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: The invention relates to an axial turbomachine compressor outer casing. The casing comprises a sealing device collaborating with a row of rotor blades. The casing comprises a wall with an annular groove in which the sealing device is housed. The sealing device comprises a segmented outer shroud and a plurality of piezoelectric actuators moving the shroud radially in the groove so as to open or close the functional clearance. The invention also proposes a method for controlling a sealing device for a turbojet engine, the method comprising a step of measuring the altitude and a step of adjusting a clearance according to the altitude.

Abstract: The invention relates to a sealing device of an axial turbomachine, comprising a circular strip with an outer surface and an inner surface; an annular layer of abradable material on one of the outer and inner surfaces of the strip, designed to provide a sealing with an annular row of rotor blades. The surface of the strip covered by the abradable layer comprises at least two perforated circular zones, each with a series of distributed perforations. The surface of the strip covered by the abradable layer further comprises a smooth circular zone disposed axially between the perforated areas. The smooth zone is centered on the outer ends of the rotor blades. The invention improves the adhesion of the abradable layer on the metal strip, and avoids a premature breakdown of the abradable layer in contact with the rotor blades, despite the presence of perforations.

Abstract: An axial compressor includes a rotor, a stator, and a blade attached to the stator at a base section and linked to a ferrule at a section opposing the base section, the ferrule being supported solely by the blade. The rotor is configured to rotate within the stator and the ferrule is configured to extend around a periphery of the rotor.

Abstract: The present application relates to a blade of low pressure rectifier axial turbomachine. The blade can also be a rotor blade and/or a turbine blade. The blade includes a composite material with a matrix and a reinforcement that includes a mesh forming a three dimensional structure with a plurality of rods that describe a three-dimensional mesh based on polyhedrons. The three-dimensional structure extends over the majority of the thickness of the blade between the pressure side surface and the suction side surface and/or the majority of the length of the blade between the leading edge and the trailing edge. The rods of the reinforcement are bonded to each other and are distributed throughout the volume between the pressure side surface and the suction side surface of the blade. The rods form a three-dimensional mesh occupying the entire blade. The present application also relates to an iterative method for manufacturing a blade by additional layer manufacturing.

Abstract: The invention relates to a housing for covering the ends of a row of rotor blades of an axial turbomachine compressor, the housing being provided with a sealing device between the blade tips and the housing. It comprises a shell segmented along its circumference, each segment being fixed to the housing by a series of elastomeric elements in a recess in the shape of a channel cut into the inner surface of the housing. In this way, in the event of misalignment of the rotor relative to the stator, the rotor blades coming into contact with sections of the shell will be able to move to compensate for this misalignment while reducing the frictional forces generated by contact between the blades and the shell. In the event of alignment being re-established the segments of the shell will be able to resume their initial position because of the elastic behavior of the elements.

Abstract: The present application relates to a stator blade sector configured to be fixed to a housing of an axial turbomachine, the sector having a plurality of blades with platforms juxtaposed, so as to describe an arc of a circle. At least one of the platforms comprises on its outer face a fixing screw and at least one other platform has no fixing screws, the platforms being fixed together at their adjacent edges. The application also relates to a stator or portion of stator having a housing forming a generally circular wall and blade sectors arranged along the wall. The housing includes several parts connected to each other by longitudinal flanges. Platforms with no fixing screws are located opposite the flanges.

Abstract: The present application relates to a compression stage of a low-pressure compressor of an axial turbomachine, such as a turboprop. The stage includes a rotor with, on its outer surface, two lip seals, each forming a radial annular rib; and a stator which includes an annular row of stator blades extending substantially radially; and an inner shell whose radial cross section includes a central part connected to the inner tips of the blades, a lateral part extending from each side of the central part to one of the two lip seals, respectively, thus forming a rotor with the annular cavity. The shell and the rotor are configured so that the radial section of the annular cavity has a length L1 and a height H, the length L1 being greater than the height H, which initiates rotational movement of the air contained therein. The speed of the air reduces its pressure, which limits downstream to upstream leaks.

Abstract: An axial compressor includes a rotor, a stator, and a blade attached to the stator at a base section and linked to a ferrule at a section opposing the base section, the ferrule being supported solely by the blade. The rotor is configured to rotate within the stator and the ferrule is configured to extend around a periphery of the rotor.

Abstract: A ferrule of a stator with blades of an axial turbomachine consists of at least two segments having the general form of an arc of a circle and intended to be arranged end to end, so as to form the ferrule, where each segment contains on its outside a plurality of openings arranged at regular distances along the general arc of the circle of the segment, into each of which fits the end of a blade of the stator. Each end of a segment possesses a section of which the profile essentially corresponds with that of the end of the corresponding blade when the segment is placed on the blades of the stator, such that the joint between two adjacent segments corresponds with the profile of the corresponding blade.

Abstract: A compressor drum for an axial turbo-machine includes a hollow body generally symmetrical in revolution about its axis of rotation and forming a shell at the periphery of which are arranged a plurality of parallel rows of vanes, each row corresponding to one stage of the compressor. Each vane includes at its root an attachment platform housed in a corresponding opening made in the shell of the hollow body. The outer surface of each platform is flush with the outer surface of the shell at the edge of the opening and each platform is attached to the hollow body by welding between the outer edge of the platform and the inner edge of the corresponding opening. The platform has the general shape of a parallelogram, a bisector of which corresponds approximately to the main axis of the profile of the vane at the platform.

Abstract: The invention relates to a housing for covering the ends of a row of rotor blades of an axial turbomachine compressor, the housing being provided with a sealing device between the blade tips and the housing. It comprises a shell segmented along its circumference, each segment being fixed to the housing by a series of elastomeric elements in a recess in the shape of a channel cut into the inner surface of the housing. In this way, in the event of misalignment of the rotor relative to the stator, the rotor blades coming into contact with sections of the shell will be able to move to compensate for this misalignment while reducing the frictional forces generated by contact between the blades and the shell. In the event of alignment being re-established the segments of the shell will be able to resume their initial position because of the elastic behaviour of the elements.

Abstract: A compressor drum for an axial turbo-machine includes a hollow body generally symmetrical in revolution about its axis of rotation and forming a shell at the periphery of which are arranged a plurality of parallel rows of vanes, each row corresponding to one stage of the compressor. Each vane includes at its root an attachment platform housed in a corresponding opening made in the shell of the hollow body. The outer surface of each platform is flush with the outer surface of the shell at the edge of the opening and each platform is attached to the hollow body by welding between the outer edge of the platform and the inner edge of the corresponding opening. The platform has the general shape of a parallelogram, a bisector of which corresponds approximately to the main axis of the profile of the vane at the platform.

Abstract: A ferrule of a stator with blades of an axial turbomachine consists of at least two segments having the general form of an arc of a circle and intended to be arranged end to end, so as to form the ferrule, where each segment contains on its outside a plurality of openings arranged at regular distances along the general arc of the circle of the segment, into each of which fits the end of a blade of the stator. Each end of a segment possesses a section of which the profile essentially corresponds with that of the end of the corresponding blade when the segment is placed on the blades of the stator, such that the joint between two adjacent segments corresponds with the profile of the corresponding blade.