Rotor, axial compressor, installation method

Patent metadata

Field	Value
Publication number	US-10830253-B2
Application number	US-201515531454-A
Country	US
Kind code	B2
Filing date	Nov 3, 2015
Priority date	Dec 4, 2014
Publication date	Nov 10, 2020
Grant date	Nov 10, 2020

Abstract

A rotor of a multi-staged axial compressor which extends along an axis of rotation. The rotor has a shaft which has rotor blade slots. Rotor blades of the rotor are arranged next to one another in the circumferential direction and are each secured to the rotor blade slots by a blade root to form a respective rotor blade stage. At least two rotor blade stages are provided in axial succession and an interspace slot, extending in the circumferential direction, is provided in the shaft axially between the two rotor blade stages. The rotor blade slots open into the interspace slots and blade roots of the rotor blades are insertable radially into the interspace slots and can be pushed into the rotor blade slots. The rotor has an interspace cover which covers the interspace slots, wherein the interspace cover is designed segmented into interspace cover segments in the circumferential direction.

First claim

The invention claimed is:

1. A rotor of a multi-stage axial compressor, which extends along an axis of rotation, with axial, radial and circumferential directions existing relative to the axis of rotation, the rotor comprising:
a shaft, wherein the shaft has rotor blade grooves,
rotor blades, wherein the rotor blades of the rotor which are arranged next to one another in the circumferential direction and are each fastened to a respective rotor blade groove by means of a blade root defining a respective rotor blade stage,
wherein at least two rotor blade stages are provided in axial succession, and an interspace groove, extending in the circumferential direction, is provided in the shaft axially between the two rotor blade stages, wherein the rotor blade grooves open into the interspace groove and are designed such that each respective blade root is are insertable radially into the interspace groove and pushed from there into the respective rotor blade groove, and
an interspace cover which covers the interspace groove,
wherein the interspace cover is designed segmented into interspace cover segments in the circumferential direction,
wherein the interspace cover segments are fastened in a form-fitting manner to the shaft,
wherein the shaft is an integral component over at least one axial portion of the two rotor blade stages and the interspace groove, and the interspace groove is formed by a turning process performed on the integral component,
wherein the interspace groove at least partially has, extending in the circumferential direction, a first undercut which is formed so as to interact in a form-fitting manner in the radial direction with a second undercut of the interspace cover segments in a manner blocking movement of the interspace cover segments in the radial direction.

2. The rotor as claimed in claim 1 ,
wherein the interspace cover covers the interspace groove such that a substantially continuously radial transition is produced in the axial direction of a radially outer surface between the rotor blade stage positioned upstream and the interspace cover, and between the interspace cover and the rotor blade stage positioned downstream.

3. The rotor as claimed in claim 1 ,
wherein the interspace cover is configured to secure the rotor blades against axial displacement in their respective rotor blade groove in an end position.

4. The rotor as claimed at least in claim 1 ,
wherein at least one interspace lock piece is provided for the interspace groove, which interspace lock piece is arranged at a certain first circumferential position of the interspace groove at which at least one of the interspace groove and the interspace lock piece is designed to avoid interaction of the undercuts for allowing radial insertion of the interspace cover segments.

5. The rotor as claimed in claim 4 ,
wherein the interspace groove does not have the first undercut at the certain first circumferential position.

6. The rotor as claimed in claim 1 ,
wherein the interspace cover segments and/or an interspace lock piece are fastened to the shaft by means of at least one screw.

7. An axial compressor comprising:
a rotor as claimed in claim 1 .

8. A method for installing a rotor of an axial compressor as claimed in claim 1 , the method comprising:
a) providing the shaft,
b) inserting the blade roots of the rotor blades radially into the interspace groove,
c) pushing the blade roots of the rotor blades axially into the rotor blade grooves,
d) installing the interspace cover segments on the shaft in a form-fitting manner to secure the axial position of the blade roots of the rotor blades in the rotor blade grooves.

Assignees

• Siemens Ag

Inventors

• Hermes Viktor
• Montante Rosario
• Muranyi Erich

Classifications

• F01D5/32

  Locking, e.g. by final locking blades or keys · CPC title

• F01D5/30 Primary

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• F01D5/022 Primary

  with concentric rows of axial blades · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F04D29/644 Primary

  especially adapted for elastic fluid pumps · CPC title