Rotation blocking device for use in turbomachine rotor of aircraft engine, has ring with split and set of cleat, which is arranged on ring and placed in groove of rotor disk that includes blocking hook with check face

The device has a ring (20) for retaining blades on a rotor disk of a turbomachine. The rotor disk (10) provides a set of blocking hooks (162, 164) that spread around a circumference and defines a groove for placing the ring. The ring is provided with a split and a set of cleat (302, 304), which is arranged on the ring and placed in the groove. The cleat is compressed against one blocking hook and the split is covered by another blocking hook. The former hook is provided with a check face that cooperates with a contact face brings the cleat next to the split. Independent claims are also included for the following: (1) a ring for retaining the blades of a turbomachine rotor (2) a disk/ring assembly of a turbomachine (3) a turbomachine rotor (4) an aircraft engine. Le dispositif d'immobilisation en rotation d'un anneau de rétention (20) sur un disque de rotor (10) comporte :- un premier (162, 262) et un deuxième (164, 264) crochets d'immobilisation successifs du disque (10),- au moins un taquet (302, 304, 306) dudit anneau de rétention (20), disposé près d'une fente (24) de l'anneau (20).La position dudit au moins un taquet (302, 304, 306) sur ledit anneau de rétention (20) est telle que, lorsque ledit anneau de rétention (20) est en place dans une gorge (22) située sur le disque de rotor (10), ledit au moins un taquet (302, 304, 306) est en butée contre ledit premier crochet d'immobilisation (162, 262), et la fente (24) est recouverte par ledit deuxième crochet d'immobilisation (164, 264).