Abstract: The present application relates to a stator of an axial turbomachine compressor. The stator includes a circular wall, such as an internal shroud, with a guiding surface in order to guide the primary flow of the turbomachine. The stator further includes a circular row of stator vanes, each of them including an airfoil which extends radially in the primary flow of the turbomachine, and a securing portion. The securing portion of the vane includes a lattice which has rods and which is secured and/or sealed in the shroud in order to fix the vanes to the shroud via the lattices. The stator includes a joint of abradable material which is arranged inside the internal shroud, and in which the lattice is secured in order to ensure retention, a fixing between the vane and the internal shroud. The vane is produced by means of additive production.

Abstract: The present application relates to a stator blade sector configured to be fixed to a housing of an axial turbomachine, the sector having a plurality of blades with platforms juxtaposed, so as to describe an arc of a circle. At least one of the platforms comprises on its outer face a fixing screw and at least one other platform has no fixing screws, the platforms being fixed together at their adjacent edges. The application also relates to a stator or portion of stator having a housing forming a generally circular wall and blade sectors arranged along the wall. The housing includes several parts connected to each other by longitudinal flanges. Platforms with no fixing screws are located opposite the flanges.

Abstract: A system for contactless measurement of circular geometrical parameters of a turbine engine component, comprising a contactless measurement module comprising a support, having a fixed position, for supporting said turbine engine component; an optical measurement device for transmitting a plurality of light beams onto at least said internal surface of said internal side wall, and for acquiring a plurality of reflections coming from said plurality of light beams, mechanically coupled to said support and comprising: an electronic conversion unit for converting a plurality of signals of said first optical sensor into a plurality of values of said plurality of circular geometrical parameters.

Abstract: The present application relates to a method of injection molding a resin such as a RTM mold. The method enables to manufacture a composite part comprising a resin body and a sheet or strip, forming a surface of the composite part. The composite part can be an annular compressor casing of an axial turbomachine, with a composite annular wall. The method includes the steps of: (a) placing and holding the sheet against a mold surface by fastening means such as welds or microwelds; (b) injection and solidification of the resin in the mold so as to form the body by binding it to the sheet; (c) release of the sheet by the fastening means when a release force is exerted on the composite and release part of the composite part.

Abstract: A fluid valve includes a valve member located between a first cavity and a second cavity, and an actuator that includes a pilot. The valve member is moved by the balance between the pressure prevailing in the first cavity and the pressure prevailing in the second cavity. The valve member includes a longitudinal hole that can be blocked by the pilot so as to modify the pressure prevailing in the first cavity and the force acting on the valve member so as to vary a fluid flow rate between an inlet and two outlets. The valve member is attached to a piston, one end of which is located in a third cavity. The force acting on the valve member is determined by the pressures prevailing in the various cavities.

Abstract: The present application relates to an electromagnetic valve, in particular for high-pressure cryogenic gas for a rocket. The valve includes a body in which a passage is formed connecting an inlet to an outlet, a seat communicating with the passage, a ball sealing the seat when the valve is at rest, a magnetic circuit with a coil, a magnetic shell, and a plunger displacing the ball relative to the seat thereof in order to open and/or close the seat. The plunger is telescopic, i.e., extendable and retractable. The plunger includes two ferromagnetic portions that are movable relative to one another and relative to the passage. The portions are fitted one inside the other and define air gaps E2 and E3 therebetween. The valve includes a magnet and a spring on either side of a secondary portion to hold the secondary portion in the closed position, distancing a ball from the exhaust seat.

Abstract: The present application relates to a blade of a rectifier of a low pressure compressor of an axial turbomachine. The blade can also be a rotor and/or turbine blade. The blade includes a composite material with a matrix and a reinforcement comprising a mesh with rods. The rods of the reinforcement are connected to each other and are distributed throughout the volume between the pressure side surface and the suction side surface of the blade. The mesh forms a three-dimensional structure extending over the majority of the thickness of the blade between the pressure side surface and the suction side surface and/or the majority of the length of the blade between the leading edge and the trailing edge. The present application also relates to an iterative method for manufacturing a blade composite where the reinforcement is formed by additive layer manufacturing based on titanium powder and then placed in an injection mold.

Abstract: A composite external casing for a compressor of an axial-flow turbomachine, the casing comprising a generally circular wall having a matrix and a woven fibrous reinforcement. The latter is formed by a stack of fibrous plies having fibers woven according to a weft positioned in the axis of the circular wall, and a warp positioned around the circumference of the wall. The stack of plies comprising, depending on thickness, two external layers and one central layer. The layers include differences in the proportions between the weft fibers and the warp fibers. In the external layers the warp fibers make up the majority. In the central layer the weft fibers make up the majority. The stack exhibits interlayers inserted between the central layer and each external layer. The plies corresponding to the interlayers exhibit fibers woven at +45° and ?45° in relation to the axis of rotation of the turbomachine.

Abstract: The invention relates to an external composite housing for a compressor of an axial turbomachine, the housing having a generally circular wall with a matrix and fiber reinforcement. The housing includes a circular wall with an internal surface having a continuous curve around the circumference of the wall. The wall includes flat facets that are flush with the internal curved surface of the wall. The facets are arranged in annular rows to receive annular rows of stator vanes. The facets are flat disks against which the vanes bear to optimize the orientation of the vanes, while reducing the concentrations of mechanical stresses at the platform/wall interfaces.

