Abstract: A disk of a rotor including an annular radial web, a radially central hub located at the inner radial end of the web and a rim located at the outer radial end of the web, the web including an upstream face and a downstream face, and a plurality of orifices through which bolts pass for the attachment of at least one annular flange forming part of another adjacent rotor disk on either the upstream face or the downstream face of the web, or on both faces. The upstream face and/or the downstream face of the web includes a globally annular shaped indentation, with a bottom set back along the axial direction inwards into the web, and that extends radially outwards from the hub of the disk towards the rim, and that surrounds a radially inner part of each of the orifices of the web, at a distance.

Abstract: A disk of a rotor including an annular radial web, a radially central hub located at the inner radial end of the web and a rim located at the outer radial end of the web, the web including an upstream face and a downstream face, and a plurality of orifices through which bolts pass for the attachment of at least one annular flange forming part of another adjacent rotor disk on either the upstream face or the downstream face of the web, or on both faces. The upstream face and/or the downstream face of the web includes a globally annular shaped indentation, with a bottom set back along the axial direction inwards into the web, and that extends radially outwards from the hub of the disk towards the rim, and that surrounds a radially inner part of each of the orifices of the web, at a distance.

Abstract: A labyrinth disk for a turbomachine is provided. The disk includes a hub, a web and a frustoconical peripheral portion, having on one face labyrinth seal teeth and on the other face radial ribs. The flanks of the ribs delimit, between one another, channels which open out at the periphery of the disk. The width of the channels decreases from the base of the frustoconical portion to the opening at the periphery. The ribs are split close to the periphery, and a recess is created between the two flanks of one and the same rib.

Abstract: A sealing ring configured to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine, the ring including a plurality of anti-rotation pegs which prevent it from rotating in relation to the rotor disc, each peg protruding axially from a ring body and including two opposite circumferential-end surfaces, respectively configured to be located facing two directly consecutive blades carried on the rotor disc. An axially opening slot passes radially through at least one of the anti-rotation pegs.

Abstract: A sealing ring configured to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine, the ring including a plurality of anti-rotation pegs which prevent it from rotating in relation to the rotor disc, each peg protruding axially from a ring body and including two opposite circumferential-end surfaces, respectively configured to be located facing two directly consecutive blades carried on the rotor disc. An axially opening slot passes radially through at least one of the anti-rotation pegs.

Abstract: The present invention relates to a labyrinth disk for a turbomachine comprising a hub, a web and a frustoconical peripheral portion, having on one face labyrinth seal teeth and on the other face radial ribs (78?) the flanks (78?f) of which delimit, between one another, channels (80) which open out at the periphery of the disk, the width of said channels decreasing from the base of the frustoconical portion to the opening at the periphery, wherein the ribs are split close to the periphery, a recess (79?) being created between the two flanks (78?f) of one and the same rib.