Abstract: An evaluation system for evaluating a flow rate of a fluid coming from a tank, the system including measurement device suitable for measuring a fluid level in the tank and including estimation device for estimating the flow rate of the fluid using an unscented Kalman filter, the estimation device including an obtaining device for obtaining the raw fluid flow rate and correction device connected to the obtaining device and to the measurement device and configured to correct the raw flow rate as obtained by the obtaining device as a function of the level measured by the measurement device. A method performed by such a system.

Abstract: A method for manufacturing a strip of impregnated anodized aluminum, for use in a coil of an electrotechnical component, said coil including an interstitial material providing dielectric cohesion and insulation functions, said interstitial material being suitable for cross-linking, in other words for forming, by chemical reactions between the components thereof when subjected to certain physical conditions, molecular structures being organized in a lattice, the method comprising: a step of applying the precursor mixture of said interstitial material to the anodized aluminum; at least one step of cross-linking the precursor mixture in order to form said interstitial material on the strip of aluminum; wherein the anodized aluminum has not been subjected to the sealing of the pores of the alumina formed by anodization prior to the application of the precursor mixture of said interstitial material.

Abstract: The invention relates to a method for manufacturing an abradable plate (32) for a turbomachine turbine shroud (24, 26), the method comprising preparing a mixture comprising a cobalt- or nickel-based metal powder and a powder based on a fluxing element, depositing a layer of the powder mixture in a mold, and making the abradable plate (32) by subjecting the powder mixture layer to a method of SPS sintering. The invention also provides a method of preparing a turbine shroud (24, 26) for a turbomachine.

Abstract: A guide vane arranged in an air flow from a fan of an twin-spool aircraft engine, the aerodynamic part of the vane including an internal lubricant cooling passage partly delimited by an extrados wall and an extrados wall of the vane. The passage is equipped with a heat conduction matrix compressed between the walls and separating a first lubricant circulation space from a second lubricant circulation space. Furthermore, the matrix defines firstly first contact elements of the intrados wall formed in the first space and between which the lubricant from the first space will circulate, and secondly second contact elements of the extrados wall formed in the second space and between which the lubricant from the first space will circulate.

Abstract: A pressurized air supply unit (1; 1?) for an aircraft, comprising: a load compressor (30; 30?) configured to supply pressurized air (3), the load compressor (30; 30?) having a compressor shaft (23; 23?); and a drive portion (10) configured to supply power via an output shaft (20); the pressurized air supply unit (1; 1) being characterized in that it comprises: a gearbox (50); an electric motor (40), the electric motor (40) being coupled to said compressor shaft (23; 23?) via the gearbox (50); and a coupling system (25) configured to enable the output shaft (20) to drive the compressor shaft (23; 23?) and to prevent the compressor shaft (23; 23?) from driving the output shaft (20), and in that the output shaft (20) and the compressor shaft (23) lie on the same axis.

Abstract: The invention proposes an assembly for a rear of a dual-flow turbomachine (10) having a longitudinal axis (X), comprising: a secondary nozzle (110) defined about the longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary vein (Vs) and a primary vein (Vp) of the turbomachine (10), the secondary nozzle being of convergent-divergent form with a neck (112) corresponding to a minimal cross-cross-section of the secondary nozzle (110), a heating system located on at least one portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck and/or upstream from the neck (112).

Abstract: A method of characterizing a bundle (1) of electrical cables (2, 3, 4, . . . ), comprising taking into consideration for at least one surface temperature of the cables (Tsurface), firstly of at least one sum of heat fluxes (?1, ?2, . . . , ?n) calculated for each cable (2, 3, 4, . . . ) for the heating effect due to the electrical resistance of each cable passing a respective electric current (i1, i2, . . . , in), and secondly of a heat flux (?s) calculated for the heat given off by the bundle (1) into its environment in order to make the dimensioning of the cables (2, 3, 4, . . . ) compatible with their use.

Abstract: A drive mechanism is provided for driving at least two adjusting members used to adjust the orientation of the blades of a turbomachine rectifier vane associated therewith, where the drive mechanism simultaneously drives the displacement of at least two adjusting members in the turbomachine. A single threaded rod drives several levers, each lever being associated with an adjusting member. A first part of each lever engages with the threaded rod and one end of an arm of the lever is connected to the adjusting member associated therewith so that the rotation of the threaded rod causes a simultaneous rotation of the levers associated with the adjusting members.

Abstract: A test cell for an aircraft turbojet, wherein the test cell comprises a U-shaped configuration, with a passageway in the form of an elongated corridor, an inlet chimney, and an outlet chimney. The corridor includes a securing area with a securing arm for holding the turbojet during its test. The passageway furthermore reveals an upstream shutter and a downstream shutter, the two shutters including one pivoting flap or a series of pivoting flaps. In the event of a fire, the shutters close due to autonomous return means. Gravity allows the flap(s) to come down to the closed position and to confine the turbojet in order to rapidly stifle the fire.

Abstract: A turbine blade including an airfoil (31) extending above a platform (32) and a root (33) extending below the platform, the root of the blade having the form of a radially extending arm (34), being produced from composite material and including at least one cylindrical face (34). The direction of the generatrices which are oriented in the direction of the platform to allow a clamping piece (5) to slide towards the latter on the cylindrical face under the action of centrifugal force. The arm includes, at its lower end, a protuberance (35) forming a radial bearing point for engagement with an element for retaining the blade on a turbine disc (1). The root (33) is located entirely on the side of the protuberance with respect to the face.

