Abstract: A method of manufacturing a blisk comprises the steps of cutting a disk to a rough shape comprising a hub with a plurality of blade blanks projecting radially therefrom, machining each blade blank by tangential milling using a tool with a rotation spindle perpendicular to the radial direction to make repeated radial passes, the tool being turned through a facet angle with respect to the disk between each pass. Each blade blank is thus milled to a blade having faceted surfaces. Preferably, the width of each facet is smaller that 5 mm, and adjacent facets subtend angles smaller than 5°, or even more preferably smaller than 3°.

Abstract: The invention relates to a repair process of a metallic piece, in particular of a rotor or stator blade of a gas turbine motor comprising an anti-wear layer formed by loading by welding of an anti-wear material to a part of its surface and whereof said layer is partially machined, characterised in that it comprises a rectification stage of said layer in which a trace of said original anti-wear layer is left to subsist on at least part of the base of the rectified zone, and a stage in which a new layer of anti-wear material is deposited by welding. The invention in particular relates to turbine blades with a shroud and has the advantage of at the same time ensuring good adhesion of the new layer and preventing the appearance of defects in the metallic substrate.

Abstract: The invention concerns a sealing method for producing a film of oxide having good saline corrosion resistance properties on a metal substrate. Said method comprises steps consisting of: providing a buffered sealing solution comprising at least one simple cobalt II salt and at least one simple lithium III salt; and bringing said metal substrate having a previously oxidized surface into contact with said sealing solution for a period sufficient to form a mixed cobalt/lithium oxide film. More particularly, this method is applicable to a metal substrate produced from aluminum or from aluminum alloy anodized in a sulfuric medium.

Abstract: The cryogenic rotary coupling comprises segments of a cryogenic line that are capable of turning relative to each other about a pivot axis of the rotary coupling. Radial retaining elements and axial retaining elements define the pivot axis of the rotary coupling. One of the segments comprises a vacuum-insulated double-walled female portion and the other segment comprises a vacuum-insulated double-walled male portion engaged at least in part in the female portion. A first sealing gasket is interposed between a free end of the male portion engaged in the female portion and one of the retaining means. A second sealing gasket is interposed between a free end of the female portion surrounding the male portion and the other one of the retaining elements. A heater device is disposed in the vicinity of the second gasket.

Abstract: Device for automatically mounting and dismantling tools (10) on a robot (16), comprising means (1) for storing a number of identical fresh tools (10) and means (11) for centering one of these tools (10) in a position for automatic mounting on the robot (16), each tool (10) comprising an axial orifice for mounting on a rotating pin (15) provided on the robot (16).

Abstract: A device for reducing the jet noise of a turbomachine, the turbomachine having a longitudinal axis and a substantially cylindrical nozzle extending along the longitudinal axis of the turbomachine, having a downstream end for mixing the flows of gas inside and outside the nozzle, the device comprising a plurality of corrugations disposed to extend the downstream end of the nozzle, and a plurality of notches disposed between pairs of successive corrugations in the plurality of corrugations, and the plurality of corrugations and the plurality of notches are asymmetrical relative to at least one axis perpendicular to the longitudinal axis of the turbomachine so as to generate a dual counter-rotating effect between the gas flows.

Abstract: A soundproofing panel (2) comprises a core (4) sandwiched between a solid wall (6) and a porous wall (8), the core being connected to the walls and comprising partitions (12) extending in the thickness direction between the two walls so as to form cells (10) each cell containing at least one sound energy dissipating layer (14), the dissipating layers (14) being constituted by hollow spherical beads (20) having mutually contacting walls that are porous and micro-perforated, and being held in position in the thickness direction between the two walls (6, 8) by nets (22) that are secured to the partitions.

Abstract: The de-icing device is intended for the vane (10) of the inlet guide wheel (4) of a turbojet (2), comprising a fixed part (12) arranged on the upstream side and a mobile flap (18) arranged on the downstream side, in which said fixed part (12) comprises a trailing edge (16) substantially in the shape of a “U”, with one of the branches (162) being located on the intrados side (I) and the other branch (164) being located on the extrados side (E). It comprises at least one emission window (202), oriented substantially along an upstream-downstream direction, and arranged along the branch (162) of the “U” located on the intrados side (I) of the trailing edge (16). The inlet guide wheel (4) vane (10) is equipped with at least such a de-icing device. The aircraft engine (2) comprises at least one vane (10) equipped with such a de-icing device.

Abstract: An assembly for ventilating a stator ring having branched pipes that include feed pipes, distributors, and a plurality of manifolds adjacent to the stator ring and provided with drilled holes. The distributors connect the feed pipes to the plurality of manifolds, and the plurality of manifolds include pairs of half-shells, each of the half-shells including an end plate having an opening and a rim surrounding the end plate, and the half-shells in each of the pairs being joined to each other at the rims. The distributors include ducts mounted between adjacent ones of the plurality of manifolds and have open ends fitted into openings of the end plates and have abutment portions to the end plates.

Abstract: The invention relates to the sealing of the cavity for bleeding air to the cabin, which cavity is delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to said external casing and to an external engine casing shell, this external casing shell being fastened to the annular structure by bolting together flanges, using sealing means provided between the annular structure and the external casing of the diffuser grating, wherein the sealing means consist of a brush seal fastened to the periphery of the upstream part of the external casing of the diffuser grating, said seal having bristles which extend radially outward and bear against the internal surface of a cylindrical sleeve which is integral with the annular structure and surrounds said brush seal.

