Abstract: A method of estimating future change in operation of a monitored aircraft (A), including the following steps performed by a computer on board the monitored aircraft, to calculate a current state of the monitored aircraft (ECA) from measurements (VFA) of variables related to operation of the monitored aircraft, to send a request to analyze the similarity of the calculated current state with previous states (EPB) of similar aircraft, and to analyze change in operation (SPB) of each similar aircraft having a similar previous state to determine a probable change (FPA) in operation of the monitored aircraft. The method includes a step performed by a computer (B) on board each aircraft, to compare the calculated current state (ECA) with previous states (EPB) of similar aircraft, and send the change in operation (SPB) corresponding to an identified similar previous state. The invention includes an on board system capable of implementing the method.

Abstract: An assembly forming a gasket for a turbomachine, includes a brush seal made of a plurality of sealing elastic bristles surrounding a core, a retaining ring including a recess to at least partly accommodate the brush seal, and a bearing cover, placed in contact with the brush seal to hold it in position against the retaining ring, the brush seal being located between the retaining ring and the bearing cover.

Abstract: The invention relates to a fixed diffuser vanes assembly (10) for guiding flow through a turbomachine, comprising an internal annular platform (12) and a plurality of fixed vanes (11) which are mounted on this platform, the internal platform comprising a support plate (121) forming the base of said vanes, a radial annular partition (120) extending from the support plate toward an axis of the vanes assembly, and an internal ring (122) attached to the radial annular partition and having an internal surface on which an abradable material (123) is arranged, the vanes assembly being characterized in that the internal ring comprises at least one cut-out (1223) delimiting a tongue (1226), the tongue being bent to press against the radial annular partition (120). The invention also relates to a method of manufacturing such a vanes assembly and to a turbomachine incorporating such vanes.

Abstract: A method of determining a duration of a movement of a starter air valve of a turbine engine, the valve for regulating the passage of a flow of pressurized air from upstream to the downstream of pipework, where the downstream side is connected to a pneumatic starter of the turbine engine, the method including determining an instant of initiation and an instant of completion of a movement of the valve during a movement phase of the valve, determining the duration of the movement of the valve, by subtracting the instant of initiation from the instant of completion, calculating a difference between the determined duration of the movement and a theoretical value of the duration.

Abstract: The invention consists in a method of characterizing a part made of composite material (30), the method comprising a step of determining a characteristic of a longitudinal ultrasound wave (41) traveling along a path within the part (30), and being characterized in that the travel time of a longitudinal ultrasound wave (42) transmitted by the part (30) is measured (E4).

Abstract: A turbine engine rotor blade having a trailing edge (20A) with a modified surface state (22, 28) enabling the flow speed passing around the blade to be altered so as to modify the acoustic interaction against structural elements (12) that interact with the flow downstream from the rotor blade.

Abstract: A compressor for a turbine engine, including: a casing, at least one compressor stage including an impeller having stationary blades and an impeller having moving blades positioned downstream of the stationary blade impeller, and cavities in a thickness of the casing that are disposed along a circumference of the casing opposite the moving blades. The cavities, which are elongate and extend along a main direction of orientation, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the casing. The cavities are offset in relation to the moving blades to overlap the moving blade impeller in the upstream portion, thereby covering the upstream end thereof. The downstream border of the cavities is oriented parallel to the chord at the head of the moving blade.

Abstract: A nacelle structure (10) surrounding a fan, the structure comprising an air inlet (100) having an inside surface (100A) defining an air feed channel; and at least one ring (22) arranged in the air inlet and selectively movable between a deployed position in which the ring is moved radially inwards from the inside surface to provide an obstacle to shock waves coming from the fan, and a retracted position in which the ring is moved radially outwards from the deployed position so as to become flush with the inside surface and thus reconstitute the air feed channel.

Abstract: A variable stator vane for a compressor guide vane is provided. The vane includes a blade and a pivot. The pivot includes an internal pivot element and a pivot cap. The blade and the internal pivot element are each made from a composite material. At least one contact surface of the pivot cap is metallic.

Abstract: The present invention relates to a propulsion unit comprising a pair of contra-rotating coaxial propellers, that are referred to as upstream (2) and downstream (3), the downstream propeller, forming a rotating reference frame, being mounted for rotation about a central member forming a stationary reference frame, and being provided with a device for changing the pitch of the blades, characterized in that the downstream propeller is supported by bearings arranged externally on the cylindrical central support, an upstream bearing (40) of which is arranged downstream of a device for changing the pitch of the blades of the upstream propeller, and in that said device for changing the pitch of the downstream propeller comprises a linear actuator (23) in the stationary reference frame with an element (235) that is able to move axially along the axis of the downstream propeller, the upstream bearing comprising an inner ring that is rigidly connected to the linear actuator and an outer ring that is rigidly connected t

Abstract: A method of characterizing a part including obtaining an X-ray tomography image of the part and then a step of correlating the image with a reference wherein the correlation step includes searching among a predefined set of X-ray tomography image transformations for a transformation that minimizes the difference between the image and the reference in order to characterize the inside of the part.

