Abstract: A fan blisk for a turbomachine, the blisk comprising a hub delimited by an upstream face and a downstream face in addition to an outer peripheral face and a revolving inner peripheral face delimiting an inner opening, the hub carrying blades each having a leading edge and a trailing edge, the hub and the blades forming a one-piece assembly. The upstream face and/or the downstream face is offset, being located along the axis of rotation (AX) between the leading edges and the trailing edges of the blades, the blisk (bladed disk) comprising a filling member mounted on the offset face, the filling member comprising an inner centring ferrule engaging in the inner face of the hub, a radial portion resting against the offset face and an outer ferrule extending the outer peripheral face of the hub.

Abstract: Relates to a vane for a turbomachine. The vane (12?) has a blade (13?) and a root (18?) to be engaged in an axial groove in a disc of the turbomachine. The upstream end (450?) of the root is connected to a radially internal end (430?) of the leading edge (431?) of the blade by the upstream end of a connecting zone having a discontinuity towards the downstream end, so that said radially internal end of the leading edge of the blade is situated further downstream than the upstream end of the root.

Abstract: The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream (26) at the radially inner ends of the leading edges of the fan blades (10), divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.

Abstract: The invention relates to a fan, in particular for a small turbine engine such as a jet engine, having a hub ratio corresponding to the ratio of the diameter of the inner limit of the air intake section (26) at the radially internal ends of the leading edges of the fan blades (10), divided by the diameter of the circle through which the outer ends of the fan blades pass, which has a value of 0.25 to 0.27.

Abstract: The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream at the radially inner ends of the leading edges of the fan blades, divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.

Abstract: The invention relates to an assembly for a turbomachine comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade with a smaller length than the first blade (20), and a damping device (4) attached to the second rotor module (3) and comprising a radial external surface (40) supported with friction against the first module (2), so as to couple the modules (2, 3) for the purpose of damping their respective vibrational movements during operation.

Abstract: The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a disk (21), a first blade (20) being mounted on the external periphery of the disk (21), the first blade (20) comprising a platform (25) and a support (27), a second rotor module (3), connected to the first rotor module (2) by means of at least two attachments (22) and comprising a second blade of smaller length than the first blade (20), and a damping device (4) attached to the attachment (22) between the first (2) and the second (3) rotor module so as to dampen their vibrational movements during operation, and comprising: a head (40) comprising a first radial external surface (42) supported with friction against the platform (25), and two attachment feet (41) extending on either side of the support (27) of the first blade (20).

Abstract: A fan blisk for a turbomachine, the blisk comprising a hub delimited by an upstream face and a downstream face in addition to an outer peripheral face and a revolving inner peripheral face delimiting an inner opening, the hub carrying blades each having a leading edge and a trailing edge, the hub and the blades forming a one-piece assembly. The upstream face and/or the downstream face is offset, being located along the axis of rotation (AX) between the leading edges and the trailing edges of the blades, the blisk (bladed disk) comprising a filling member mounted on the offset face, the filling member comprising an inner centring ferrule engaging in the inner face of the hub, a radial portion resting against the offset face and an outer ferrule extending the outer peripheral face of the hub.

Abstract: The invention relates to a single-piece fan blisk (14) for a turbojet, this blisk (14) comprising a hub (16) with a general shape of revolution about a rotation axis (AX) and comprising an external peripheral face (18) of revolution extending radially towards the rotation axis at an upstream face (19) and a downstream face both of which are in the form of rings. This hub (16) supports radially oriented blades (17) at its external peripheral face (18), each comprising a base through which it is connected to this external peripheral face (18), each blade (17) having a leading edge (22) and a trailing edge (23) that are radially oriented. The spacing between the upstream face (19) and the downstream face of the hub (16) along the rotation axis (AX) is less than the distance separating the leading edge (22) from the trailing edge (23) of each blade.

Abstract: Relates to a vane for a turbomachine. The vane (12?) has a blade (13?) and a root (18?) to be engaged in an axial groove in a disc of the turbomachine. The upstream end (450?) of the root is connected to a radially internal end (430?) of the leading edge (431?) of the blade by the upstream end of a connecting zone having a discontinuity towards the downstream end, so that said radially internal end of the leading edge of the blade is situated further downstream than the upstream end of the root.

Abstract: The invention relates to a blade, the platform (14) of which has at least one bumper (40) which rises, on the inner face, from a connection to an intermediate area of the blade located along a longitudinal axis of the blade, between the blade root and the outer face (143), towards a free side edge (145) of the platform. The platform bumper (40) locally has a thinned portion at a distance from said free side edge of the platform. The invention is applicable to turboshaft engine fans.

