Patent ID: 11952908
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. A turbine for a turbomachine comprising:
an annular row (20) of moving blades (20a) surrounded by a support ring (26) of an abradable material (24) carried by a housing (10), the ring (26) defining a radially outer face (26b),
a distributor (30) mounted downstream of the said annular row (20) of moving blades (20a) and comprising a means of attachment to a means of support of the housing (10), the said means of attachment comprising a radially outer spoiler (38) coming to bear radially inwards on a radially outer annular face (12b) of a cylindrical wall of said means of support, the said means of support further comprising a radial annular wall (14) extending radially inwards from the cylindrical wall (12) and the radial annular wall comprising a radially inner end engaged in an annular groove (28) of the ring (26), and in which a free annular space (40) is formed between the radially outer face (26b) of the ring (26) and the cylindrical wall (12) of the means of support,
in which the means of attachment of the distributor (30) comprises a radially inner spoiler (34) connected to the upstream end of a radially outer platform (32) of the distributor (30), the radially inner spoiler (34) coming to bear on a radially inner face (26a) of the support ring (26) of abradable material (24).