Abstract: The invention proposes a test bench comprising at least one accelerometer (26, 28) which is linked by rigid mechanical linking to a support (12) and comprising a vibration chamber (38) able to convert an electrical signal into a mechanical vibration disseminated to the support and to the accelerometer by rigid mechanical linking between an oscillating part (40) of the vibration chamber and the support in such a way as to use the support as an acoustic amplifier and to excite the accelerometer according to a predetermined mechanical wave.

Abstract: A turbomachine rotor blade including a blade root and a blade tip spaced apart by a blade height, including at least one intermediate segment between the blade root and the blade tip that presents forward sweep over at least 50% of the blade height, and a distal segment with backward sweep between the intermediate segment and the blade tip, the distal segment also presenting a positive tangential angle of inclination.

Abstract: A method for estimating the temperature of the fuel entering a turbomachine injector, the turbomachine including engine spaces and an oil/fuel exchanger upstream of the injector, the engine spaces and the oil/fuel exchanger having oil passing through them, the oil/fuel exchanger having an efficiency, the engine spaces including a high-pressure spool, the method including (a) measuring the temperature of the oil entering the engine spaces; (b) measuring the rotational speed of the high-pressure spool; (c) calculating the temperature of the fuel leaving the oil/fuel exchanger using the temperature of the oil entering the engine spaces and the rotational speed of the high-pressure spool.

Abstract: Stub for discharging drained fluids for a propulsion unit. The stub includes a cavity for storing the drained fluids and at least one orifice for discharging the fluids contained in the storage cavity, and elements for measuring a difference in pressure outside the stub and a member for draining the storage cavity. The member is able to move between a first position of closing the discharge orifice and a second position of releasing the orifice, and is configured so as to move from the first to the second position when the difference in pressure is greater than, or equal to, a predetermined value.

Abstract: A method of designing a common preform for providing a plurality of preforms for turbine engine outlet guide vanes of different geometrical profiles and made out of composite material, the method including 3D geometrical modeling of the geometrical profiles of the different outlet guide vane preforms, flattening out each of the geometrical profiles of the different outlet guide vane preforms, superposing the geometrical profiles of the different flattened outlet guide vane preforms, and converging towards a single geometrical profile for an outlet guide vane preform common to all of the outlet guide vane preforms while guaranteeing identical positioning for the top and bottom regions of non-interlinking for all of the outlet guide vane preforms.

Abstract: A device for controlling feed of fluid to equipment, such as a heat exchanger, the device including: a fluid slide valve mounted in a fluid circuit including a slide movable between two positions, a first position in which it allows the fluid to flow through the equipment, and a second position in which it prevents the fluid from flowing through the equipment; a laminar flow constriction arranged in the fluid circuit upstream from the slide valve; and a drive mechanism moving the slide of the slide valve between its two positions by head loss of the fluid in the laminar flow constriction.

Abstract: A method for manufacturing a turbine engine blade including an airfoil with a profile defined by a theoretical digital model, the method including: manufacturing a blank having a thickened portion along a trailing edge of the airfoil relative to the theoretical profile; removing the thickened portion by adaptive machining, including: positioning the blank in a reference frame; acquiring, by probing at a predetermined number of points on a first surface of the blank along the trailing edge, positions of the points in the reference frame; determining differences, in one direction, in position from corresponding points of the theoretical model; producing machining grids on the blank surface, peaks of the grids determined from the points; determining an amount of material to be removed from the surface of the grids, based on the position of the points relative to the peaks and the deviations in position; and machining the airfoil.

Abstract: A turbomachine assembly including first and second bodies, in which one of the bodies is rotating relative to the other body around the axis of rotation of the turbomachine, is provided. A tight zone is formed between the bodies and includes a sealing gasket. A flowing fluid, in particular lubricant oil, is able to circulate inside the first and second bodies and to be driven toward the one rotating body from the other body. The one rotating body includes a device for guiding the rotation, in the direction of rotation of the one rotating body, of the flow of fluid inside the one rotating body so as to drive the flowing fluid away from the tight zone.

Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).