Abstract: The invention relates to an aircraft turbine engine (101) which comprises, downstream of the low pressure compressor of its low pressure body (104) and upstream of its combustion chamber (102), an electric motor (206) which is configured to rotate a rotor blade ring so as to generate a flow of air. Moreover, the rotational speed of the electric machine rotor is independent of the rotational speed of the compressor rotor.

Abstract: Electrical power supply circuit for a power module comprising an electrical transformer, a first substrate having a first side including a heat sink and a second side, a second substrate having a first side including a heat sink and a second side, first metal tracks disposed on the second side of the first substrate, second metal tracks disposed on the second side of the second substrate, electrical connectors disposed between the first and second substrates to electrically connect a first metal track to a second metal track, the primary circuit of the electrical transformer comprising a first part of the first metal tracks and a first part of the second metal tracks, and the secondary circuit of the electrical transformer comprising a second part of the first metal tracks and a second part of the second metal tracks.

Abstract: A method for controlling the speed of an engine assembly of an aircraft, including updating the speed setpoint of the engine assembly as a function of the current state-of-charge of an onboard energy storage device, and controlling the engine assembly according to the speed setpoint of the engine assembly, as well as a control device suitable for implementing this method and an engine assembly and an aircraft incorporating such a control device.

Abstract: A method for producing a component including a plurality of hollow complex elements, includes: filling a plurality of molding cavities with a thermoplastic material, the mold being maintained at a first temperature, applying a hold pressure to the thermoplastic material while the mold is cooled to a second temperature, and interrupting the hold pressure on the thermoplastic material while the mold is cooled to a third temperature.

Abstract: A method for forming an acoustic resonator panel for an aircraft propulsion assembly nacelle, the acoustic panel including cells with transverse internal obstacles in order to lengthen the path traveled by the sound waves. The method includes forming a perforated metal sheet, stacking a plurality of thermoplastic cellular cores and at least one perforated sheet, two successive cellular cores being separated by a perforated sheet, compacting the stack, and thermoplastic welding.

Abstract: A system for monitoring an aircraft engine, including an acquisition module for acquiring current measurements of physical quantities, referred to as input and output physical sizes, relative to the aircraft engine, a module for simulating the physical behavior of the aircraft engine, in order to simulate output physical quantities as a function of the current measurements of input physical sizes, a processor for calculating physical margins, referred to as actual physical margins, between the simulated values of output physical quantities and the corresponding current measurements of output physical quantities, a learning module for predicting margins, the margins being predicted using current measurements of input physical quantities and wherein the processor is configured to calculate surveillance residuals giving an indication of the state of the aircraft engine.

Abstract: This method (200) for producing a composite spacer ring for a turbine engine fan comprises preparing (210) an upstream skin preform, preparing (220) a downstream skin preform, preparing (230) an insert preform, inserting (251) the insert preform between the upstream skin preform and the downstream skin preform so as to form a rotating spacer ring preform, and baking (260) the rotating spacer ring preform. The preparation (210) of the upstream skin preform and/or the preparation (220) of the downstream skin preform comprises drape forming (212, 222) prepreg tows on a skin mold by means of automated fiber placement.

Abstract: A system for exchanging power in an aircraft includes voltage bus, a low-pressure and high-pressure electromechanical converters, and for each electromechanical converter, a voltage control module. The system further includes a computer providing a sharing setpoint between the exchanged powers, the sharing setpoint varying over time; and for at least one of the electromechanical converters: a module that ensures the sharing setpoint is observed. The module is configured to adjust the power that is exchanged by the relevant electromechanical converter in order to observe the received sharing setpoint, taking into account a received evaluation of the power exchanged by the other of the electromechanical converters.

Abstract: A method for controlling the speed of an engine assembly of an aircraft. The engine assembly includes at least a combustion engine and an electric machine mechanically coupled to the combustion engine and electrically connected to an onboard energy storage device of the aircraft. The method includes steps of comparing an electrical reserve required for engine assistance with an available electrical reserve, and controlling the speed of the engine assembly as a function of the difference between the electrical power reserve required for engine assistance and the available electrical power. A control device suitable for implementing this method, as well as the engine assembly and aircraft incorporating the control device.

Abstract: A method for monitoring the state of health of an aircraft turbomachine for a flight of interest VI, based on a setpoint vector XSC of input parameters relative to the turbomachine of interest in steady-state regime, the method using a database of values of input and output parameters in transient regime for a plurality of flights including the flight of interest, and values of input and output parameters in steady-state regime for a plurality of flights with the exception of the flight of interest. The transient data are used to estimate a transient prediction model f, at least one portion of the transient prediction model f then being used, associated with the steady-state data, in order to estimate a steady-state prediction model H of the turbomachine of interest for the flight of interest and to determine the behaviour, in steady-state regime, of the turbomachine for the flight of interest.

Abstract: A method for determining the presence of at least one defect in a three-dimensional part on the basis of a reference base, wherein: an image of the part is acquired by tomography; the image is segmented and the segmented image is registered with respect to the images of the reference base; the subdomains associated with the registered segmented image are determined; and for each subdomain of the registered segmented image, the following steps are carried out: registering the subdomain; breaking down the subdomain with respect to the principal modes of the reference base; generating a synthetic image of the subdomain from the breakdown, which is subtracted from the registered segmented image of the subdomain; and determining that a defect is present on the basis of the comparison of the value of each pixel of the residual image with a predetermined threshold.

