Abstract: An aircraft bypass turbojet engine lubrication unit includes from three to five superposed pumps, a body housing the pumps and an internal passage in the body for communicating with each of the pumps. The material of the body exhibits a stack of layers in a direction of stacking, the pumps being housed in the said stack of layers. The passage exhibits an end in the direction of stacking of the layers and an internal profile, for example triangular, with two straight lines which form the said end and which are inclined with respect to the stacked layers. The lubrication unit may be manufactured by additive manufacturing in layers.

Abstract: A fluid valve is suitable for use with a hydraulic circuit of an item of aircraft equipment. The fluid valve includes a valve body having one inlet, two outlets and a communication channel with an external pressure source. The fluid valve further includes an electric solenoid actuator located in the valve body and having a movable ferromagnetic pilot. A valve member is movable inside valve body to at least partially block a passage between said inlet and one of the two outlets. The valve member at least partially defines first and second cavities. A fixed limiter is disposed within the communication channel such that a displacement of the movable pilot causes a variation in pressure in one of the first and second cavities to produce a force for moving the valve member.

Abstract: A composition for an abradable seal for a turbomachine, in particular in powder form, is able to crumble in the event of contact with a rotor of said turbomachine. The seal is formed on the arcuate wall of a substrate casing. The composition includes a majority metallic phase with a majority by mass of aluminium with some chromium, a minority second phase including a mineral material and/or an organic material.

Abstract: A stator blades of an axial turbomachine intended to be fitted on a ferrule in an annular row of identical blades. Each blade includes a platform with opposed lateral edges and a screw to the ferrule. The contour of the platform has, at each of the lateral edges, an angular profile designed to mate with the contiguous edge of the platform of an adjacent blade. This feature enables the angular position or pitch of the blade to be set. In a blade row fixed on a stator, mechanical clearances J1, J2, J3 and the fixation screws cause an average angular orientation error. The blades are made with a compensatory angle to offset the angular orientation error.

Abstract: The present application relates to a method for producing a housing for an axial turbomachine compressor having a metal sheet with annular rows of stator blades which are welded to the metal sheet. The method includes the steps of: (a) providing or producing a planar metal sheet with a step of machining in order to form blade stumps; (b) welding stator blades of friction to one of the planar faces of the metal sheet, the blades being arranged so as to form parallel straight rows of blades; (c) bending the metal sheet about a bending axis perpendicular to each row of blades, so as to form a half-tube with annular half-rows of blades which are axially spaced apart, and producing annular grooves by rolling; (d) welding annular flanges and axial flanges; (e) application of annular layers of abradable material.

Abstract: A test bench for an aircraft turbojet engine is provided. The test bench comprises a U-shaped configuration with a passage in the form of an elongated corridor, an inlet duct, and an outlet duct. The corridor comprises a fixing zone with a fixing arm for holding a turbojet engine during testing. The passage furthermore has an upstream shutter with vertical pivoting air guides and a downstream shutter with an inflatable balloon in a collector tube. In the event of fire, the shutters close to confine the turbojet engine in order to suffocate the fire rapidly. A method for managing a fire in a test bench with a passage is also provided. Shutters are placed in the passage, where they deploy.

Abstract: A test bench for turbomachine comprising: an installation zone for turbomachine; an active system for attenuating the noise emissions produced by the turbomachine. The active system includes an attenuation zone with emitters such as loudspeakers; a first microphone placed downstream of the turbomachine; and a second microphone placed downstream of the attenuation zone. The system reduces the turbomachine waves on the basis of the measurements from the first microphone and from the second microphone. The invention also proposes a method for attenuating the noise emissions from the turbomachine tested in the test bench.

Abstract: The invention proposes a splitter lip for a low-pressure compressor of an axial turbomachine for an aeroplane. The splitter lip comprises an upstream annular wall made of metal with a circular leading edge, and a downstream annular partition made of an organic-matrix, short-fiber composite material. The splitter lip also supports an outer shroud for a stator upstream of the compressor. The upstream wall comprises an annular anchoring portion arranged in the thickness of the downstream partition so as to anchor the partition and the wall to one another. The anchoring portion has distributed hexagonal openings in order to increase anchoring. The invention also proposes a method for producing, by molding, a bi-material splitter lip or a mixed lip.

Abstract: A low-pressure compressor for a turbine engine, such as an aircraft turbojet engine includes a rotor with two rows of rotor blades between which two annular ribs are positioned; and one annular row of stator blades between the rotor blades. An internal shroud is connected to the stator blades. The internal shroud includes abradable material collaborating with the annular ribs, and annular teeth made of an abradable material and which extend radially towards the rotor, so as to provide sealing. The system may be used in a method for manufacturing a bypass turbojet engine compressor.

Abstract: A method for manufacturing a component of an axial turbine engine includes the following steps: (a) providing or producing a component with a temporary surface; (b) placing the component in a chamber containing particles; and (c) vibratory peening of the temporary surface using the particles. The chamber includes an abrasive paste mixed with the particles so as to polish the surface of the component during the peening step (c). Thus, at the end of the peening step (c), the surface becomes a polished surface with a surface compression stress or prestress. The present application is notably applicable to a one-piece bladed drum of an aircraft turbojet engine low-pressure compressor.

