Abstract: An angular diffuser sector for a turbine engine compressor is provided. The sector includes an inner shroud; an outer shroud; a vane; a casing element mounted at least in part around one of the shrouds and having an open groove facing an axial end of the corresponding shroud; a wedge-forming fitting interposed between the casing element and the corresponding shroud, the wedge presenting a first surface that contacts with a bearing surface of the axial end of the corresponding shroud, and a second surface that is inclined relative to the first surface and that contacts with a corresponding sloping surface of the groove in the casing element; and a device that exerts an axial force on the wedge so as to keep its first surface in contact with the bearing surface and its second surface in contact with the sloping surface of the groove in the casing element.

Abstract: A stator angular sector for a turbine engine compressor including: an outer shroud and an inner shroud, and at least one vane extending radially between the shrouds. The outer shroud includes first and second mounting mechanisms for mounting the stator angular sector on a casing of the engine, which mechanisms are oriented parallel to the axis in opposite directions and connected together by an intermediate portion. The outer shroud includes at least one axial end portion extending from the intermediate portion with which at least one damper-forming insert is configured to come into contact, such that beyond a given value for amplitude of vibration of the end portion, the damper insert and the end portion are configured to move relative to each other to vary total moving mass moving with the end portion, thereby modifying vibratory behavior of the end portion.

Abstract: A stator angular sector for a turbine engine compressor and including: an outer shroud and an inner shroud; and at least one vane extending radially between the shrouds and connected thereto at its radial ends. At one of its axial ends the outer shroud includes a cavity opening out to the axial end and extending between a radially-inner tongue of the outer shroud to which the radially-outer end of the vane is connected and a radially-outer tongue of the outer shroud carrying a mounting mechanism for mounting the stator angular sector to a casing of the engine. An abutment-forming insert is housed at least in part in the cavity, the abutment-forming insert configured to limit radial movements of the radially-inner tongue by contact and thus to modify vibratory behavior of the radially-inner tongue.

Abstract: The invention provides an angular diffuser sector (16) for a turbine engine compressor, the sector comprising an inner shroud (20), an outer shroud (22), at least one vane (24), a casing element (36?) mounted at least in part around one of the shrouds and having an open groove (42) facing an axial end of the corresponding shroud, a wedge-forming fitting (44) interposed between the casing element and the corresponding shroud, the wedge presenting a first surface (46) for coming into contact with a bearing surface (22a) of the axial end of the corresponding shroud, and a second surface (48) that is inclined relative to the first surface and that is to come into contact with a corresponding sloping surface (50) of the groove in the casing element, and means (52) for exerting an axial force on the wedge so as to keep its first surface in contact with the bearing surface and its bearing surface in contact with the sloping surface of the groove in the casing element.

Abstract: The invention relates to a device (30) for blockage of vanes in a circumferential groove (10) of a turbine engine disc, the device being intended to deploy in a radial direction to be locked in the circumferential groove open radially. According to the invention, the blocking device comprises a first and a second piece (32, 34) designed to deploy in the radial direction by relative displacement of these pieces in the circumferential direction (23).

Abstract: A device for axial retention of mobile vanes mounted on a rotor disc includes two open rings, superimposed. At least one of the rings includes a rotating stop mechanism configured to cooperate with at least one hook of the disc. The two open rings are mounted in a discontinuous groove formed in the hooks, at the end of teeth situated on the periphery of the rotor disc, such that the rotating stop mechanism of the first ring is placed in the opening of the second ring. The significance of contact surfaces between the two rings allows a damping of vibrations during operation.

Abstract: A stator angular sector for a turbine engine compressor including: an outer shroud and an inner shroud, and at least one vane extending radially between the shrouds. The outer shroud includes first and second mounting mechanisms for mounting the stator angular sector on a casing of the engine, which mechanisms are oriented parallel to the axis in opposite directions and connected together by an intermediate portion. The outer shroud includes at least one axial end portion extending from the intermediate portion with which at least one damper-forming insert is configured to come into contact, such that beyond a given value for amplitude of vibration of the end portion, the damper insert and the end portion are configured to move relative to each other to vary total moving mass moving with the end portion, thereby modifying vibratory behavior of the end portion.

Abstract: A stator angular sector for a turbine engine compressor and including: an outer shroud and an inner shroud; and at least one vane extending radially between the shrouds and connected thereto at its radial ends. At one of its axial ends the outer shroud includes a cavity opening out to the axial end and extending between a radially-inner tongue of the outer shroud to which the radially-outer end of the vane is connected, and a radially-outer tongue of the outer shroud carrying a mounting mechanism for mounting the stator angular sector to a casing of the engine. An abutment-forming insert is housed at least in part in the cavity, the abutment-forming insert configured to limit radial movements of the radially-inner tongue by contact and thus to modify vibratory behavior of the radially-inner tongue.

