Abstract: A system for pylon attachment for mounting an engine on a structure of an aircraft, or to wings of the aircraft, including a first attachment mechanism that can be secured to the pylon and a second attachment mechanism that can be secured to the structure of the aircraft. A connection mechanism connects the first and second attachment mechanism, the connection mechanism configured to allow movement of the first attachment mechanism in relation to the second attachment mechanism between first and second positions.

Abstract: The invention relates to a method of identifying and/or tracking deformation of a mechanical part (14) made of composite material for a turbine engine, the part comprising a preform (26) of fiber material and a resin (24). The method consists in incorporating metal particles (22) in the preform or the resin (24) during fabrication of the part (14), and in subjecting the mechanical part (14) to two X-ray inspections on two different occasions so as to identify the part (14) and/or so as to deduce deformation of its internal structure.

Abstract: A detection method of a breakdown of a pressure relief valve of a fuel injection circuit for a turbomachine, the injection circuit including a low pressure stage and a high pressure stage, the low pressure stage having an inlet and an outlet, the high pressure stage having an inlet and an outlet, the low pressure stage being connected to the high pressure stage, the pressure relief valve being connected in parallel with respect to the high pressure stage, the injection circuit further including a recirculation loop including an inlet connected to the outlet of the high pressure stage and an outlet connected to the outlet of the low pressure stage, the method including measuring a differential pressure in the injection circuit.

Abstract: A sealing device for a chamber including at least one rotary member and at least one static member of a jet engine and can contain a lubricating oil droplet suspension. The sealing device includes at least one brush seal that includes juxtaposed strands and is set to ensure sealing between at least one rotary member and at least one stationary member, a mechanism to recover part of the oil suspended within the inner space of the chamber, and a mechanism to deliver the recovered oil. The delivery mechanism is set up to generate a flow of oil along the strands of the brush seal, the oil flow being oriented in the direction of the rotary member. The brush seal thus provides better resistance to coking.

Abstract: A wall in which there is formed at least one cooling channel, said wall being cooled by cool air flowing in the channel, the channel comprising a hole and a diffusion portion, the hole opening out at one end into the inside surface of the wall, and at its other end into the diffusion portion where it forms an orifice, the diffusion portion flaring around said orifice and opening out into the outside surface of the wall, the diffusion portion having a bottom whose front end is substantially plane, sloping, and extending in front of the orifice, and also having a margin extending behind, round the sides, and in front of the orifice, said margin joining the sides of the front end. A method and an electrode for making such a cooling channel. A turbomachine blade presenting such a wall.

Abstract: After the control system has been started, which system has two control paths that are used as alternatives for delivering a control electric current to an electrohydraulic member for transforming said current into hydraulic power that is delivered to the actuator, and before powering a starter-generator of the engine, the detection method comprises implementing the following steps for each of the control paths in succession: delivering a predetermined test electric current over said path; evaluating a difference between the test electric current and a measurement of the electric current as transformed into hydraulic power by the electrohydraulic member; and if said difference is greater than a predefined threshold, detecting an electrical failure on said path.

Abstract: A method of fabricating a part covered in an abradable coating (55), the method comprising the following steps: a blank (10) for the part, the blank having a housing (20) opening out into the surface (15) of the blank (10); filling the housing (20) with an abradable material in powder form; and hot rolling the blank (10) and the abradable material together so as to sinter the abradable material and cause it to adhere to the blank, in order to obtain an abradable coating (55).

Abstract: The invention relates to a device for sealing an opening of an enclosure wall for access to a rotary shaft. The device is capable of being sealingly inserted in said opening and of being secured against the wall by securing elements. The device includes two cylindrical parts assembled slidably relative to one another, coaxially relative to the opening: a first part capable of being statically inserted in the opening, and a second part capable of being secured to the wall by the securing elements and subjected to the action of a resilient means provided between the parts and tending to axially separate the second part from the wall.

Abstract: A two-mode ignitor and to a two-mode method of injection into the ignitor, which includes a feed for a first propellant, a feed for a second propellant, a feed for a high pressure fluid, a first buffer tank, a second buffer tank, a first switch device, a second switch device, and a torch-forming combustion chamber; a downstream orifice from the first buffer tank and a downstream orifice from the second buffer tank both open out into the combustion chamber; the first switch device and second switch device devices are configured respectively to connect an upstream orifice of the first buffer tank with either the first feed or with the feed for high pressure fluid, and to connect the upstream orifice of the second buffer tank either with the second feed or with the feed for the high pressure fluid.

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: The pump includes a stator and a rotor having an impeller in which a fluid duct passes. An axial balancing device arranged on this wheel includes a rear balancing chamber and a passage arranged between the wheel and the stator, enabling evacuation of fluid from the fluid duct to the balancing chamber. The pressure of fluid in the balancing chamber compensates the pressures exerted by the fluid on the rest of the rotor allowing axial balancing of the rotor. The passage includes an upstream nozzle and a downstream nozzle, as well as an intermediate annular chamber, arranged between walls of the wheel and of the stator, the intermediate chamber being arranged downstream of the upstream nozzle and upstream of the downstream nozzle.

