Abstract: A rotor disk comprises a plurality of circumferentially distributed hooks, the set of hooks defining an annular groove adapted to cooperate with at least two flange sectors. At least one of the hooks comprises a second element through which a recess is formed which opens up at each of the transverse flanks of the second element and at the internal peripheral surface of the second element.

Abstract: A rotor disk comprises a plurality of circumferentially distributed hooks, the set of hooks defining an annular groove adapted to cooperate with at least two flange sectors. At least one of the hooks comprises a second element through which a recess is formed which opens up at each of the transverse flanks of the second element and at the internal peripheral surface of the second element.

Abstract: Unbalanced mass effects can occur at the low pressure compressor (5) of an aircraft engine. Stiffeners (20) are proposed to increase the stiffness of the assembly and therefore reduce possible cracks due to accidental unbalanced masses, one end (22) of the stiffener can be fixed to the engine casing (7) at the structural arm (10), and the other end (32) can be fixed to the compressor (5), preferably at the upstream face of the third guide vane (RD3). Advantageously, the stiffeners (20) are made of two parts fixed to each other; their manufacturing is optimized to limit the additional weight due to their presence.

Abstract: Turboshaft engine including two subassemblies defining between them an annular chamber housing a seal. The two subassemblies are assembled under axial stress thereby defining an annular chamber housing the seal and an interposed part is inserted between the butting surfaces of the two parts of the annular chamber.

Abstract: A control lever for the pitch angle of a blade in a turbomachine, said lever having a first end intended to be mounted on a blade pivot so as to rotate it and a second end comprising a cylindrical peg for mounting on a control annulus, this peg being fixed by crimping of one of its ends in an orifice of the second end of the lever and comprising an annular flange to which is applied the second end of the lever, wherein stress distribution means are interposed between the second end of the lever and the crimped end of the peg.

Abstract: The invention relates to a compressor blade for a rotary disk of a turbine engine, the blade presenting orthogonal axes that are longitudinal, tangential, and radial, said blade extending radially between a root and a tip, and longitudinally between a leading edge and a trailing edge, said blade being for rotating inside an outer stator shroud having its surface covered in an abradable material. In the invention the tip of the blade presents at least one chamfer in order to reduce the area of contact that can exist between the tip of the blade and the abradable material.

Abstract: Unbalanced mass effects can occur at the low pressure compressor (5) of an aircraft engine. Stiffeners (20) are proposed to increase the stiffness of the assembly and therefore reduce possible cracks due to accidental unbalanced masses, one end (22) of the stiffener can be fixed to the engine casing (7) at the structural arm (10), and the other end (32) can be fixed to the compressor (5), preferably at the upstream face of the third guide vane (RD3). Advantageously, the stiffeners (20) are made of two parts fixed to each other; their manufacturing is optimized to limit the additional weight due to their presence.

Abstract: An epoxy resin composition for encapsulating semiconductors including (A) an epoxy resin, (B) a phenol resin, (C) an inorganic filler, (D) a curing promoter, and (E) a surface-treated coloring agent, wherein the coloring agent before the surface treatment is a carbon precursor with a carbon content of 90 wt % or more or carbon black having a DBP absorption of 100 cm 3/100 g or more, and a semiconductor device encapsulated with the epoxy resin composition. The epoxy resin composition can produce semiconductors which are free from electrical failures such as a short circuit, a leak current, and the like, do not induce wire deformation, and exhibits excellent laser marking characteristics.

Abstract: The invention relates to a bladed disk for a turbomachine, the disk including blades which extend into a conical stream and which are held in a peripheral groove of said disk by hammerhead type fasteners, each of said blades further including a platform whose radially-outer face defines the boundary of the gas flow stream and whose radially-inner face presents an upstream rib and a downstream rib disposed in planes that are perpendicular to the axis of rotation of said disk and that are radially adjacent respectively to an upstream ring and a downstream ring formed at the periphery of said disk on either side of said groove in order to provide leaktightness in these zones, wherein the thickness of the downstream rib in the axial direction is greater than the thickness of the upstream ring.

Abstract: The invention relates to a method of improving the retention capacity of a blade having an asymmetrical hammerhead connection and extending in a conical stream, with the root of the blade being retained in a peripheral groove in a disk, said groove having an upstream lip and a downstream lip presenting respective bearing surfaces that extend in planes that are asymmetrical relative to planes perpendicular to the axis of rotation of said disk, and against which the surfaces of the upstream and downstream flanks of said root come to bear, the bearing surface of said upstream lip being connected to the bottom wall of said groove via a rounded surface, and the upstream flank presenting, in the vicinity of said rounded surface, a heel situated inside a circle of radius R centered on the axis about which said blade tends to pivot when axial stress is applied thereto, said circle outlining, in the upstream lip, a crescent shape of thickness e, wherein: a) the connection between the bearing surface of the upstream

Abstract: Control lever for the angular setting of a stator blade, comprising a first end intended to be fitted in a fixed manner on a blade pivot, a second end comprising a cylindrical pin for fitting on a control ring, and a flat intermediate part connecting the first and second ends having shapes and dimensions determined in order to increase the natural frequencies of the lever in flexion and in torsion above the vibratory frequencies of the turboshaft engine upstream of the lever and in order to retain the stiffness of the lever.

