Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: An electrothermally actuated microelectromechanical and/or nanoelectromechanical structure including a stationary portion, at least one portion which is movable relative to the stationary portion, at least one electrothermal actuation beam which makes it possible to cause an electric current to flow from the stationary portion to the movable portion, is mechanically connected to the movable portion and is intended to move the movable portion relative to the stationary portion by electrothermal actuation, and at least one electrically conductive connection element electrically connecting the movable portion to the stationary portion, the actuation beam having a thickness of no greater than half one thickness of the movable portion and no greater than half one thickness of the connection element.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y, Zadim given in Table 1, in which the coordinate Zadim is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: An aircraft engine-part including at least a metal substrate and a protective coating for protection against erosion that is present on the substrate, the coating including at least one phase including at least chromium at an atom content greater than or equal to 45% and carbon at an atom content lying in the range 5% to 20%, the phase including Cr7C3 and Cr23C6 chromium carbides. A method of fabricating such a part in which electroplating is used to deposit a coating composition on the part and the part is subjected to heat treatment at a temperature lying in the range 250° C to 70° C.

Abstract: A method of identifying and/or tracking deformation of a mechanical part made of composite material for a turbine engine, in which the part includes a preform of fiber material and a resin, is provided. The method includes incorporating metal particles in the preform or the resin during fabrication of the part, and subjecting the mechanical part to two X-ray inspections on two different occasions so as to identify the part and/or so as to deduce deformation of its internal structure.

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: A method of creating a database of operating states of an aircraft fleet, in which a computer executes the steps of acquiring parameters wherein a state of operation of an aircraft of the aircraft fleet; acquiring at least one item of degradation information indicative of a level of degradation of at least one aircraft from among the fleet of aircraft; storing series of parameters in said database, each series of parameters including parameters wherein a state of operation of one of the aircraft and if the item of degradation information has been acquired, at least one item of degradation information indicative of a level of degradation of the aircraft.

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 fan disk is for a jet engine in which there flows a gas stream in a flow direction. A pin-shaped radial section of the fan disk includes a first branch, designed to be fixed to a drive shaft of the jet engine, a second branch, extending opposite the first branch and designed to support a plurality of fan blades, and a curved junction wall that extends between the first branch and the second branch.

Abstract: A device to test the peeling resistance of coupons, each formed of a support and an adhesive, includes: (i) a frame including rollers with parallel axes designed to maintain the coupon supported while guiding movement of the latter, (ii) a traction device including a vertical jack linked to an attachment element including a loop configured in order to cause detachment of the adhesive from the surface of the support, (iii) a device for measuring the force exerted by the jack in order to pull the loop during peeling, and (iv) a coupon, complex in shape, such as one derived from a reinforced vane. At least one roller is translationally adjustable in relation to other rollers and the coupon is specially prepared in order to facilitate carrying out the tests.

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: A decamouflaging method includes: obtaining image representing a scene including a multispectral image including components in the spectral domain ranging from the visible domain to the short-wavelength infrared and a thermal image including a component in the medium infrared and/or the long-wavelength infrared; extracting a sub-part (“window”) from each of the images obtained at a given position; applying a contrast accentuation procedure to the window extracted from the multispectral image allowing an improved window to be obtained where contrast between pixels corresponding to the object and pixels not corresponding to the object is accentuated; forming a multicomponent window, the improved window obtained and the window extracted from the thermal image each supplying a component of the multicomponent window; and applying the procedure to the multicomponent window; generating an image by inserting the improved window obtained by applying the procedure to the multicomponent window in a receiving image repre

Abstract: A method for making an aerodynamic element, particularly for an aircraft, including an external face and a plurality of parallel ribs and/or grooves formed on the external face, the method including making the element and its ribs and/or its grooves simultaneously with a mold, including a step to supply a film made of a deformable material that includes ribs and/or grooves complementary to the ribs and/or grooves of the element, a step to position the film on a wall of the mold, a step in which the element is molded, a step in which the element is separated from the mold simultaneously with the film, and a step in which the film is separated from the element.

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: A method and device for monitoring an electrical network, including: a mechanism detecting electrical signals and additional signals produced in the electrical network, the additional signals being of a different physical nature to the electrical signals; a mechanism for processing the electrical signals to define a first time reference representing a detection time of the electrical signals emitted upon a fault event arising in the electrical network; a mechanism processing the additional signals to define a second time reference representing a detection time of the additional signals emitted upon the fault event arising in the electrical network; and a processor spatially locating the fault event in the electrical network according to the first and second time references.

Abstract: A titanium-based intermetallic alloy includes, in atomic percent, 16% to 26% Al, 18% to 28% Nb, 0% to 3% of a metal M selected from Mo, W, Hf, and V, 0.1% to 2% of Si, 0% to 2% of Ta, 1% to 4% of Zr, with the condition Fe+Ni?400 ppm, the balance being Ti, the alloy also presenting an Al/Nb ratio in atomic percent lying in the range 1.05 to 1.15.

Abstract: A composite reinforcement insert includes a strand formed by a central fiber made of ceramic material surrounded by filaments of metal alloy helically wound around the central fiber, and a metal reinforcement layer covering the strand.

Abstract: An unducted fan for an aircraft turbine engine, including a propeller having a hub and an annular array of blades extending substantially radially outwards from the hub, is provided. The hub includes an annular array of cowls, each of which is mounted between the radially inner ends of the blades and suitable for being fixed to an upstream collar and to a downstream collar of the hub. At least one cowl includes, at a circumferential end, a joint edge which is contiguous with a complementary joint edge of an adjacent cowl. The at least one cowl and at least one of the upstream and downstream collars are configured so that the cowl can be mounted and dismounted by a movement including a pivoting about an initial pivot axis circumferentially separated from the at least one joint edge.