Abstract: A device for cutting a fibrous preform, for production of a part made of a composite material by injection of resin under vacuum. The device includes a die for receiving the preform, on which a template of outer edges of the part is referenced, a mechanism cutting outer edges of the preform according to the template, and a mechanism for cooling the preform that is suitable for solidifying a liquid forming a substrate for the preform.

Abstract: The invention provides a fan casing for a gas turbine engine, the casing having a substantially cylindrical portion that terminates at one end in an annular flange made of composite material. The flange includes at least one setback in a fraction of its thickness and at least one bolt for fastening pieces of equipment passing right through the flange in the axial direction, the bolt for fastening pieces of equipment having a head that presents a flat that is to bear flat against a rim of the setback, and a shank forming a stud for fastening pieces of equipment on the casing.

Abstract: A casting pattern for a lost-pattern casting, the pattern being in a shape of a turbine engine blade with a root and a body on either side of a platform that is substantially perpendicular to a main axis of the blade, and a method of producing a shell mold from the pattern, and a casting method using the shell mold. The blade body presents a pressure side, a suction side, a leading edge, and a trailing edge. The pattern also includes an expansion strip adjacent to the trailing edge, and a refractory core embedded in the pattern but presenting, both on the pressure side and on the suction side, a respective flush varnished surface between the trailing edge and the expansion strip. A web extends between the platform and the expansion strip and presents a free edge between them.

Abstract: A turbine engine fan rotor having a disk carrying blades, a substantially frustoconical cover mounted on the disk, and axial retention device for retaining the blades and including a ring mounted in an annular groove in the disk and forming a bearing surface for roots of the blades. The ring is festooned or crenellated and co-operates with a festooned radial annular lip of the disk. The rotor also has at least one axial tooth inserted in hollow portions of the ring and of the lip of the disk. Two coaxial parts arranged radially inside the disk have respective first and second fastener flanges for fastening to the disk, said flanges being axially interposed between the cover and the disk, being circumferentially offset relative to one another, and being fastened independently of one another to the disk.

Abstract: A vane intended to be mounted in a supply fluid pattern, the vane comprising: a blade delimited in a lateral direction by an outer surface having an upper surface and an lower surface which are joined at ends, so as to form there a leading edge and a trailing edge respectively, the blade housing a channel for routing data and having a groove leading to at least one of the upper surface and lower surface walls and which communicates with the data routing channel, and data collecting means for collecting data on one of the outer surface of the blade and the close vicinity thereof, the data collecting means being connected, through the groove, to the data routing channel, or extending therethrough, wherein the data collecting means comprises one of an inserted tube and a cable, and the groove is formed in one of the upper surface and lower surface wall opposite that whereto said one of the tube and the cable leads, and the blade is gone through by an orifice provided between the upper surface and the lower su

Abstract: The invention relates to an assembly comprising a turbine engine casing and a bladed rotor wheel arranged therein. The casing presents an inside wall having a circumferential strip of abradable material. Facing the tips of the blades, the casing presents upstream the strip of abradable material, and downstream a circumferential groove. The strip of abradable material is defined downstream by the circumferential groove. The downstream end of the circumferential groove is in register with or downstream from the trailing edges of the blades. This arrangement optimizes the use of abradable material in the casings of the turbine engines.

Abstract: The invention relates to an appliance (8) for compacting, drying and cutting a preform of a hollow component of a turbomachine, said appliance comprising: a base (2, 2a) acting as a support for a sheet of material (1, 7) and comprising a long impression (22, 22a); a mandrel (3, 3a) which can be positioned in said long impression, clamping the sheet of material against the base, thus defining two flaps (12, 13, 72, 73) of said sheet (1, 7) arranged either side of the mandrel (3, 3a); and two side blocks (5, 6, 5a, 6a) which can be positioned such that they are supported on the base, either side of the mandrel, clamping the flaps of the sheet against the mandrel, said side blocks and/or the mandrel co-operating with means for cutting said flaps in such a way that they are adjusted to the dimensions of the mandrel or said side blocks.

Abstract: A field of casting, and more particularly to a shell mold, and also to methods of fabricating and using such a shell mold. This shell mold includes a central cylinder, a plurality of molding cavities arranged in an assembly around the central cylinder, and at least one heat shield that is substantially perpendicular to the main axis. The central cylinder extends along a main axis between a casting cup and a base. Each molding cavity is connected to the casting cup by at least one feed channel, and also, by a baffle-selector with a starter in the base. The at least one heat shield completely surrounds each molding cavity in a plane that is substantially perpendicular to the main axis.

Abstract: The invention provides an injection mold core (100) for making a composite material part having a closed box, the core being in the shape of a wedge that is to be inserted inside a closed box (12) of at least one fiber preform into which a matrix-precursor fluid is to be injected, the core presenting both an opening right section (106) through which the core is to be unmolded from the box of the preform after the matrix has set, and also a maximum right section (108) of greater size than the opening right section, the core comprising at least three distinct elements (110, 112, 114) that are assembled together, each core element presenting a maximum right section of size that is smaller than the opening section.