| 摘要 |
Disclosed is a rotor assembly (10) for a turbomachine includes a disk (12) having a first axial face (20) and a second axial face (22). The disk (12) includes at least one circumferential dovetail (30) extending around an outer surface (32) of the disk (12) and a plurality of axial dovetails (18) extending from the first axial face (20) to the second axial face (22). Each blade (14) of a plurality of blades (14) is installed into an axial dovetail (30) of the plurality of axial dovetails (30) and each platform (16) of a plurality of platforms (16) is installed adjacent to a blade (14) of the plurality of blades (14) via the at least one circumferential dovetail (30). Further disclosed is a method of assembly of a rotor for a turbomachine. |