Abstract: An inter-vane platform (3), for a vane support disk (1) of a turbine engine fan, comprises a central part (5) of one piece with the support disk (1) between two adjacent vanes (2), and two lateral parts (8,9), forming extensions to two lateral edges (6,7) of the central part (5), and each designed in such a way as to deflect under the impact of the vane (2) opposite which it is located.

Abstract: An interblade platform (3) for a blade support disc (1) on a turbojet blower comprises a deflecting part (4) comprising a lower face (5) provided with a first fixing lug (6) provided with a first orifice (7) for the passage of a first fixing stud (8) and a second fixing lug (9) provided with second (10) and third (11) orifices for the passage of second (12) and third (13) fixing studs. The fixing studs (8, 12, 13) are intended to fix the two fixing lugs (6, 9) to the support disc (1) between two adjacent blades (2).

Abstract: Turboshaft engine comprising two subassemblies defining between them an annular chamber housing a seal. The two subassemblies are assembled under axial stress thereby defining an annular chamber housing the seal and an interposed part is inserted between the butting surfaces of the two parts of the annular chamber.

Abstract: The invention relates to a turbojet section comprising an external casing having a surface that extends radially inwards, an internal casing having an essentially axial wall that extends toward said surface, and a seal located between said wall and said surface to prevent communication between the high and low pressure regions situated on either side of said seal, in which said seal is made in the form of an annular sheet-metal ring comprising an essentially cylindrical first part fixed in a leaktight manner to one face of the axial wall and a second part continuing from said first part and situated in the space separating said axial wall from said radial surface, said second part exhibiting, in section on a radial plane containing the axis of the turbojet, a V-shaped profile and having an end portion in leaktight sliding contact with said radial surface.

Abstract: The invention relates to a ceramic-based bushing for mounting in a turbomachine casing to provide a smooth bearing for a pivot of a variable-pitch vane. The bushing is constituted by a metal jacket and a ceramic ring secured to the inside wall of said jacket by brazing. The invention also provides a turbomachine compressor having variable-pitch stator vanes with pivots mounted in the casing by means of such bushings.

Abstract: A control lever for the pitch angle of a blade in a turbomachine, said lever having a first end intended to be mounted on a blade pivot so as to rotate it and a second end comprising a cylindrical peg for mounting on a control annulus, this peg being fixed by crimping of one of its ends in an orifice of the second end of the lever and comprising an annular flange to which is applied the second end of the lever, wherein stress distribution means are interposed between the second end of the lever and the crimped end of the peg.

Abstract: An inter-vane platform (3) for a vane support disk (1) of a fan of a turbine engine, comprising a deflecting part (4) includes a lower face (5) provided with at least one first securing foot (6), provided with at least one aperture (7) for the passage of a securing pin (8) intended to connect it to a second securing foot (12) of the support disk (1), between two adjacent vanes.

Abstract: The invention relates to a method of improving the retention capacity of a blade having an asymmetrical hammerhead connection and extending in a conical stream, with the root of the blade being retained in a peripheral groove in a disk, said groove having an upstream lip and a downstream lip presenting respective bearing surfaces that extend in planes that are asymmetrical relative to planes perpendicular to the axis of rotation of said disk, and against which the surfaces of the upstream and downstream flanks of said root come to bear, the bearing surface of said upstream lip being connected to the bottom wall of said groove via a rounded surface, and the upstream flank presenting, in the vicinity of said rounded surface, a heel situated inside a circle of radius R centered on the axis about which said blade tends to pivot when axial stress is applied thereto, said circle outlining, in the upstream lip, a crescent shape of thickness e, wherein: a) the connection between the bearing surface of the upstream li

Abstract: The invention relates to a bladed disk for a turbomachine, the disk including blades which extend into a conical stream and which are held in a peripheral groove of said disk by hammerhead type fasteners, each of said blades further including a platform whose radially-outer face defines the boundary of the gas flow stream and whose radially-inner face presents an upstream rib and a downstream rib disposed in planes that are perpendicular to the axis of rotation of said disk and that are radially adjacent respectively to an upstream ring and a downstream ring formed at the periphery of said disk on either side of said groove in order to provide leaktightness in these zones, wherein the thickness of the downstream rib in the axial direction is greater than the thickness of the upstream ring.