Abstract: The present invention relates to a turbomachine rectifier comprising a plurality of stator vanes (5) connecting an inner collar (4) to an outer collar (3), each of said vanes (5) comprising a blade (11) and a blade-head platform (10), comprising an intermediate piece (6) arranged between the inner collar (4) and the outer collar (3) and fastened to the outer collar (3), said intermediate piece (6) comprising openings (14) for the passage of the vane blades (11) and said vane platforms (10) resting, on one side, on the outer collar (3) and, on the other side, on the intermediate piece (6).

Abstract: The present invention relates to a rotor stage of a compressor drum (2) for an axial turbomachine comprising a row of rotor vanes (9) each provided with a platform (12), and a wall (3) that is generally symmetrical in revolution relative to the rotation axis of the turbomachine and forming a hollow body, said wall (3) comprising a partition wall and a support zone (5) that is raised relative to the partition wall in a direction oriented towards the outside of the hollow body, said support zone (5) having a central portion (8) and side walls (7) connecting the central portion (8) to the partition wall of the drum, said platform (12) of each of said vanes (9) being assembled to said central portion (8) by means of one or more fastening elements.

Abstract: The present invention relates to an automated method for manufacturing layer by layer a composite part with rotational symmetry and complex cross-section, comprising the following stages: a) a reel or roll comprising a reinforcement is continuously unwound; b) as an option, the reinforcement is impregnated with a liquid resin by passing through a bath; c) the impregnated reinforcement is wound onto a rotating cylindrical mandrel; d) the impregnated reinforcement is completely or partially polymerised in order to obtain a composite material; e) a support and/or support material is deposited on both sides of the composite material forming the part being manufactured in such a way as to fill the gaps surrounding said part.

Abstract: A straightener blade for a turbomachine, comprising a platform arranged at a radially external end of the blade and adapted to be engaged in a annular groove of a housing, and a threaded rod radially extending outwardly from the platform and adapted to pass through an orifice of the housing in order to receive a fixing nut, the upstream and downstream edges of the platform each comprising a protrusion extending in the plan of the platform in order to limit the rotation of the platform in the groove when the nut screwed on the threaded rod is tightened.

Abstract: The present invention relates to a method for manufacturing a turbine-engine composite rectifier comprising a ferrule provided with a plurality of stator vanes (2), said stator vanes each comprising a blade (4) and optionally a platform (3), said method comprising at least the following steps: a) first layers of a reinforcement (6) are wound on a mandrel, said mandrel also acting as a mold and comprising protruding portions, said first reinforcement layers (6) comprising buttonholes (7) positioned facing the protruding portions; b) a prefabricated disc (9) is positioned on each of the protruding portions: c) last reinforcement layers (8) are wound above the discs (9), thereby forming a preform; d) a resin is injected into the closed mold with the preform and the resin-impregnated preform is polymerized; e) the polymerized preform is taken out of the mold and the base of the blade (4) or optionally the platform of the vane (3), if the latter comprises one of them, is added by welding on each of the discs (9

Abstract: The present invention relates to a turbomachine comprising an air compressor (3) and a lubrication circuit with an oil tank (1), said oil tank (1) being possibly isolated from the rest of the lubrication circuit (4,4A; 6,6A) by means of an isolation valve (7), wherein the isolation valve (7) is configured so as to: operate, i.e. to close and open respectively as the engine (2) stops and starts; remain open when the engine (2) is running; remain closed when the engine (2) is stopped.

Abstract: The present invention relates to a turbine engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule support 19 to an outer ferrule support 14, said inner ferrule support and said outer ferrule support defining an aerodynamic vein and comprising a set of contiguously assembled sectors 20,15 respectively, the plurality of fixed vanes comprising so-called structural vanes 5 surrounding so-called non-structural or aero vanes 6 so as to form boxes 7, said structural vanes 5 being rigidly attached to the ends of the sectors of the inner ferrule support 20 by means of attachment elements 17 in order to impart increased stiffness to the boxes 7.

Abstract: The present invention relates to a method for manufacturing an air/fluid heat exchanger (1), said method comprising at least the following steps: a) on a first sheet metal plate (2), a plurality of tight folds are formed, said folds acting as fins (3), or, alternatively, the first sheet metal plate (2) comprising a first portion (2a) and a second portion (2b), tight folds (3) are formed only on the first portion (2a); said first sheet metal plate (2) or said first portion (2a) forming a sheet metal plate in the upper position; b) the tight folds (3) are opened on a portion across their height; c) the first sheet metal plate (2) obtained in step b) is placed on a second sheet metal plate (6), said second sheet metal plate (6) forming a sheet metal plate in the lower position, or, alternatively, the first portion (2a) obtained in step b) is folded on the second portion (2b), said second portion (2b) forming a sheet metal plate in the lower position, d) the tight portion of the folds (3) is brazed and the

Abstract: The invention relates to an assembly for a stator stage of a turbomachine, the assembly comprising: an outer shroud presenting a series of openings for mounting each stationary vane by welding between the edge of an opening and the outline of the platform of the vane, the outline of the outer segment of an opening surrounding, in radial projection, the outline of the inner segment thereof, the shroud not having any other holes; and at least one stationary vane with its top including a non-pierced platform received in one of said openings prior to the welding step, such that an inside face of the platform bears against a bearing face of the shroud, the outline of the platform presenting a shape that is identical to the shape of the outline of the opening. The invention is applicable to the stator stage of an axial compressor or a turbine of a turbomachine.

