Abstract: A method for deburring an aeronautical part with an articulated tooling including a plurality of axes of rotation, the aeronautical part including at least one edge to be deburred, the articulated tooling including a tool holder, holding a calibration tool and a machining tool, the calibration tool and the machining tool being fixed to the tool holder and being immovable relative to one another, the method including steps of calibrating the calibration tool and the machining tool, of parameterizing the aeronautical part, of deburring the at least one edge to be deburred with the machining tool moving along a predetermined trajectory, on the basis of the parameters obtained during the parameterization step.

Abstract: A de-icing device for an air intake of an aircraft jet engine nacelle extending along an axis in which a flow of air flows from upstream to downstream, the intake comprising an inner wall and an outer wall connected by a leading edge, the inner wall comprising a plurality of blowing lines, each blowing line comprising a plurality of through-openings configured to blow elementary streams from the hot air source in order to de-ice said inner wall, the blowing lines being parallel to one another in a cylindrical projection plane, each blowing line having a depth defined along the axis X and a length defined along the axis Y in the cylindrical projection plane, two adjacent blowing lines being spaced apart by a distance, the ratio of the distances L3/D3 being between 1 and 2.

Abstract: A fibrous texture intended to form the fibrous reinforcement of a turbomachine blade made of composite material including a fibrous reinforcement densified by a matrix, wherein the fibrous texture includes an area of reduced stiffness including warp yarns or strands made of second fibers having a second elongation at break greater than the first elongation at break, the area of reduced stiffness extending in the longitudinal direction from the stilt area and up to a height less than or equal to 30% of the height of the blade, extending in the transverse direction between a first area and a second area, the first area extending over a first length from a first edge of the texture intended to form a leading edge, and the second area extending over a second length from a second edge of the texture intended to form a trailing edge.

Abstract: A turbomachine rotor blade includes plural blade sections stacked along an axis between a blade root and a blade head defining between the blade root and the blade head the height of the blade, each blade section including a chord and a maximum sweep defined by the maximum length of a segment perpendicular to the chord line and connecting a point of the chord line and a point of a camber line formed of all points located equidistant from the extrados and the intrados in the section, and verifying that the ratio between the maximum sweep and the chord at mid-height of the blade and the same blade head ratio is between 25% and 40% of the ratio between a maximum sweep and a blade root chord.

Abstract: An assembly for a turbomachine through which an air flow passes, includes a stator including guide vanes extending radially in relation to a longitudinal axis, at least one inter-vane platform extending between the radially outer ends of two circumferentially consecutive guide vanes, each inter-vane platform including an outer surface that faces the axis, a heat exchanger located downstream of the stator in relation to a direction of circulation of the air flow in the turbomachine during operation, this stator including a heat exchange surface extending in the extension of an inter-vane platform. At least one inter-vane platform located in the upstream extension of the heat exchange surface is provided with at least one turbulence generator on its outer surface.

Abstract: An aircraft seat includes an actuator and a movement transmission device. The transmission device includes a frame provided with an immobilizing portion and a drive shaft. The transmission device further includes a gear wheel provided with coupling teeth having inclined side walls and a sleeve with an immobilizing portion complementary to the immobilizing portion of the frame, and coupling teeth having inclined side walls. The transmission device also has an elastic member configured to push the sleeve. The stiffness of the elastic member and the inclination of the side walls of the coupling teeth of the gear wheel and sleeve are chosen such that, when a torque greater than a threshold torque is applied to the gear wheel, the sleeve slides on the drive shaft from a position of coupling the sleeve to the gear wheel to a position of immobilizing the sleeve relative to the frame.

Abstract: The invention relates to a method (1) for monitoring a rotating machine (100) of an aircraft, wherein a measurement signal is acquired from the rotating machine. According to the invention, instantaneous frequencies (fK(t)) of sinusoidal components of the measurement signal are estimated, and, using a computing module (12), a plurality of successive iterations are carried out in each of which: complex envelopes of the components are updated (C1), parameters of a model of a noise of the signal are updated (C21) on the basis of the envelopes, whether the model has converged from the preceding iteration to the present iteration is tested (C4), with a view to: o if not, carrying out a new iteration, o if so, performing a computation (D) of the complex envelopes on the basis of the iterations that have been carried out.

