Abstract: Sealing ring for a wheel of an aircraft turbomachine turbine, the ring having an annular body extending around an axis of revolution and including an outer surface and an inner surface which is coated with an annular layer of an abradable material, the ring further including an annular wall extending around the annular body and at a radial distance from the body, the annular wall including openings through which cooling air flows by impact on the outer surface, wherein the body and the wall are integrally formed.

Abstract: Sealing ring (36, 38) for a wheel (26) of an aircraft turbomachine turbine, said ring comprising an annular body (51) extending around an axis of revolution (A) and comprising an outer surface (51a) and an inner surface (51b) which is coated with an annular layer (53) of an abradable material, the ring further comprising an annular wall (52) extending around the annular body and at a radial distance from said body, said annular wall comprising openings (54) through which cooling air flows by impact on the outer surface, characterised in that the body and the wall are integrally formed.

Abstract: A module for an aircraft turbine engine including at least one annular casing of an annular combustion chamber, at least one sealing ring for a turbine wheel, and at least one annular bearing support, wherein this module is made in one piece.