Labyrinth disk for a turbomachine
View Patent ↗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.
1. A labyrinth disk for a turbomachine comprising:
a hub;
a web; and
a frustoconical peripheral portion, the frustoconical peripheral portion including labyrinth seal teeth on an outer face and radial ribs distributed circumferentially on an inner face,
wherein flanks of the ribs delimit, between one another, channels which open out at a downstream periphery of the disk at a downstream end of the frustoconical portion, a width of said channels decreasing from a base at an upstream end of the frustoconical portion to an opening at the downstream periphery of the disk,
wherein a recess is created between two flanks of one of the ribs at the downstream periphery of the disk, the recess opening out at the downstream periphery of the disk.
2. The labyrinth disk as claimed in claim 1 , bases of the flanks are radiused in shape.
3. The labyrinth disk for a turbomachine as claimed in claim 2 , wherein a radius of curvature of the base of the flank on a recess side is different from a radius of curvature of the base of the flank on a channel side.
4. The labyrinth disk as claimed in claim 1 , wherein a height of the flanks on a recess side with respect to a bottom of said recess is the same as a height of the flanks on a ventilation channel side with respect to the bottom of said recess.
5. The labyrinth disk as claimed in claim 1 , wherein a width of the rib including the recess at the downstream periphery of the disk is the same as a width of one of the ribs at the base at the upstream end of the frustoconical portion.
6. A turbine rotor comprising a turbine disk and blades mounted on a rim of the turbine disk, wherein a labyrinth disk as claimed in claim 1 is mounted on the turbine disk and creates blade ventilation channels.
7. The rotor as claimed in claim 6 , wherein the labyrinth disk comprises a cover which creates said ventilation channels.
8. The rotor as claimed in claim 6 , comprising an upstream flange for axially locking the blades, wherein the labyrinth disk is wedged against a radially inward edge of the upstream flange.
9. A gas turbine engine comprising a turbine rotor as claimed in claim 6 .