Abstract: A method for treating an aromatic mineral oil or a mixture of aromatic mineral oil and naphthenic mineral oil, the oil or the mixture of oils being loaded with polycyclic aromatic hydrocarbons, the method including a—optional removal of polycyclic aromatic hydrocarbon s having a molecular weight greater than or equal to 200 from the aromatic mineral oil or the mixture of aromatic mineral oil and naphthenic mineral oil loaded with polycyclic aromatic hydrocarbons; b—extraction, at a pressure lower than atmospheric pressure, of polycyclic aromatic hydrocarbons having a molecular weight lower than 200 solubilised in the oil or the mixture of oils obtained in step (a); and c—recovery of the oil or the mixture of oils depleted in polycyclic aromatic hydrocarbons.

Abstract: A fibrous preform obtained by three-dimensional weaving, comprising a first skin, a second skin, and a central portion connecting them and forming a stiffening element. In a transverse plane, transverse threads of the first skin and the second skin are woven in pairs in the first skin and the second skin on either side of the central portion; the threads of a first pair of the first skin and of a second pair of the second skin are separated into two unitary threads at the central portion by being woven with longitudinal threads, and a thread of the first pair crosses a thread of the second pair at least twice in the central portion.

Abstract: The present invention relates to a bypass air/fluid heat exchanger (2) for a turbofan engine. According to the invention, this exchanger (2) comprises: —an annular outer shroud (3) with two walls, an inner wall (32) and an outer wall (31), —an annular inner shroud (4) concentric with the outer shroud (3), —a series of OGV guide vanes (5) which connect said outer shroud to said inner shroud, —and a circulation circuit (6) for circulating said fluid, the two shrouds delimiting a bypass air flow path, the fluid circulation circuit (6) is formed in the body of the outer shroud (3) and in the body of at least one of the OGV guide vanes (5), this circulation circuit (6) opening at the two respective ends thereof into an inlet opening (34) and into an outlet opening (35), formed through said outer wall (31) of the outer shroud, and the two shrouds (3, 4), the OGV guide vanes (5) and the circulation circuit (6) of said fluid are integral.

Abstract: Method for manufacturing a CMC, i.e. ceramic matrix composite material, part provided with at least one cutout, as well as to such a CMC part provided with at least one cutout, the method comprising the following steps: providing (E1) a fibrous reinforcement (10), forming (E2?) a cavity in a portion of the fibrous reinforcement (10), injecting (E3) a slip comprising at least a ceramic powder and a solvent, the slip being injected so as to impregnate the fibrous reinforcement (10?) and to fill the cavity of the fibrous reinforcement (10?), drying (E4) the obtained assembly, carrying out a densification (E6) by infiltration of a liquid densification material and solidification of said densification material, machining (E7) at least one cutout in the obtained blank (30) within the volume corresponding to the cavity of the fibrous reinforcement (10).

Abstract: A turbomachine turbine blade, includes a platform, a vane, a cooling cavity supplying a plurality of cooling outlets provided along the trailing edge, two radially adjacent cooling outlets defining therebetween a rib. At least one cooling hole is formed in the thickness of at least one rib and/or in the thickness of a portion of the trailing edge fillet located in the axial extension of at least one rib, so as to ensure fluid communication for a cooling flow between the inside and the outside of the blade for cooling the at least one rib.

Abstract: The invention relates to an epicyclic reduction gear for a turbomachine, including a sun wheel that is rotatable about a first axis (A); a ring gear surrounding the sun wheel and being rotatable about the first axis (A); at least one planetary gear that is rotatable about a second axis (B), the planetary gear being meshed with the sun wheel and the ring gear; an immobile planet carrier, the planetary gear being rotatably guided about the second axis (B) with respect to a bearing of the planet carrier; an item of equipment including a rotor. The invention is characterized in that the item of equipment is fastened to the bearing of the planet carrier and the rotor of the item of equipment is rotatably driven by the planetary gear.

