Abstract: A method for refitting blade shrouds of a rotor wheel in an aircraft turbomachine is described. The rotor wheel has a disc bearing blades that each have an airfoil extending between a root and a shroud, the shroud of each blade having lateral edges including shapes complementary to the lateral edges of the shrouds of the adjacent blades. The lateral edges of the shrouds are interlocked in engagement with one another such that anti-wear coatings of these edges are in contact with one another in a desired interlocking engagement position, and at least one of the lateral edges of at least one of the shrouds being able to be disengaged from the lateral edge of an adjacent shroud in an undesired disengagement position. The method includes, when an undesired disengagement position is detected, a step of inserting a re-engagement device into the turbomachine.

Abstract: A method for refitting blade shrouds of a rotor wheel in an aircraft turbomachine is described. The rotor wheel has a disc bearing blades that each have an airfoil extending between a root and a shroud, the shroud of each blade having lateral edges comprising including shapes complementary to the lateral edges of the shrouds of the adjacent blades. The lateral edges of the shrouds are interlocked in engagement with one another such that anti-Wear coatings of these edges are in contact With one another in a desired interlocking engagement position, and at least one of the lateral edges of at least one of the shrouds being able to be disengaged from the lateral edge of an adjacent shroud in an undesired disengagement position. The method includes, when an undesired disengagement position is detected, a step of inserting a re-engagement device into the turbomachine.

Abstract: A turbine unit for an aircraft turbine engine, comprises a rotor disc (17) axially continued by a rim (36) and carrying rotary blades (18) defining together with the disc (17) channels for air flow (43); an annular flange (33) including a bearing end (34) and defining together with the rim (36) an air passage (42) communicating with the channels for air flow (43); a member (32) for axially retaining the blades applied against the disc (17) by the bearing end (34), this turbine unit being characterised in that at least one element, out of the retaining member (32) and the flange (33), comprises a groove (44) formed facing the other element, out of the retaining member (32) and the flange (33), and into which a sealing joint (45) against which the other element axially bears is inserted.

Abstract: A turbine unit for an aircraft turbine engine, comprises a rotor disc (17) axially continued by a rim (36) and carrying rotary blades (18) defining together with the disc (17) channels for air flow (43); an annular flange (33) including a bearing end (34) and defining together with the rim (36) an air passage (42) communicating with the channels for air flow (43); a member (32) for axially retaining the blades applied against the disc (17) by the bearing end (34), this turbine unit being characterised in that at least one element, out of the retaining member (32) and the flange (33), comprises a groove (44) formed facing the other element, out of the retaining member (32) and the flange (33), and into which a sealing joint (45) against which the other element axially bears is inserted.