Labyrinth seal arrangement for aircraft turbine

The invention relates to a labyrinth seal device for an aircraft turbomachine, the device comprising:-a rotor comprising at least one outer annular lip (12a, 12b), and-a stator comprising an annular coating (16) made of a wear resistant material, the annular coating extending around the lip (12a, 12b) and being configured to cooperate in operation with the lip (12a, 12b), the invention relates to a rotor (10) having a lip (12a, 12b) for forming a labyrinth seal with respect to an airflow flowing axially from upstream to downstream through the rotor, the coating (16) having:-an inner cylindrical surface (30a, 30b) extending around the lip (12a, 12b) and being contactable with the lip to form an annular groove by friction; and a preformed annular slot (32a, 32b) upstream of the lip (12a, 12b). 本发明涉及一种用于飞行器涡轮机的迷宫式密封装置，该装置包括：-转子，转子包括至少一个外部环形唇部(12a，12b)，和-定子，定子包括由耐磨材料制成的环形涂层(16)，环形涂层围绕唇部(12a，12b)延伸并且环形涂层被构造成在运作中与唇部(12a，12b)配合，以相对于轴向地从上游到下游流动通过转子的气流形成迷宫式密封，涂层(16)具有：-内圆柱形表面(30a，30b)，内圆柱形表面围绕唇部(12a，12b)延伸并且能够与唇部接触以通过