Abstract: The present invention relates to a method for manufacturing a turbomachine rectifier comprising an outer ring (5) and a plurality of stator vanes (2), said vanes comprising a platform (9) and a blade (12), wherein said method comprises at least the following steps: a) first folds (7) are draped over a core comprising perforations and having the shape of the aerodynamic flow; b) optionally, the first folds (7) are cut along incisions (8) placed opposite the perforations of the core; c) the blades (12) of the vanes or, alternatively, the blades (12) of the vane preforms, are inserted through the incisions (8) of the first folds (7) and through the perforations of the core; d) last folds (10) are draped over the platforms (9) thus forming a rectifier preform; e) a resin is injected into a closed mold with the preform and the resin-impregnated preform is polymerized; f) a molded piece, essentially having the shape and dimensions of said rectifier, is retrieved from the mold.

Abstract: The present invention relates to an automatic method for manufacturing a stator or rotor blade preform for a turbine engine, comprising at least the following successive steps: a) a step for the helical braiding of a plurality of interlocked tubular braids (1), called nested braids, said step being conducted on braiding machines (2) placed in a row in a braiding direction; b) a step for flattening the nested braids (1); c) a step for stitching the nested braids (1) together in a direction perpendicular to the braiding direction; d) a step for winding the nested braids (1) on a transport mandrel (3); e) a step for cutting the nested braids (1) unwound from the transport mandrel (3), said cut being performed in a direction perpendicular to the braiding direction.

Abstract: The present invention concerns a lubrication system in a closed circuit provided with a valve comprising a first position and a second position, as well as an IN inlet, a first BP outlet and a second M outlet, said IN inlet being connected to the outlet of the feed pump, the first BP outlet being connected to the bypass circuit and the second M outlet being connected to the feed circuit. In the first position of the valve, the flow entering via the IN inlet is diverted to the first BP outlet and in the second position, the incoming flow is diverted to the second M outlet, said valve switching from the first position to the second position and vice versa, when the incoming flow rate exceeds a predetermined threshold upwards and downwards respectively.

Abstract: The present invention relates to a combined machine for pumping and separating into two distinct and purified phases a two-phase liquid/gas mixture or fluid, preferably oil/air, entering the machine, comprising means for the suction, pumping and partial separation of the two-phase fluid, means for drying and extracting the separated gas and means for degassing and forcing back the separated liquid, comprising at least three physically separated stages (A,B,C) intended to be activated by a means that is internal or external to the machine, and built into a single casing: a first stage (A), equipped with an intake for the two-phase fluid, in which the two-phase fluid is sucked, pumped and partially separated into two distinct phases, one phase being mainly liquid and the other being mainly gaseous; a second stage (B), comprising two zones: a first zone in which the mainly liquid phase extracted from the first stage (A) is degassed, and a second zone in which the mainly gaseous phase extracted from the first

Abstract: The present invention relates to an automated method for manufacturing layer by layer a composite part with rotational symmetry and complex cross-section, comprising the following stages: a) a reel or roll comprising a reinforcement is continuously unwound; b) as an option, the reinforcement is impregnated with a liquid resin by passing through a bath; c) the impregnated reinforcement is wound onto a rotating cylindrical mandrel; d) the impregnated reinforcement is completely or partially polymerised in order to obtain a composite material; e) a support and/or support material is deposited on both sides of the composite material forming the part being manufactured in such a way as to fill the gaps surrounding said part.

Abstract: Guide vane stage of a turbine engine comprising a series of fixed blades connecting an inner collar to an outer collar, characterised in that said fixed blades comprise attachment platforms with flat surfaces that co-operate with a plurality of juxtaposed flat facets, said flat facets being located on the inner face of the outer collar in order to ensure attachment with a contact of a flat/flat type between the fixed blades and the outer collar.

Abstract: A turbo-engine stator blading is disclosed. The turbo-engine stator blading includes a crown of fixed blades mounted on a ring. Each blade includes a platform and each blade is fastened to the ring. The ring includes a plurality of individual receptacles for the each of the platforms, the receptacles being machined in the thickness of the ring, the form of each receptacle being complementary to that of the corresponding platform. By means of the receptacles, the mounting of the blades within the blading is both simple and accurate.

Abstract: A method and a system for lubricating a turbomachine including an oil tank, an oil feed pump, an oil/air separator, and at least two enclosures closed by air flow rate seals, each including a low outlet and housing shaft-supporting rolling bearings. The method injects oil from the tank into the enclosures by the pump to lubricate the bearings, introduces compressed air at a low flow rate into the enclosures via the seals to pressurize the enclosures, recuperates all of the air and the oil introduced into the enclosures via their low outlet, uses gravity and the pressurization of the enclosures to convey the oil/air mixture as recovered in this way to the oil/air separator, separates the oil and the air of the mixture by the oil/air separator, returns the oil to the tank, and exhausts the air to outside the turbomachine.

Abstract: The invention relates to a platform (150) for a bladed wheel of a turbomachine comprising a drum (130) and blades (120) of hammer-head attachment type, the foot (122) of which is retained in a circumferential groove (131) of the drum (130), having bearing and/or retaining faces cooperating with the drum (130). Characteristically, the platform (150) comprises at least two openings (151) spaced apart circumferentially and each able to receive the foot of a blade (120), whereby it constitutes a multiple-blade platform in the form of a piece separate from the blades (120). Applicable to a bladed wheel or a turbomachine compressor.

Abstract: Use of the stator blade platforms for the deposition of a track of adjacent abradable material inside an external turbomachine shell. The stator blades (13) are attached to the shell (11) so as to define an annular edge (33) that is substantially continuous and the abradable material is deposited using this edge to delimit a boundary of said track of abradable material (15).

Abstract: The invention relates to an air-oil heat exchanger located at the inner shroud of the secondary duct of a turbojet. In characteristic manner, it comprises an oil circuit placed inside the separator nose and fins placed outside the top wall of the separator nose, between the leading edge of the separator nose and the outlet guide vanes.