Abstract: The invention relates to a module of a turbomachine of longitudinal axis X, the module comprising: ?—a rotary casing (31) that rotates about the longitudinal axis and bears a propeller (2; 20, 21, 22) which is provided with a plurality of blades (32); ?—a fixed casing (48) comprising a cylindrical wall (49) extending between an inner wall (40) and an outer wall (41) of the rotary casing (31); and, ?—a system (30) for changing the pitch of the blades of the propeller, mounted around the fixed casing and comprising: a control means (55) comprising a movable body (57) that is able to move axially on said fixed casing, at least one load transfer bearing (56) comprising an inner ring (65) that is connected to the movable body (57), and an outer ring (66); and a connection mechanism (61) for connecting the outer ring (66) to the blades of the propeller.

Abstract: An annular heat exchanger for a turbomachine, is intended, for example, to be supported by an annular ferrule of a housing of the turbomachine, and includes an annular one-piece part having a first fluid circuit having at least one first conduit and at least one second conduit extending in an annular manner. The first conduit and the second conduit lead into a first cavity formed on a first circumferential end of said annular part, and the heat exchanger includes detachable sealing means which are applied to said first end and designed to allow a flow of fluid from the second conduit into the first cavity then into the first conduit.

Abstract: An aircraft turbine engine includes a gas generator having a longitudinal axis (A), a fan which is located at an upstream end of the gas generator and which is configured to rotate about the axis, and an electric machine which has a generally annular shape. The electric machine is mounted coaxially downstream of the fan and has a rotor which is coupled in terms of rotation to the fan, and a stator which is connected to an electronic power circuit by at least one rigid electroconductive bar.

Abstract: A distribution element intended to be fixed to a support structure for supplying cooling fluid to a wall to be cooled facing the distribution element, the distribution element including a body defining a cooling fluid distribution internal volume and a multi-perforated plate which delimits the internal volume and includes a plurality of outlet through-perforations which put the cooling fluid distribution internal volume into communication with the wall to be cooled, the distribution element including an inlet orifice opening into the cooling fluid distribution internal volume, wherein for directing the cooling fluid from the inlet orifice to the plurality of outlet through-perforations the cooling fluid distribution internal volume includes directional fins.

Abstract: Fuel pump for an aircraft engine, comprising an inducer and a centrifugal impeller fixed together and having an axis of rotation, an annular space spacing axially the inducer and the impeller, and two contact portions between the inducer and the impeller disposed radially outside the annular space, a first plenum chamber and a second plenum chamber, in which the inducer and the impeller are spaced axially from each other, each being disposed between the two contact portions, the plenum chambers being symmetrical to each other with respect to the axis of rotation and in fluid communication with the annular space, the centrifugal impeller comprising a plurality of axial balancing holes distributed about the axis of rotation and opening out into the annular space at one end, and into a downstream space of the impeller at the other end.

Abstract: A method for manufacturing a part made of composite material includes forming a ceramic matrix phase in pores of a fibrous preform by pyrolysis of a cross-linked copolymer ceramic precursor, the cross-linked copolymer including a first precursor macromolecular chain of a first ceramic having free carbon, and a second precursor macromolecular chain of a second ceramic having free silicon, the first macromolecular chain being bonded to the second macromolecular chain by cross-linking bridges including a bonding structure of formula *1—X—*2; in this formula, X designates boron or aluminium, -*1 designates the bond to the first macromolecular chain and -*2 the bond to the second macromolecular chain.

Abstract: The present invention concerns a method for monitoring an actuating system of a movable component, in particular a movable component of a turbomachine such as a nozzle or a blade, the actuating system comprising a control device configured to deliver a position instruction to a first cylinder and a second cylinder, each cylinder being configured to deliver a position feedback measurement in response to the position instruction, the method being implemented in a monitoring system and comprising, —a first monitoring mode in which the deviations between the position feedback measurements of the two cylinders are detected; —a second monitoring mode in which the deviations between the position feedback measurements of the two cylinders are not detected; method in which the second mode is selected when at least one of the two position feedback measurements is in a transient phase.