| 摘要 |
The invention relates to a rotor (R), of a multi-staged axial compressor (ACO), which extends along an axis of rotation (X), wherein the rotor (R) has a shaft (SH), wherein the shaft (SH) has rotor blade slots (RBG), wherein rotor blades (RB) of the rotor (R) which are arranged next to one another in the circumferential direction (CD) and are each secured to the rotor blade slots (RBG) by means of a blade root (RBF) form a respective rotor blade stage (RBS), wherein at least two rotor blade stages (RBS) are provided in axial succession and an interspace slot (IG), extending in the circumferential direction, is provided in the shaft (SH) axially between the two rotor blade stages (RBS), wherein the rotor blade slots (RBG) open into the interspace slots (IG) and this arrangement is designed such that blade roots (RBF) of the rotor blades (RB) can be inserted radially into the interspace slots (IG) and can be pushed thence into the rotor blade slots (RBG). In order to improve the aerodynamics and to simplify installation, it is proposed that the rotor (R) has an interspace cover (IC) which covers the interspace slots (IG), wherein the interspace cover (IC) is designed segmented into interspace cover segments (ICS) in the circumferential direction (CD). |