Abstract: The invention relates to a mold for injecting a layer of abradable material, such as silicone, inside an inner shroud of an axial-flow turbomachine. The mold comprises a circular wall or tubular wall extending axially and two annular walls extending radially outwardly from the axial ends of the axial wall. Each radial wall of the mold comprises an annular hook in contact with the outer surface of the shroud so as to hold the mold against the shroud. The injection pressure presses the hooks against the shroud, providing a seal. The walls form an annular molding cavity inside the inner shroud in combination with the inner shroud. The invention also relates to a method for molding an abradable layer inside the shroud with the aid of the mold. The latter is deformed by spreading apart the hooks so as to fit over the shroud.

Abstract: The present application relates to an axial turbomachine gaseous flow-guiding element, such as a compressor inner shroud or vane. The element includes a plasma generator including: a layer of dielectric material with a guiding surface in contact with the gaseous flow, a first electrode placed in the guiding surface, and a second electrode electrically isolated from the first electrode by means of the dielectric layer. The plasma generator drives the gaseous flow along the guiding surface from the first electrode to the second electrode and includes a third electrode covered by the dielectric layer and electrically connected to the second electrode, so as to participate in the generation of the plasma in combination with the first electrode and the second electrode, the second electrode being closer to the guiding surface than the third electrode.

Abstract: The present application relates to a rotor of a compressor or axial turbomachine comprising a vibration-damping system equipped with piezoelectric transducers distributed circularly and connected to dissipative resonant electric circuits. The circuits are closed and are equipped with a resistor and a coil. The piezoelectric transducers are divided into two sets of alternated transducers, each set being connected to a passive RLC circuit. In order to ensure a pooling of capacitances and currents thereof, the piezoelectric transducers are connected in parallel. During operation, the rotor is subjected to a turning excitation and is likely to vibrate and to deform in accordance with a modal shape with diameters with orthogonal deformation waves. The number of transducers is equal to the quadruple of the number of diameters of the mode, so as to be able to utilize the symmetrical character of this mode with diameters.

Abstract: The invention relates to an axial-flow turbomachine blading comprising a semi-circular row of blades extending radially. Each blade comprises a airfoil and lateral branches or lateral legs. Each branch has an end joined to the airfoil and an end opposite the airfoil. The blading comprises a first shroud segment connected to at least two opposite ends of two adjacent branches of two adjacent blades and/or of the same blade so as to connect the airfoils to the shroud segment via the lateral branches of the airfoils. The blading also comprises a second shroud segment concentric with the first shroud segment. The segments are connected to one another via the airfoils and the branches. The blading forms a rigid casing and is provided by additive manufacturing with a titanium-based powder.

Abstract: A system for measuring turbulence of a flow of a turbine engine, notably of a turbine engine compressor includes a first housing with a first pressure sensor and a first inlet, a second housing with a second pressure sensor and a second inlet inclined relative to the first inlet, and a temperature sensor. The system is configured to calculate at least two orientation components of the velocity of the flow on the basis of the pressure sensors and the temperature sensor. The inlets are disposed at the vane foot, on the leading edge at the level of an internal shell.

Abstract: An oil tank of a turbine engine, particularly of an aircraft turbojet includes an external wall forming a generally curved main cavity. This cavity includes an arched sensor for electrically measuring the oil level, for example in a capacitive manner. Said arched sensor matches the curvature of the main cavity in order to be integrated therein. Sensor supporting arms distributed along the curvature of the arched sensor and/or an arched sleeve with an arched cavity receive the arched sensor. A turbine engine is provided with an oil tank, as well as a method for mounting a sensor in an oil tank.

Abstract: The present application relates to a segmented inner shroud of a low-pressure compressor for an axial-flow turbine engine. The shroud includes an axial tubular wall, and a row of apertures formed in the axial wall. Each aperture has opposing edges situated to either side of a stator vane positioned in the aperture for the purpose of its attachment. The axial wall includes a radial flange which passes through the apertures in the circumferential direction of the shroud, so as to form a mechanical link between the opposing edges of the apertures. This mechanical seal permits the opposing edges to be joined together through each aperture, which improves the rigidity and the sealing. The shroud exhibits an E-shaped profile forming a sandwich structure with the annular sealing fins of the rotor, or sealing lips. The present application also relates to a method for the assembly of stator vanes abutting radially against the transverse radial flange.

Abstract: A method for selecting a milling cutter, which method makes it possible to select a milling cutter on the basis of a part to be machined such that the cutting force is constant while the part is being machined.

Abstract: A corrosion-resistant abradable covering to adhesively bond to a wear portion of a structural part, the covering including at least a polyester-based matrix and an aluminum alloy filler that are molded together.

Abstract: The invention relates to a test bench for an axial turbine engine, especially for a turbojet, including: a chamber intended to accommodate the turbine engine; a vertical inlet channel connected to the chamber upstream of the turbine engine; and a vertical outlet channel connected to the chamber downstream of the turbine engine; at least one wind power engine capable of converting the kinetic energy of a portion of the gas stream generated by the turbine engine into mechanical energy; the wind power engine or at least one of the wind power engines is situated in the vertical inlet channel and/or the vertical outlet channel. The invention also relates to a process for recovering energy of such a test bench.