Turbine for a turbomachine, such as an aeroplane turbofan or turboprop engine

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).