公开(公告)号：US11536157B2

公开(公告)日：2022-12-27

申请号：US16955518

申请日：2018-12-18

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Philippe Gérard Edmond Joly ,  François Jean Comin ,  Charles Jean-Pierre Douguet ,  Laurent Jablonski ,  Romain Nicolas LaGarde ,  Jean-Marc Claude Perrollaz

IPC分类号： F01D25/04

摘要： The invention relates to an assembly (1) for a turbomachine comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade with a length less than the first blade (20), and a damping device (4) extending with at least one component along a turbomachine longitudinal axis (X-X), characterized in that the damping device (4) is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device (4) comprises a first radial external surface (40) supported with friction against the first module (2) as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) in order to damp their respective vibrational movements during operation.