Abstract: Seat assemblies including seat brackets and spreader brackets are described. A seat bracket can include an upper portion, a lower portion, and a frangible portion. The frangible portion can be formed from composite material and include a particular layer orientation. A spreader bracket can include a first component configured to couple with a second component to form a coupled structure. A structural fill material can be disposed within the coupled structure. The first component and the second component can be formed from composite material.

Abstract: The invention relates to a tab (5) for a sealing gasket device of a part of an aircraft gas turbine engine. The tab is arranged in respective slots of adjacent sectorized parts of the turbine engine nozzle. This tab has two bulging ends (51a, 51b) joined by a thinner intermediate part (51c) each having a connection with the other (53a, 53b), which can deform into a flat position by bracing the tab, when excess pressure is applied to its intermediate part from one side of the tab.

Abstract: The invention relates to guide tooling (22) for a circular needling table for needling a textile structure made from a helical fiber sheet, the tooling comprising an inner guide rail (24) of circularly arcuate shape, and an outer guide rail (26) of circularly arcuate shape arranged coaxially around the inner guide rail and connected thereto by radial reinforcement (28), the outer and inner guide rails defining between them a passage for guiding the helical fiber sheet under a needling head, the outer guide rail being made up of two outer guide rail angular sectors (26a, 26b) that are connected to each other by an outer actuator (28), the outer actuator being suitable for moving the adjacent free ends (26a-1, 26b-1) of the outer guide rail angular sectors apart from each other so as to expand the outer guide rail.

Abstract: A turbomachine blade that includes an airfoil that includes an intrados wall, an extrados wall, a leading edge, a trailing edge, an internal cavity and a plurality of cooling holes made in the walls and leading and trailing edges, each cooling hole connecting the internal cavity to the exterior, one end of each cooling hole opening up into the cavity, the other end of each cooling hole opening to the exterior through an outlet, wherein the cooling holes are distributed in at least one first alignment and a second alignment made in a wall of the airfoil, wherein this outlet of at least one of the cooling holes belonging to at least the second alignment is an oblong shape with its long dimension along the principal direction of said second alignment.

Abstract: A method for measuring a thrust margin of a turbomachine, in which data are acquired including the thrust margin which is determined as a function of a specified thrust and a measured thrust, the measured thrust being determined on a measuring bench which includes a bench equipment and on which the turbomachine is, wherein a time evolution of the thrust margin is modelled by at least one linear or affine function which is calculated for at least one determined time interval of the thrust margin, at least one bias of the bench equipment is calculated relative to at least one linear or affine function having been calculated, the thrust margin is corrected by subtracting from it at least one bias of the bench equipment in at least one determined time interval.

Abstract: The invention provides a method of forming an annular textile preform by needling a helical fiber sheet, the method comprising in succession: unwinding a helical fiber sheet (8) from a horizontal sheet-forming turntable (6) driven at a constant and predefined speed of rotation NFS onto a horizontal intermediate unwinder (24) driven at a speed of rotation NDI and positioned on a horizontal intermediate turntable (22) driven at a speed of rotation NFI, unwinding the helical fiber sheet from the intermediate unwinder onto a final horizontal unwinder (12) driven at a speed of rotation NDF, and unwinding the fiber sheet from the final unwinder onto a horizontal preform-forming turntable (18) driven at a variable and predefined speed of rotation NFP so as to be subjected to needling thereon, the speeds NDI, NFI, and NDF being controlled in such a manner that NDF is proportional to NFP, NFI=(NFS?NDF)/2, and NDI=(NFS+NDF)/2.

Abstract: A stator ring of a flow path, preferably secondary, of a turbomachine, the ring including an inner platform and an outer platform, a plurality of stators extending radially between the two platforms, in which at least one of the two platforms includes a plurality of integrated platforms, each one of the integrated platforms being integral with one of the stators, and the integrated platforms are all of the same shape as one another, and a plurality of attached platforms, each one of the attached platforms being in the form of a part that is assembled and arranged between two integrated platforms, and the attached platforms are also all of the same shape as one another.

Abstract: Method for collaborative observation between a local targeting device and a distant targeting device located at different geographical positions and able to acquire images, respectively referred to as local images and distant images, the method comprising, when it is implemented by the local targeting device, an execution of a procedure for determining a position of an observed object, referred to as the local targeted object, comprising an application (403) of a method for matching points of interest representing a distant image obtained (400, 401) from the distant targeting device with points of interest (402) determined on a local image by the local targeting device.

Abstract: An outlet guide vane for a turbine engine, the vane having a plurality of vane sections stacked along a radial axis Z. Over a bottom portion of the vane in the range 0 to 50% of its total height, the leading edge of each section is in front of the leading edge of the corresponding section at the total height, and the maximum thicknesses are located at positions that are offset from the leading edge by at least 50% of the chord.

Abstract: A shock absorber assembly for a non-streamlined blower includes an extension collar having a first interface suitable for being rigidly attached on a first module of the blower; a connector support housing including a third interface suitable for being rigidly attached on a second module of the blower; and a fourth interface allowing a mechanical connection to be made between the housing and a second interface of the collar; a plurality of elastic devices arranged between the collar and the housing; a flange element rigidly attached on the third interface of the housing comprising a stop bearing on the collar in such a way as to define a space between the collar and the flange element; the elastic means are arranged so that a residual clearance exists between the flange element and the housing.