Abstract: The invention relates to a turbine wheel (1) for a turbomachine, the disk (4) of which comprises upstream and downstream ribs (14a, 14b) extending in the annular direction around an axis (2), each blade segment (6) installed on the disk possibly being retained by the disk in an external radial direction using upstream engagement means (16a) forming part of the segment root (8) and capable of cooperating with complementary upstream engagement means (18a) forming an external radial end of the upstream rib, and downstream engagement means (16b) forming part of the root and capable of cooperating with complementary downstream engagement means (18b) forming an external radial end of the downstream rib. Furthermore, the upstream and downstream ribs are designed so that they can be moved from a separated engagement position to a close position, and vice versa, so that each blade segment can be assembled on the turbine disk.

Abstract: The invention relates to a process for manufacturing or repairing a monobloc bladed disc including a stage of forming, on a protruding projection (4) belonging to a disc (1) and extending from an upstream end (4a) to a downstream end (4b) along a protruding projection chord (6), a welded joint surface (8) intended to allow a subsequent stage of fitting a blade (2) by linear friction welding onto the protruding projection (4) of the disc (1). According to the invention, the stage of forming the welded joint surface (8) is carried out in such a way that it includes at least two butt-jointed plane portions (8a, 8b, 8c), arranged in sequence along the protruding projection chord (6). Application to turboshaft engine rotors.

Abstract: Titanium-based metal parts (1, 3) are soldered by using as a filler metal (7) an aluminium alloy containing magnesium and virtually no silicon. Application to the bonding of blades (3) to the inner shroud (1) of an aeronautical gas turbine engine compressor nozzle ring.

Abstract: A fixed guide vane assembly includes a circular casing composed of at least two parts (11) and supporting sectors (5), each composed of an inner segment (7) and an outer segment (6) connected by vanes (8). The parts of the casing and the sectors of the guide vane assembly are held together by a system forming a slide and a slider. An anti-rotation mechanism (30) is provided to prevent the sectors from rotating with respect to the casing.

Abstract: The present invention provides: a material, which is dense, with a density of ?90%, bulk dry self-lubricating, with a coefficient of friction of <0.3, constituted by a matrix that endows it with suitable strength, with a Rm of ?400 MPa in a medium to high temperature range of 300° C.???600° C.; said matrix including particles of solid lubricant in its volume; mechanical parts formed from said material; a method of manufacturing said material.

Abstract: The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which circulates a stream of cooling air, a convergent divergent axisymmetric nozzle arranged downstream of said afterburn chamber, each circle of flaps comprising alternately a plurality of controlled flaps, and a plurality of follower flaps, a circle of cold flaps arranged radially outside said nozzle and hinged at their upstream end to a conical shell linked to the downstream part of the casing.

Abstract: A method of moving a virtual articulated object in a virtual environment in a succession of unit movements, the articulated object comprising a set of articulated elements connected together by a set of joints, the relative positions of the articulated elements being defined by a plurality of joint angles about a plurality of degrees of freedom, the method comprising the following steps: calculating an interaction distance between a given articulated element and the other articulated elements of the articulated object; extracting from said interaction distance, a first point belonging to the given articulated element, and a second point belonging to one of the other articulated elements of the articulated object; defining a single extraction vector from said first and second points; and moving the given articulated element away from the other articulated elements of the articulated object in a movement defined as a function of the single extraction vector by acting on the degrees of freedom of the articulated

Abstract: Turboshaft engine, such as for example a turbine, comprising a segmented seal between two longitudinally adjacent elements such as, for example, a casing and a ring of sectors of vanes. According to one embodiment, a seal is interposed between a casing and a ring of sectors of vanes and consists of a plurality of flexible segments having a straight deformation zone and a straight fluid-tight bearing zone.

Abstract: A method of moving a virtual articulated object in a succession of individual movements in a virtual environment, the articulated object being specified in said environment by a global position, a global orientation, and a plurality of joint angles defining the positions of a set of articulated elements making up said articulated object with a plurality of degrees of freedom, the method comprising the following steps: calculating an interaction distance between the articulated object and its environment; extracting from said interaction distance a first point belonging to one of the elements of the articulated object, and a second point belonging to the environment; defining a single extraction vector from said first and second points; and moving the articulated object away from its environment by a movement defined as a function of the single extraction vector and acting on the global position, and/or the global orientation, and/or the degrees of freedom of the articulated object so as to avoid a collision b

Abstract: A low-pressure turbine of a turbomachine, the turbomachine comprising a high-pressure turbine disposed upstream from the low-pressure turbine, and an exhaust casing disposed downstream from the low-pressure turbine, the low-pressure turbine comprising a rotor secured on a low-pressure trunnion, a low-pressure shaft, a first rolling bearing disposed on said low-pressure shaft and supporting a high-pressure trunnion having fastened thereon a rotor of the high-pressure turbine, a second rolling bearing disposed on said low-pressure trunnion downstream from said first rolling bearing and enabling said low-pressure trunnion to be centered relative to said exhaust casing, and a system of fluting for enabling said low-pressure trunnion to drive said low-pressure shaft, said system of fluting being disposed between said first and second rolling bearings.