Patent ID: 11952901
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 10:
11. A turbomachine sealing ring having an axis of revolution and comprising:
an annular support which comprises fastening elements and/or hooking elements configured to cooperate with a stator element of the turbomachine,
an annular coating made of abradable material which is secured to said support, and
an annular thermal protection plate which is secured to said support,
said ring being sectorised and comprising a plurality of ring sectors arranged circumferentially next to one another about said axis, each ring sector comprising a support sector, a coating sector and a plate sector, each plate sector comprising a flat tab pressed against a face of the corresponding support sector and fixed to this face by brazing,
wherein said tab is inserted into a through-slot in said support sector in order to improve its integrity in operation,
and wherein said support comprises a first annular wall extending perpendicular to said axis and the outer periphery of which is connected to a second cylindrical or frustoconical wall to which said coating is fixed, and the inner periphery of which is connected to a cylindrical fastening rim, said tab of each plate sector being applied against a free face of a sector of the first wall and inserted into a through-slot in the second wall of a sector.