Abstract: There is provided a seat base frame (10) comprising one or more base frame tubes (16) having noncircular cross-sections. In a specific example, the tubes (16) have elliptical cross-sections. Further embodiments provide base frame tubes (16) made of magnesium or magnesium alloys.

Abstract: Embodiments of the disclosure relate to a device for limiting overspeeding of a turbine shaft of a turbomachine, comprising structure for destroying the rotor blades of at least one turbine stage. The structure includes a casing and at least one projectile configured for projecting into the path of the rotor blades of the stage in order for the stage in question to be destroyed.

Abstract: A reversible system for dissipating heat power generated in a gas turbine engine, the system including a condenser-forming first heat exchanger, an evaporator-forming second heat exchanger, a scroll compressor suitable for operating as a compressor when the temperature of the cold source is higher than a predefined threshold temperature and as a turbine when the temperature of the cold source is lower than the threshold temperature, an expander and a pump arranged in parallel, and a control valve arranged upstream from the expander and the pump and suitable for directing the refrigerant fluid to the expander when the temperature of the cold source is higher than the threshold temperature and to the pump when the temperature of the cold source is lower than the threshold temperature.

Abstract: The invention concerns an assembly for the stator of a compressor of an axial-flow turbine engine, such as a low-pressure compressor of the turbojet engine also known as a booster. The assembly comprises: a first annular array of first vanes of the stator extending radially in the axial flow; and a second annular row of second vanes of the stator, with controlled orientation, also known as variable-pitch vanes or VSV. In addition, the assembly comprises an external monobloc shroud on which the first vanes and the second vanes are mounted in a pivoting manner.

Abstract: The invention relates to an automatic assistance method for landing an aircraft on a landing runway, from a return point (A) to a completion point (PA) at which the aircraft comes into contact with the landing runway, implemented by a data-processing device on-board said aircraft and configured to be linked to an inertial unit, an altimeter and a deviation meter, said method comprising: —guidance, based on position and attitude data provided by the inertia unit and altitude data provided by the altimeter, of the aircraft along a predefined trajectory from the return point (A) to a predetermined holding point (C) approximately aligned with the axis of the landing runway, the guidance been performed over at least one part of said predefined trajectory on the basis of corrected position data calculated using position data of the aircraft provided by the inertia unit and measurements transmitted by the deviation meter, —guidance from the holding point (C) to the completion point (PA).

Abstract: The present invention relates to a turbine engine guide (23) vane (25), with a height (H) extending between a vane root (26) and a vane tip (27) along a radial direction (Z), said vane (25) comprising a succession of five bulge portions along a tangential direction (Y) perpendicular to the radial direction (Z), this succession of bulge portions extending over the whole height (H) of the vane (25), and the convexity of the successive bulge portions being alternately in one direction and in the other. The vane (25) has the advantage of having an eigenfrequency for the first striped vibration mode which is different from the urging frequencies of said vane (25), during the operation of the turbine engine.

Abstract: A turbomachine rotor blade, which includes a body radially extending and an insert covering the body tip, the insert being made of a first portion radially covering the blade tip and of a second portion partly covering the intrados face of the blade. The cross-section of the insert along a radial plane with respect to an axis of a rotor is corner-shaped and the first portion of the insert extends tangentially with respect to the main axis of the rotor and the second portion extends globally radially with respect to the main axis of the rotor.

Abstract: The assembly (25) links a static housing (24) of the turbomachine, into which supply lines, in particular fluid supply lines (23), arrive, to the blades of the propeller, and comprises: —a system for controlling fluid pitch (27), rigidly connected to the static housing (24), capable of being linked to the supply lines, —a linear actuator (28) having two chambers separated by a piston (71) of which the sliding is dictated by the control system and allows the blades to rotate, and —two concentric tubes (36, 37) housed in the planetary shaft of the epicyclic reduction gear and linking the system (27) to the actuator (28) by delimiting two fluid passages (45, 48) linked, respectively, with the two chambers (72, 73) of the actuator.

Abstract: A radial control shaft for a device for controlling the pitch of fan blades of a turbine engine having an unducted fan, is disclosed. The shaft includes an external portion that is designed to be mounted in the control device from its outside and to be coupled to at least one fan blade in order to adjust its pitch, and an internal portion, independent of the external portion, that is designed to be mounted from the inside of the control device, to be connected to a load transfer bearing in order to pivot the shaft about a radial axis, and to close an oil enclosure in which the bearing is housed, the external and internal portions of the shaft being coupled to each other. A method of mounting such a shaft and a control device including such a shaft are also disclosed.

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: The invention relates to a method for manufacturing a blade made of composite material extending in a main elongation direction, the composite material of said blade comprising a fiber reinforcement densified by a matrix, the method comprising the following steps: a step of weaving warp yarns and weft yarns to produce a fiber preform, the fiber preform comprising at least one warp yarn adapted to form in the matrix at least one first portion of a channel, said portion of length of the warp yarn being directed according to the main elongation direction of the blade and opening at the root of the blade, the first channel portion formed in the matrix by said portion of length of warp yarn constituting at least one first portion of the internal airflow channel; a step of forming the fiber preform so as to produce a blade preform and densifying said blade preform; characterized in that the weaving step comprises placing at least one second portion of yarn adapted to form in the matrix a second portion of a cha

Abstract: The invention proposes a method comprising the evaluation of a function F obtained by applying to n sub-functions fi a first operation, the evaluation comprising: the application of a series of calculation steps in which a first unit assumes a role of a client and a second unit assumes a role of a server, and the repetition of the series of calculation steps in which the roles of client and of server are exchanged between the units, each series of steps comprising: a) randomly generating, by the server, first data, and a second datum, b) for each sub-function fi, generating by the server a set of elements formed by: a result of fi evaluated in the data of the client and of the server, masked by a first datum, by applying the first operation between the result and the first datum, and masked by the second datum, by applying between the masked result and the second datum of a second operation different from the first and distributed relatively to the latter, c) recovering by oblivious transfer, by the

Abstract: A device for reducing the jet noise of a turbine engine includes an outer cover having an inside wall defining the outside of an annular passage for passing a bypass stream from the engine, the wall of the outer cover including a plurality of microjet circuits, each including intakes for taking a gas stream from the bypass stream flow passage and leading to a single feed duct, which in turn opens out into the trailing edge of the outer cover via at least one ejection grating suitable for splitting the intake gas stream into a plurality of gas streams of right sections of dimensions less than a right section of the feed duct.

Abstract: A fastening method for fastening a tube (50) to a connector (101, 102), the method comprising the following steps: a) providing a connection kit comprising a sleeve, and a coupling for connecting together at least one pair of tubes, of generally tubular shape; b) placing the coupling in a first position in which the first end of the coupling projects outside the sleeve through a first end (10A) thereof; c) then fastening the first tube in leaktight manner to the first orifice; d) moving the coupling relative to the sleeve into a second position in which the first orifice lies inside the sleeve; and e) with the coupling in the second position, fastening the sleeve (10) at a sufficient distance from the coupling (20). A connection kit for performing the method.

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: 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: 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: 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.