Abstract: The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream (26) at the radially inner ends of the leading edges of the fan blades (10), divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.

Abstract: A fan rotor including a disk carrying blades including roots engaged in slots in the disk, a frustoconical cap mounted on the disk upstream from the blades, and a retaining mechanism axially retaining the blades on the disk and including a ring mounted in an annular groove of the disk and forming an abutment for the roots of the blades, the ring being festooned or crenellated and co-operating with a festooned radial annular bead of the annular groove of the disk, and a mechanism preventing the ring from moving in rotation, which includes an annulus carrying at least one axial tooth inserted in hollow portions of the bead of the disk and of the ring, the annulus being fastened by bolts on an upstream radial face of the disk.

Abstract: The invention relates to a fan, in particular for a small turbine engine such as a jet engine, having a hub ratio corresponding to the ratio of the diameter of the inner limit of the air intake section (26) at the radially internal ends of the leading edges of the fan blades (10), divided by the diameter of the circle through which the outer ends of the fan blades pass, which has a value of 0.25 to 0.27.

Abstract: A helical ring including a polygonal body and a plurality of cylindrical radial housings arranged in the body is provided. Each housing includes a surface adapted to receive a support of a blade of a helix. The surface of each housing is arranged on a radially internal surface of a corresponding hub. Each hub is a separate piece attached to the body of the ring, intended to be received in a radial housing of the body of the ring. The hub includes two projecting pins relative to its external surface to be fastened to the edges of a housing of the annular body, the two projecting pins forming a centering axis.

Abstract: The invention relates to a single-piece fan blisk (14) for a turbojet, this blisk (14) comprising a hub (16) with a general shape of revolution about a rotation axis (AX) and comprising an external peripheral face (18) of revolution extending radially towards the rotation axis at an upstream face (19) and a downstream face both of which are in the form of rings. This hub (16) supports radially oriented blades (17) at its external peripheral face (18), each comprising a base through which it is connected to this external peripheral face (18), each blade (17) having a leading edge (22) and a trailing edge (23) that are radially oriented. The spacing between the upstream face (19) and the downstream face of the hub (16) along the rotation axis (AX) is less than the distance separating the leading edge (22) from the trailing edge (23) of each blade.

Abstract: A variable pitch blade propeller hub for a turbomachine with a longitudinal axis includes a polygonal ring supporting the blades, concentric with the longitudinal axis and including two spaced parallel annular end flanges between which are diametrically fastened, by root areas arising from the annular flanges, collars with cylindrical radial housings to receive the blades. The collars are equi-angularly distributed at the lateral periphery of the polygonal ring and separated from each other by intermediate areas with through-openings. The also includes connectors connecting the polygonal ring to a turbine rotor element of the turbomachine. The intermediate areas defined between two concentric collars and the annular end flanges include elements for reinforcing the collars that are arranged radially and/or tangentially and fastened at least to the lateral walls of two consecutive collars.

Abstract: A prestressing device extending about an axis between a first plane and a second plane, the first plane being located at a predetermined distance from the second plane, each plane being perpendicular to the axis. The device includes at least three deformation areas. The deformation areas extend in the first plane. The device further includes, between each deformation area, a planar contact surface extending in the second plane.

Abstract: An anti-rotation device for a nut in tightened position on a male part, includes a plurality of upper notches provided on one end of the nut, the upper notches extending along a longitudinal axis of the nut, a plurality of lower notches provided in one peripheral zone of the male part, the lower notches extending along a longitudinal axis of the male part, and the lower and higher notches at least partially overlapping when the nut is in tightened position on the male part, a ring including at least one locking component accommodated both in one of the lower notches of the male part and in one of the higher notches of the nut.

Abstract: An assembly in a turbine engine for controlling plural toothed pivotally-mounted blades arranged in azimuth around the axis of the turbine engine and including an actuator ring controlling a position of the blades. Racks mounted on the ring present corresponding sets of teeth meshing with the set of teeth of a respective one of the blades to place it in a selected angular position, and they are held in the radial direction by radial positioning mechanism fastened to the blade. Each rack is mounted on the ring by plural guides spaced apart circumferentially around the ring, that connect together movements of the rack and of the ring in the circumferential direction, and that are configured to slide relative to the ring, for each guide in its own radial direction, and relative to the rack in a direction of movement that is substantially radial and specific to the rack.