Abstract: The invention relates to a mechanical fuse intended to be rigidly mounted between a drive unit (8, 9), and a receiver unit (10), each rotating about the same axis (7) of rotation, said fuse comprising a body (13) extending in a longitudinal direction parallel to said axis (7) of rotation, once the fuse is mounted between said drive unit (8, 9) and receiver unit (10). The invention is characterized in that said body (13) comprises a plurality of longitudinal bars (14), each bar (14) being deformable by bending, such as to form a twist-breakable mechanical fuse.

Abstract: The invention relates to a turbine blade (1) of a turbine engine including an upper surface (11), a lower surface (12), a leading edge (13), a trailing edge (14), and a squealer tip (2) at the top thereof, wherein said squealer tip (2) is defined by a rim (2a) and comprises at least one inner rib (3) that is spaced apart from the rim (2a) defining the squealer tip (2). The invention is characterized in that said inner rib (3) is shaped to define, inside the squealer tip, a cavity (4) inside of which the passage of leak flows (5) is limited, wherein an upstream opening (131) is made in the rim (2a) at the leading edge (13), and a downstream opening (141) is made in the rim (2a) at the trailing edge (14).

Abstract: A method for nondestructive inspection by ultrasound of a bonded assembly is provided. The method comprises two steps, consisting of measuring a thickness of an adhesive joint of the bonded assembly by an ultrasound transducer arranged on the bonded assembly in a determined position, and measuring the degree of adhesion of parts of the bonded assembly by the same ultrasound transducer maintained in the determined position, the degree of adhesion being measured by ZGV Lamb waves.

Abstract: An assembly for a turbine engine. The assembly includes a mount, a nut clamping around the male portion of the mount, a member projecting from the mount and a device for limiting loosening of the nut. The loosening limitation device includes a member for locking the nut against rotation relative to the mount. The rotation locking member includes an inner surface designed to limit rotation of the nut with shape engagement with an outer surface of the nut. The rotation locking member includes a first anti-rotation abutment designed to rotatably abut against the projecting member. The loosening limitation device includes a translation locking member designed to limit translation of the rotation locking member relative to the nut.

Abstract: The invention relates to a method for securing a document including a visual element, carried out by a processing unit comprising processing means, the method comprising generation, from the visual element, of a reference security datum, and storage of the reference security datum, wherein the reference security datum is generated by means of an algorithm configured so as to generate: for any image acquired from the visual element, a security datum whereof the differences relative to the reference security datum are less than a determined threshold, and for any image acquired on a different visual element, a security datum whereof the differences relative to the reference security datum are greater than said threshold.

Abstract: The invention relates to a navigational aid method for an inertial navigation system including at least one inertial sensor (4) having a sensitive axis (X-X), each inertial sensor (4) comprising an ASG gyroscope (8) able to deliver an ASG signal representative of a rotation about the corresponding sensitive axis (X-X), and a MEMS gyroscope (10) able to deliver a MEMS signal representative of a rotation about the corresponding sensitive axis (X-X), the method including the steps of: between a first date and a subsequent third date, calculating a path from the MEMS signals; from the third date, calculating the path from the ASG signals; estimating a bias vector introduced by the MEMS gyroscopes (10), from the MEMS signals and ASG signals; at a fourth date subsequent to the third date, resetting the path.

Abstract: A system and method for detecting a fluid leak in a turbomachine. The turbomachine includes a high temperature fluid source, at least one fluid distribution pipe adapted to distribute the fluid to different parts of the turbomachine and/or an aircraft which is to be equipped with the turbomachine, a turbomachine compartment in which the distribution pipe is at least partly accommodated, the compartment having in operation a low temperature relative to the high temperature of the fluid supplied by the fluid source. The method includes measuring a temperature variation in the compartment between two instants to obtain a temperature gradient, and detecting a fluid leak when the temperature gradient is greater than or equal to a threshold temperature gradient.

Abstract: An extraction sleeve for extracting two rotationally symmetrical parts that are joined together by interference fit, the extraction sleeve including: a head having a conical part; a cylindrical body, the internal part of the cylindrical body having a screw thread suitable for the screwing of an extraction screw; the conical part of the head of the extraction sleeve forming a friction component suitable for coming into contact with one of the rotationally symmetrical parts, the friction component being designed so as to determine a limit slipping torque greater than the friction torque generated at the screw thread of the sleeve by screwing of the extraction screw.

Abstract: The invention relates to a blade of a low-pressure compressor of an axial turbine engine. The blade comprises a vane in which a cavity is formed. The vane has a leading edge and a trailing edge, an intrados surface and an extrados surface which extend from the leading edge to the trailing edge, an outer casing which forms the intrados surface and the extrados surface and which delimits the cavity. The blade further comprises closed foam, such as a polymethacrylic foam, which blocks the cavity in order to isolate it from the environment of the blade. The blade further has a three-dimensional lattice which is formed in the cavity and which is integral with the vane of the blade. This barrier protects from chemical attacks and the introduction of impurities. The invention also relates to a production method for a hollow turbine engine blade which is filled with foam.

Abstract: A method for monitoring an LVDT sensor including two secondary circuits, the method including: calculating the difference between voltages at terminals of one of the secondary circuits at a given instant and at a previous instant; calculating the difference between voltages at terminals of the other one of the secondary circuits at the given instant and at the previous instant; calculating the sum of the two differences calculated; modifying an indicator according to a distance to zero of the previously calculated sum; and comparing the indicator with at least one predetermined threshold.