Abstract: A method for producing a part, in particular a part made of composite material, in particular for a turbomachine, including at least: a step of producing a preform, during which a fibrous preform intended to form an outer skin of the part is produced; a step of producing a core, during which a rigid core, in particular a hollow rigid core, intended to form a framework of the part is produced; an insertion step, during which the rigid core is inserted into the fibrous preform, an injection step, during which a matrix is injected into the fibrous preform; and a heat-treatment step, during which polymerisation of the matrix is carried out.

Abstract: The invention relates to a stator part (20) comprising a platform (22), a blade (24, 26) that has a maximum camber (526), a fin (28) extending from a root (44) to a head (46), the head (46) extending from a leading edge (31) to a trailing edge (37), the fin (28) and the blade (24, 26) being arranged such that: —the maximum camber (526) lies between the leading edge (31) and the trailing edge (37); —a ratio of a distance between the maximum camber (526) and the leading edge (31) to a fin chord length (54) is between 5% and 95%; and—the fin head defines a recess (45) extending on either side of the maximum camber (526) over a recess length (47) that is less than or equal to 20% of the chord length (54).

Abstract: This invention relates to a method for monitoring a rotary machine (MAC) based on a vibration signal (SIG), the rotary machine (MAC) comprising a plurality of subsystems (SA-SB) of mechanical parts in rotation (LA1-LA2, LB1-LB2) and the vibration signal (SIG) comprising vibrational contributions of the subsystems (SA-SB), the method comprising, for at least one said subsystem (SA), steps consisting in: estimating (S210) the vibrational contribution of said subsystem (SA) from a set of synchronous averages of the vibration signal (SIG) associated with rotation frequencies (FA1-FA2) of the parts of said subsystem (SA) and with multiples of these rotation frequencies (FA1-FA2); determining (S310) whether or not said subsystem (SA) is faulty by comparative analysis of a so-called health indicator corresponding to the estimated vibrational contribution (SIGA) of said subsystem (SA).

Abstract: A heat exchange system, in particular for an aircraft turbine engine, includes an outer annular wall and an inner annular wall. A first annular heat exchange device is carried by one of the walls and includes a heat exchange matrix positioned between this wall and a cover. The system further includes a second annular heat exchange device which has a heat exchange matrix axially spaced apart from the heat exchange matrix of the first device and which is positioned between the cover of the first device and the opposite wall or another cover of the second device.

Abstract: A method for producing a nitrided steel part in which a semi-finished blank made of nitriding steel is produced from a blank or a steel bar and in which a reinforcing treatment is carried out on the semi-finished blank thus obtained, the method including a preliminary heat treatment in which the blank or steel bar from which said semi-finished blank is obtained is heat-treated beforehand. The preliminary heat treatment includes a hardening treatment by a heating which ensures austenitization of the steel and a tempering treatment at a temperature between 200° C. and 650° C. A surface induction hardening is performed on the semi-finished blank prior to a step of shallow nitriding, the step of shallow nitriding being carried out for a period of less than 250 hours, at a temperature of between 400° C. and 600° C.

Abstract: An acoustic panel for an aircraft turbomachine. The acoustic panel includes a first skin formed from a first composite material having a first polymer matrix and reinforcing fibers embedded in the matrix, a second skin formed from a second composite material having a second, thermoplastic polymer matrix and reinforcing fibers embedded in the second matrix, and a core having a honeycomb structure The core can be arranged between the first skin and the second skin, and the second skin can contain holes having a diameter less than 1 mm.

Abstract: A component made from nickel-based superalloy powder consisting of, by mass percent, 14.00 to 15.25% chromium, 14.25 to 15.75% cobalt, 3.9 to 4.5% molybdenum, 4.0 to 4.6% aluminum, 3.0 to 3.7% titanium, 0 to 200 ppm carbon, the remainder consisting of nickel and unavoidable impurities.

Abstract: The invention relates to a method for detecting a defect (DEF) in at least one gear of an aircraft turbomachine based on a vibratory signal (s(n)) of the gear, each gear having a determined meshing frequency (fc) corresponding to a carrier frequency, the method comprising steps consisting in estimating (E3) a target signal (x(n)) comprising a set of characteristic spectral lines based on a whitened vibratory spectrum (y(n)) obtained from a vibratory signal, the method comprising steps of determining, in the whitened vibratory spectrum (y(n)), a plurality of modulation blocks having a modulation index, each modulation block having a carrier coefficient that is dependent on a predetermined carrier frequency (fc) and on the modulation index and a plurality of modulation coefficients that are symmetric about the carrier coefficient.

Abstract: Method for monitoring the navigation of a vehicle for the implementation of a navigation maneuver, the method including the steps of: estimating a magnitude by a Kalman filter from parameters, a digital model of the vehicle in its environment, and at least one measurement made by at least one sensor and associated with an uncertainty on this measurement, the magnitude serving to implement the navigation maneuver; determining at least one partial derivative value of the magnitude with respect to the at least one measurement; obtaining at least one criticality value of the at least one measurement for the estimation, from the at least one partial derivative.