Abstract: A sealing system for at least one floatingly mounted ring in a support for a rotary shaft rotatable about an axis directed along a longitudinal direction provides dynamic sealing between the shaft and the support. The system includes a coupling part interposed between the ring and the support, whereby the ring is secured to the support. A first cylindrical type joint directed with respect to a first transverse direction provides a joint between the support and the coupling part. A second cylindrical type joint directed with respect to a second transverse direction perpendicular to the first transverse direction provides a joint between the ring and the coupling part. A turbopump includes such rotary shafts and sealing systems.

Abstract: A monitoring method and system for a test bench for at least one engine component, including: an acquisition mechanism to acquire time signal packets corresponding to measurements of endogenic and exogenic parameters specific to the combination of the test bench and the engine component, at successive instants; and a processor to construct an endogenic indicator vector and an associated exogenic indicator factor at each instant of the successive instants, using time signal packets earlier than the instant, to identify a context class for the exogenic indicator vector, and to calculate a risk probability of the endogenic indicator vector conditioned by the identified context class for the associated exogenic indicator vector using at least one anomaly detector, to produce a diagnostic of a state of the test bench and engine component combination.

Abstract: The present application proposes an axial turbomachine compressor comprising a rotor with at least one annular row of rotor blades, a stator casing surrounding the row of rotor blades, the casing including a device for generating counter-vortexes. During operation of the compressor, the movement of the blades creates leakage vortexes at the blade tip. The generating device in turn injects counter-vortexes rotating in the opposite direction to the leakage vortexes in order to counter the leakage vortexes. This improves the surge margin of the compressor. The present application also provides a method for controlling the stability of a turbomachine compressor by counter-vortex injection.

Abstract: A stator designed to be placed radially in a flow which passes through one or more rotors which share the same axis of rotation, with a leading edge and a trailing edge. The leading edge and trailing edge are connected by a lower face and an upper face, wherein at least one of the faces of the stator has radial undulations which extend axially from the leading edge to the trailing edge. The radial undulations can have at least two bosses in the same azimuth direction, the amplitude of which is at least one centimeter on at least part of the axial length of the stator. A propulsion assembly formed by the rotor and the stator, and to a turbine engine comprising such assembly is also provided.

Abstract: An aircraft turbomachine calculator including a parallelepiped metal casing including an electronic circuit wherein a control channel and a monitoring channel are integrated. The casing includes a first cavity wherein a first electronic board is provided for managing the control channel and a second cavity, independent of the first cavity, wherein a second electronic board is provided for managing the monitoring channel, these electronic boards being provided in two planes oriented with respect to each other at an angle of 90°.

Abstract: A sized yarn for subjecting to a textile operation, the yarn including a plurality of ceramic and/or carbon fibers; an interphase coating covering the fibers; and a film covering the interphase coating and including a linear polysiloxane.

Abstract: A device for controlling variable-pitch turbomachine members such as stator vanes, wherein the movement of a control mechanism is imparted to a ring that rotates the levers for pivoting the vanes about a stator, and takes place with a possible change in the length of the bottle screw connecting the ring to the control mechanism, thereby allowing the blade pitch angle law to be changed according to the extension of the control device. A greater freedom of adjustment is thus obtained. The device can be useful when a single control mechanism is used for multiple rings arranged side by side, making it possible to have different control laws for the rings.

Abstract: A method of making a multi-vane model for a nozzle guide out of sacrificial material, includes the steps of fabricating a single-vane model out of sacrificial material, assembling at least two sacrificial material single-vane models with each other, and positioning (104, 108) a holder element on at least one sacrificial material single-vane model so as to hold a predetermined spacing between an inner platform and an outer platform. An assembly of a sacrificial material single-vane model for a nozzle guide together with a holder element, and also an assembly of a sacrificial material multi-vane model for a nozzle guide together with a holder element.

Abstract: An aircraft turbine engine includes a rotating body comprising a compressor rotor and a turbine rotor interconnected by a rotor shaft, the turbine engine being configured to drive a member by said rotor shaft via an epicyclic reduction gear, said epicyclic reduction gear comprising a first element (50) configured to be rotationally secured to said shaft, a second element (56) rotationally secured to said member, and a third element configured to be selectively secured to a stator of the turbine engine and disengaged from the stator, wherein the turbine engine comprises driving means to rotationally drive said third element at a piloted speed when it is disengaged from said stator.

Abstract: A field of test methods, and more particularly to a method for testing a device, the method including one operating stage corresponding to a stable value of one operating setpoint for the device and/or for a test bench for testing the device. The operating stage is finalized before a maximum duration threshold if a criterion associated with a set of physical parameters picked up during the operating stage is satisfied and if a confidence level associated with the set of physical parameters reaches at least a predetermined threshold.

Abstract: Ramp mounts may facilitate the movement of a passenger seat pan relative to a passenger seat frame during movement of the seat pan between an upright position and a recline position relative to the passenger seat frame. During cycling of the seat pan from the recline position to the upright position, ramp mounts may break. Embodiments of the ramp mount disclosed herein may increase the ramp mount durability so as to reduce the instances of ramp mounts breaking during cycling of the seat pan between the recline and upright positions. Additionally, some embodiments may provide for a ramp mount that has fewer components. Such embodiments may simplify coupling of the ramp mount to a seat pan and may reduce passenger seat system assembly time. Moreover, in some embodiments, the reduced number of components may further reduce manufacturing time and/or costs—thereby providing a relatively low cost ramp mount.

