Labyrinth sealing joint for an aircraft turbomachine

A labyrinth sealing joint for a turbomachine, comprising a rotor element extending around an axis, and a stator element extending around the rotor element, the rotor element comprising:

• two annular lips extending radially outwards and surrounded by at least one abradable element carried by said stator element;
• a plurality of gas passage cavities being arranged circumferentially next to one another between the two annular lips, the two annular lips being interconnected by connecting partitions, at least one of said annular lips comprising at least one axial gas passage opening that leads into at least some of said gas passage cavities, and said connecting partitions extending axially between the annular lips and defining therebetween sectors of spaces for gas passage,
• wherein said sectors of spaces are divided by separation walls to form said gas passage cavities, and
• wherein said rotor element comprises a disc having an outer periphery connected to two annular flanges, respectively upstream and downstream, the outer periphery comprising an outer cylindrical surface on which said two annular lips are protrudingly formed.