Abstract: The invention relates to a ring (1) for a turbomachine turbine or a turboshaft engine turbine, intended to surround an impeller (2) of a turbine rotor, the said ring (1) extending circumferentially about an axis and comprising an annular and continuous support part (9), radially external, and a part (10) delimiting a circulation passage (6) of a gas flow, radially internal and comprising a plurality of angular segments (13) distributed over the periphery and situated adjacent to one another so as to form an annular part delimiting the passage (6), characterised in that circumferential clearances (j) are formed between the circumferential ends of the adjacent segments (13) located opposite each other, each segment (13) being connected to the support part (9) by means of a connecting zone (14), an annular channel (15) for the circulation of cooling fluid being delimited radially between the outer support part (9) and the inner part (10) delimiting the passage.

Abstract: A method for manufacturing a compressor impeller or rotor including a hub that carries blades, involving a step of manufacturing a hub which includes all or some of the blades, and a step of additive manufacture by adding localised material using a method such as the LMD process to form or finish each blade.