capacitive sensor including a first electrode the material of which is abradable so as to get worn upon contacting an apex of a vane, the material of the first electrode having a degree of wear substantially identical to the degree of wear of the material of the abradable coating.

Abstract: An ignition unit for a turbojet engine, including: an electrical power supply, a single control channel to receive a control signal from a computer, a main sparkplug ignition channel to energize at least one main sparkplug of a main combustion chamber, and an afterburner sparkplug ignition channel to energize at least one afterburner sparkplug of an afterburner chamber. The ignition unit is configured, in response to pulsed controls on the single control channel, to selectively activate the main sparkplug ignition channel or the afterburner sparkplug ignition channel.

Abstract: A method for manufacturing a turbomachine casing from composite material including: creating a semi-rigid protective layer from dry glass fibers that protects against galvanic corrosion, arranging the protective layer on a profiled mandrel by applying the protective layer against the annular radial flange thereof, forming and densifying the fibrous reinforcement on the mandrel while covering the protective layer.

Abstract: A turbomachine fitted with a device for gathering the information recorded during operation of the former by a strain gauge positioned on a fan blade borne by a fan disc of the turbomachine, the device including a hollow cylindrical pipe positioned inside one of the rotating shafts of the turbomachine in order to guide at least one wire for transmitting this information, wherein the device further includes a part for attaching the pipe to the rotating shaft.

Abstract: A device for sealing the coaxial shafts of a turbomachine includes an annular seal able to perform sealing by contact with the outer shaft, and a lubricating device to lubricate the region of contact between the annular seal and the outer shaft.

Abstract: The balance weight is fixed to the flange of a rotor element by a pre-fixing screw with a conical head engaged into a conical counterbore having a shape complementary to the flange, which places the weight at a very accurate position before permanently fixing it by a clamping stud.

Abstract: A fan including a system for holding blades having variable pitch, in which the bases of the blades are mounted onto radial shafts of a rotor of the fan by pivots, is provided. The system includes a main body capable of being attached onto the rotor; and at least one holding arm mounted onto the main body and capable of extending inside a pivot so as to engage with the pivot in order to lock the movement of the pivot along the axis of the shaft on which the holding arm is mounted.

Abstract: The device for securing and retaining at least one electrical harness in a turbomachine includes: at least one hollow profiled element that extends in one direction and has at least two slots of approximately the same dimension and; and a clamping element intended to retain the at least one harness in position in a manner parallel to the hollow profiled element. The clamping element includes: a touch-and-close tape designed to cooperate with the width of the slots so as to allow it to pass on both sides of the profiled element and; an end stop secured to the tape, the end stop preventing the tape from passing through one of the slots in the profiled element.