Abstract: A method for producing cavities in a turbomachine disk, the cavities extending between first and second lateral surfaces of the disk, the method including positioning a ring facing the first surface, the ring including an inner periphery including protrusions complementary in shape to the cavities that are to be produced; circulating an electrolyte close to the protrusions on the ring; activating a first translational movement of the ring towards the second surface; activating a rotation of the disk; generating an electric current pulse in the electrolyte when the ring is substantially at the first surface, the pulse resulting in the ionic dissolution of the disk at the protrusions; reducing the speed of rotation to a first reduced speed, when the ring is substantially at the first surface, for a first period of time; and stopping the first translation of the ring when the ring is beyond the second surface.

Abstract: An actuator for a flight control surface of an aircraft, including: a fixed annulus for fixing to the fuselage, an rotatable annulus with respect to the fixed annulus about an axis of rotation, an output ring which can be fixed to the control surface, and a coupling mechanism having a disc with translational mobility with respect to the mobile annulus in a direction parallel to the axis of rotation, the disc able to move between an engaged position, and a disengaged position, in which the disc is disengaged from the mobile annulus to disconnect the output ring from the mobile annulus. A retaining piece keeps the disc in the engaged position, and a rupture member activates to break the retaining piece to allow the disc to move into the disengaged position.

Abstract: A defective-pixel detection method included in an image-processing procedure, including a pixel-processing procedure applied to pixels of an image supplied by an image sensor. Each pixel is associated with a classification value representing a state of said pixel. The method includes, for each pixel: applying the pixel-processing procedure; analyzing a result of the pixel-processing procedure; in the event of obtaining an unusual result representing a defect on a photosite of the image sensor that supplied said pixel, incrementing a number of detections of an unusual result for said pixel; and associating said pixel with a classification value representing a defective pixel when said number reaches a first threshold.

Abstract: The method of estimating a quality index of a gray-scale encoded three-dimensional image of a composite material part includes an obtaining step for obtaining a histogram from the image, the histogram representing for each class of a plurality of classes each including at least one gray-scale level, the number of voxels of the image having a gray-scale level belonging to the class; an extraction step for extracting a predetermined number of Gaussian functions present in the histogram; and an estimation step for estimating at least one quality index of the image from parameters characterizing the Gaussian functions extracted from the histogram.

Abstract: An airplane unducted propeller turboshaft engine having a gas generator and a receiver including a propulsion assembly carrying least one propeller, the engine including a first casing, a second casing, and a third casing, the third casing being provided between the first and second casings and surrounding at least a portion of the gas generator, a reinforcing shell presenting a first attachment zone mounted on the first casing, second attachment zone mounted on the second casing, and a wall provided between the first and second attachment zones and surrounding the third casing, wherein the reinforcing shell further includes at least one pipe segment integrated in the wall.

Abstract: The present invention relates to a method for dimensioning a turbomachine comprising a casing and a disc to which at least one blade is secured, said disc being rotationally driven by a shaft about a turbomachine axis (z), comprising: —acquisition (E1) of the coordinates (P) of the ends of the leading edge and of the trailing edge of the blade in a frame of reference connected with the disc; —expression (E2) of the coordinates (P?) of the ends of the leading edge and of the trailing edge of the blade in a frame of reference connected with the casing; —calculation (E3) of the distance (g) between the casing and the ends of the leading edge and trailing edge of the blade from the coordinates (P?) expressed in the frame of reference connected with the casing; —calculation (E4) of the contact pressures between the blade and the casing along the end of the blade from the calculated distance (g); —calculation (E5) of the reaction forces and moments resulting from contact between the blade and the casing from the ca

Abstract: A method of determining the wear of a flank of a cutter tool, in which the wear is determined by a general function calculating a characteristic length of the wear as a function of at least one variable that depends on time, is provided.

Abstract: A part made of oxide/oxide composite material includes fiber reinforcement constituted by a plurality of warp yarn layers and of weft yarn layers interlinked by three-dimensional weaving, with the spaces present between the reinforcing yarns being filled with a refractory oxide matrix. The fiber reinforcement presents a weave selected from the following weaves: interlock; multi-plain; multi-satin; and multi-serge, with warp and weft thread counts lying in the range 4 yarns/cm to 20 yarns/cm. The fiber reinforcement also presents a fiber volume fraction lying in the range 40% to 51%.

Abstract: The invention relates to equipment (40) for disassembling a planet carrier (14), said planet carrier (14) comprising: a cage (20) comprising an inner bridge (24) and an outer bridge (26); a cage carrier (30) comprising at least one finger bar (31) to be inserted between the inner bridge (24) and the outer bridge (26); and a connection shaft (14) housed in through-holes (25, 27, 33) formed in the bridges (24, 26) and in the finger bar (31), such as to retain the cage (20) on the cage carrier (30). The equipment comprises: a jack (41) including a body and a piston (42), said piston (42) being designed to apply a force to the connection shaft (14); and a support (43) designed to bear on the finger bar (31) when the piston (42) applies a force to the connection shaft (14).

Abstract: A power supply and control system of a plurality of electrically controlled actuators on board an aircraft and an actuation system for an aircraft including the electrically controlled actuators and a system for their power supply and their control. The system includes: P electrical power supply units each capable of generating a power signal for powering an actuator, Q control units, each configured for executing at least one servo control algorithm driving a power module of an actuator, and a network communication module connecting each control unit to a computer network for communicating with each actuator.