| 摘要 |
The invention relates to a set (1) of rotor discs (19, 20, 21) for a turbomachine such as an aircraft turbojet or turboprop engine, comprising rotor discs (19, 20, 21) which are rigidly connected and formed at their external periphery with cavities (3) in which to mount blade roots. Each disc (19, 20, 21) is formed of a rim (22) extending radially and having no axial flange, two consecutive discs being connected using an axially extending shell ring (24) fixed to the rims (22) of the discs and fitted with a clamping plate (30) to hold the blade roots of the disc (20, 21) downstream. |