Abstract: A jet pump type ejector for a turbomachine, including a duct through which a secondary ventilation air flow passes, and a first end of which forms an air intake and a second end of which forms an air outlet, the two nozzles for spraying a primary air flow being mounted in the duct which defines a mixer and a diffuser downstream from the nozzle, the two nozzles being parallel and adjacent to one another, the mixer including two substantially planar longitudinal walls, bottom and top respectively, connected to one another by two side walls having a semicircular cross-section, in which the radius of curvature R2 is centered on the axis of a nozzle, the center-to-center distance of the nozzles being substantially equal to ?/2 times R2 or (?/2)R2.

Abstract: A method of synchronizing data for algorithms of asynchronous computers in an aircraft, the method comprising the steps consisting in: a) generating a sequencing table for each algorithm and, in said table, identifying the number of valid windows for each of which all of the parameters for input to the algorithm are updated at least once; b) distributing the load corresponding to updating the parameters for each algorithm in a send table; and c) instructing the first computer to use the send table.

Abstract: The present invention relates to an aircraft comprising a fuselage (1), a propulsion unit (7) at the rear tip of the fuselage and at least two engines (3, 5) each driving an engine shaft (32, 52), the propulsion unit including at least one propeller (71, 73) driven mechanically by the engine shafts (32, 52), characterized in that the propulsion unit (7) includes two propellers (71, 73), each of the propellers being driven by a propeller shaft (72, 74), the two propeller shafts being driven by the engine shafts (32, 52) via a first differential epicyclic gear train (40). Specifically, the input of the first differential gear train (40) is connected to the output of a second differential epicyclic gear train (60), the second differential gear train (60) including two inputs (61c2, 62c2), each of said two inputs being connected mechanically to one of said engine shafts (32, 52).

Abstract: A turbomachine part including at least first and second blades, and a platform from which the blades extend, wherein the platform has a non-axisymmetric surface limited by first and second end planes, and defined by at least three construction curves of class CI each representing the value of a radius of the surface on the basis of a position between the lower surface of the first blade and the upper surface of the second blade according to a plane substantially parallel to the end planes, including a first curve that increases in the vicinity of the second blade; a second curve that decreases in the vicinity of the second blade; a third curve having a minimum at the second blade.

Abstract: The invention relates to an assembly on an engine, which comprises a first and a second piece mounted so as to rotate relative to one another. A connecting device is provided between such pieces. It comprises a first annular part defining a flange fixed to the first piece a second annular part extending substantially parallel with the axis of rotation of the engine and studs connecting the first and second annular parts together. An interface for the rotational sliding about said axis is positioned between the second annular part and the second piece. The second annular part is sectorized.

Abstract: Compression assembly for a turbine engine, in particular a turboshaft engine, said assembly comprising an air inlet duct capable of receiving an air flow, at least one air compression stage comprising at least one movable compressor wheel onto which the duct discharges, and a pre-rotation grille which is positioned in the air inlet duct upstream of the movable compressor wheel in order to adjust the speed of the air in said flow at the inlet of the movable wheel and comprises a plurality of variable-setting vanes, the assembly being characterized in that the pitch between two consecutive vanes of the grille is greater than the chord of one of the two vanes at a given height of the air duct, preferably in its upper part.

Abstract: An equipment support including at least one attachment including an output shaft, an input gear wheel, the input gear wheel being both rotated by the motor shaft at a main speed and also connected to the output shaft of the attachment in order to rotate it at a determined output speed, an input shaft, rotated by the input gear wheel at a determined input speed, and a reducer with magnetic gears, arranged between the input shaft and the output shaft, such that the input speed is different from the output speed.

Abstract: The invention relates to a rotation sensor, comprising: —a stator (A) and rotor (B), arranged coaxially and forming a magnetic circuit (10, 20), the rotor being mounted angularly displaced with respect to the stator, —a primary winding, suitable for generating a magnetic field in the magnetic circuit, and —at least one secondary winding, characterized in that the magnetic circuit comprises at least one tooth (220) extending radially with respect to the axis (X-X) of the stator and of the rotor, and at least one notch (12) suitable for receiving said tooth, such that the tooth is separated from the notch by at least one tangential air gap (51) that is variable according to the angular displacement of the rotor with respect to the stator, the tooth and the notch being shaped so that, during a rotation of the rotor with respect to the stator, a variation in the width of the tangential air gap causes an increase or a decrease in the permeance of the air and, respectively, an increase or a decrease in the voltage

Abstract: A test bench comprising at least one accelerometer which is linked by rigid mechanical linking to a support and comprising a vibration chamber able to convert an electrical signal into a mechanical vibration disseminated to the support and to the accelerometer by rigid mechanical linking between an oscillating part of the vibration chamber and the support in such a way as to use the support as an acoustic amplifier and to excite the accelerometer according to a predetermined mechanical wave.