Abstract: A stator stage of a compressor of a turbomachine including an annular row of variable-pitch vanes is disclosed. Each vane includes an external cylindrical pivot defining the axis of rotation of the vane, and an internal cylindrical pivot mounted in a housing of an internal ring. The internal pivot of each vane extends along an axis substantially parallel to the axis of rotation of the vane and at a distance from this axis, and is mounted in the housing of the ring by a swiveling or a tilting system.

Abstract: The invention relates to a device (30) for blockage of vanes in a circumferential groove (10) of a turbine engine disc, the device being intended to deploy in a radial direction to be locked in the circumferential groove open radially. According to the invention, the blocking device comprises a first and a second piece (32, 34) designed to deploy in the radial direction by relative displacement of these pieces in the circumferential direction (23).

Abstract: A split ring for mounting with elastic prestress in an annular groove of a rotary part of a turbomachine and having, in the free state, a diameter that is greater than the diameter of the groove, is remarkable in that, in the free state and without stress, the end portions of the ring are circular arcs having a radius of curvature that is substantially equal to the radius of curvature of the annular groove.

Abstract: A turbomachine variable-pitch stator blade is disclosed. The stator blade includes an aerofoil, extended on one side by a pivot by which it is mounted so as to rotate in a bore of the casing of the turbomachine, and a plate, between the aerofoil and the pivot, perpendicular to the line formed by the aerofoil and the pivot. Since the face of the plate opposite to the aerofoil includes a first zone and a second zone, the first zone being subjected to an intense friction with the wall of the casing because of the transverse forces applied to the aerofoil, the thickness of the plate on the second zone is reduced relative to the thickness of the plate of the first zone. Therefore, it is possible to reduce the weight of the blade without loss of performance.

Abstract: A device for axial retention of mobile vanes mounted on a rotor disc includes two open rings, superimposed. At least one of the rings includes a rotating stop mechanism configured to cooperate with at least one hook of the disc. The two open rings are mounted in a discontinuous groove formed in the hooks, at the end of teeth situated on the periphery of the rotor disc, such that the rotating stop mechanism of the first ring is placed in the opening of the second ring. The significance of contact surfaces between the two rings allows a damping of vibrations during operation.

Abstract: An assembly of sectorized fixed compressors for a turbomachine compressor is disclosed. The assembly is a single piece and includes two coaxial rings connected by radial airfoils. The outer ring includes two annular mounting lugs on a casing of the compressor. At least one of these annular lugs is connected to the outer ring in a zone axially separate from the zone for connecting the leading edges or trailing edges of the airfoils to the outer ring.

Abstract: A turbomachine rotor blade comprising a root (14) mounted in a channel of the periphery of a disk and held by an annular flange (18) which presses on the root (14) of the blade (12), this root comprising a stop (44) engaging in a matching cavity of the flange in order to stop it rotating about the axis of the disk, the central portion of the stop having a thickness less than that of the ends of the stop.

Abstract: The present invention relates to a turbomachine variable-pitch stator blade comprising an aerofoil (12), extended on one side by a pivot (14) by which it is mounted so as to rotate in a bore of the casing (3) of the turbomachine, and a plate (13), between the aerofoil and the pivot, perpendicular to the line formed by the aerofoil and the pivot. The blade is characterized in that, since the face of the plate opposite to the aerofoil comprises a first zone (20) and a second zone (22), the first zone (20) being subjected to an intense friction with the wall of the casing (3) because of the transverse forces applied to the aerofoil (12), the thickness of the plate on the second zone (22) is reduced relative to the thickness of the plate of the first zone (20). The invention makes it possible to reduce the weight of the blade without loss of performance.

Abstract: A split ring for mounting with elastic prestress in an annular groove of a rotary part of a turbomachine and having, in the free state, a diameter that is greater than the diameter of the groove, is remarkable in that, in the free state and without stress, the end portions of the ring are circular arcs having a radius of curvature that is substantially equal to the radius of curvature of the annular groove.

Abstract: A stator stage of a compressor of a turbomachine, comprising an annular row of variable-pitch vanes, each vane comprising an external cylindrical pivot defining the axis of rotation of the vane, and an internal cylindrical pivot mounted in a housing of an internal ring, the internal pivot of each vane extending along an axis substantially parallel to the axis of rotation of the vane and at a distance from this axis, and being mounted in the housing of the ring by a swiveling or a tilting system.

Abstract: A turbomachine rotor blade comprising a root (14) mounted in a channel of the periphery of a disk and held by an annular flange (18) which presses on the root (14) of the blade (12), this root comprising a stop (44) engaging in a matching cavity of the flange in order to stop it rotating about the axis of the disk, the central portion of the stop having a thickness less than that of the ends of the stop.

Abstract: An assembly of sectorized fixed compressors (50) for a turbomachine compressor, this assembly being made in a single piece and comprising two coaxial rings (20, 52) connected by radial airfoils (24), the outer ring comprising two annular mounting lugs (56, 66) on a casing of the compressor, at least one of these annular lugs being connected to the outer ring in a zone axially separate from the zone for connecting the leading edges (26) or trailing edges (28) of the airfoils to the outer ring.