Abstract: The present application relates to a splitter nose of an axial turbomachine designed to separate an annular flow into the turbomachine into a primary flow and a secondary flow for undergoing a thermodynamic cycle. The nose includes a de-icing device with a wall defining, at least partially, an annular channel. A hot oil stream created by the turbomachine circulates in this latter. The oil runs through the circular nose and de-ices it while itself getting cooled. The wall is located so as to form the leading edge of the said splitter nose. The wall is an open or closed strip such as a tube which can be fixed by bonding, welding or recessing. The present application also relates to a multi-flow turbomachine with splitter noses fitted with de-icing devices.

Abstract: The present application relates to a method for assembling a stator stage of a turbomachine, the stage having an inner ring, an outer ring, and vanes extending radially between the inner ring and the outer ring. The method includes at least the following essential step: applying at least one inflatable bladder against at least one opening between a vane and one of the inner ring and the outer ring on that face of the ring which is opposite the face for application of a sealing material, so as to form one or more retention surfaces for the sealing material. The present application also relates to an assembly device designed for implementing the method.

Abstract: The invention relates to a blade of an axial turbomachine comprising an airfoil which extends radially and a first set of branches or divisions, which radially extend a radial end of the airfoil, and a second set of branches which radially extend the other of the radial ends of the airfoil and which are offset over the circumference of the turbomachine. The branches extend axially along the entire length of the airfoil. The sets have different numbers of branches. The branches further occupy the channel of the turbomachine and further counteract debris in the event of intake.

Abstract: An internal gear pump includes a pinion, a ring arranged around the pinion, and a cylindrical wall arranged around the ring. A support element, on which the pinion and the ring are supported, carries high-pressure liquid towards a recess located at the junction between the ring and the cylindrical wall, and also carries low-pressure liquid towards another recess located at another point of the junction between the ring and the cylindrical wall. The recess allows the load of the ring on the cylindrical wall to be reduced.

Abstract: An aircraft comprising a turbine engine, an atomizer, a reservoir, a conduit connecting the reservoir to the atomizer, and a unit for controlling the flow of liquid in the atomizer. The turbine engine, the atomizer, the reservoir, the conduit and the control unit are fixed to the aircraft. This allows cleaning in flight of at least some parts of the turbine engine.

Abstract: An annular cover for a lubrication chamber of a rotary bearing of a turbomachine. The cover includes a wall that is generally circular and flared with an orifice that is designed to receive a transmission shaft opposite an assembly surface for the cover, and at least one duct communicating with the inside of the wall and extending along the wall as far as the assembly surface. The duct is formed in the thickness of the body of the wall which is made from the same material, and which includes a composite material with a thermoplastic matrix and carbon fibers.

Abstract: The present application relates to a blade of low pressure rectifier axial turbomachine. The blade can also be a rotor blade and/or a turbine blade. The blade includes a composite material with a matrix and a reinforcement that includes a mesh forming a three dimensional structure with a plurality of rods that describe a three-dimensional mesh based on polyhedrons. The three-dimensional structure extends over the majority of the thickness of the blade between the pressure side surface and the suction side surface and/or the majority of the length of the blade between the leading edge and the trailing edge. The rods of the reinforcement are bonded to each other and are distributed throughout the volume between the pressure side surface and the suction side surface of the blade. The rods form a three-dimensional mesh occupying the entire blade. The present application also relates to an iterative method for manufacturing a blade by additional layer manufacturing.

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: The invention relates to an axial turbomachine stator (2) comprising an inner shell (28) with an annular row of openings; an annular row of blades (26); the said blades extending substantially radially through the said openings, respectively, and each comprising a cut-out (34) on the inside of the shell; at least one blade-retaining plate (36) inserted in at least one cut-out (34), with means of immobilization of the said plate in the cut-out(s). The means of immobilization comprise at least one tongue (38) with an end forming a support surface (40) in contact with a part of the blade (26) or of one of the blades (26) located radially directly above the corresponding cut-out.

Abstract: A sealing device of an axial turbomachine, comprising a circular strip with an outer surface and an inner surface; an annular layer of abradable material on one of the outer and inner surfaces of the strip, designed to provide a sealing with an annular row of rotor blades. The surface of the strip covered by the abradable layer comprises at least two perforated circular zones, each with a series of distributed perforations. The surface of the strip covered by the abradable layer further comprises a smooth circular zone disposed axially between the perforated areas. The smooth zone is centered on the outer ends of the rotor blades. The smooth circular zone and the two perforated circular zones improve the adhesion of the abradable layer on the metal strip, and avoid a premature breakdown of the abradable layer in contact with the rotor blades, despite the presence of perforations.

Abstract: The present application relates to the compressor drum of an axial turbomachine. The drum includes a wall of revolution that forms a hollow body. The wall includes two annular retaining surfaces of the blades which mate with corresponding retaining surfaces of the said blades. These surfaces are generally directed away from one another to form a profile which diverges as its distance radially from the outer surface of the wall increases. The retaining surfaces of the drum may be formed on an outer annular body or on inclined annular flanges.