Turbomachine and Method of Dismantling a Portion Thereof

Abstract

A turbomachine (2) has a combustion chamber (1), in particular a gas turbine, with a casing (8) which has a closable maintenance opening at least in the region of the combustion chamber (1), which maintenance opening, in the open state, provides access to an outer carrier (3), an inner segment carrier (5), and a front plate (4), which together define the combustion chamber (1). In order to simplify the maintenance of the turbomachine (2) and thereby reduce any downtimes and maintenance costs, the outer carrier (3), the inner segment carrier (5) and the front plate (4) are designed as annular shell elements (13) having a respective bottom half shell (14) and a respective top half shell (15) which can be connected thereto. In the assembled state, the outer carrier (3), the inner segment carrier (5), and the front plate (4) are connected to one another and/or to the casing (8) via connecting contours (7) which are axially releasable from one another.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

Preferred exemplary embodiments of the invention are shown in the drawings and described in more detail below, the same reference numerals designating the same or similar or functionally identical components.

In the drawings, in each case in a highly schematic manner,

FIG. 1 shows a cross section through a combustion chamber,

FIG. 2 shows an axial section of a turbomachine with closed casing,

FIG. 3 shows an illustration as in FIG. 2, but with open casing in the region of the combustion chamber and with visible top half shell of the outer carrier,

FIG. 4 shows an illustration as in FIG. 3, but with removed top half shell of the outer carrier and with auxiliary tool arranged on the rotor,

FIG. 5 shows an illustration as in FIG. 4, but with slightly rotated rotor,

FIG. 6 shows an illustration as in FIG. 4, but with rotor rotated by 180°.

Claims

1. A turbomachine comprising: a combustion chamber including an outer carrier, an inner segment carrier, and a front plate together defining the combustion chamber, the outer carrier, inner segment and front plate comprising connecting contours which are axially releasable from one another;a casing including a closable maintenance opening at least in the region of the combustion chamber, which maintenance opening, in an open state, provides access to the outer carrier, the inner segment carrier, and the front plate;wherein the outer carrier, the inner segment carrier, and the front plate comprise annular shell elements;wherein the shell elements each include a bottom half shell and a top half shell which is configured and arranged to be connected to the bottom half shell; andwherein the outer carrier, the inner segment carrier, and the front plate, when in an assembled state, are connected to one another, to the casing, or to both, by the connecting contours.

2. The turbomachine as claimed in claim 1, wherein at least one of the connecting contours comprises an axially open circumferential groove or a circumferential tongue.

3. The turbomachine as claimed in claim 1, wherein at least one of the connecting contours comprises a step.

4. The turbomachine as claimed in claim 1, wherein the top half shells are configured and arranged to be displaced axially and removed radially relative to a rotor of the turbomachine for dismantling.

5. The turbomachine as claimed in claim 1, wherein the bottom half shells are configured and arranged to be axially displaced and rotated upward about the rotor axis.

6. The turbomachine as claimed in claim 1, wherein the inner segment carrier, the outer carrier, and the front plate each comprise a heat-resistant layer.

7. A method of dismantling an element of a turbomachine, the element including an annular shell element including a bottom half shell and a top half shell which can be connected to the bottom half shell, the method comprising: opening a casing of the turbomachine in the region of a combustion chamber;releasing the top half shell from the bottom half shell;axially displacing the top half shell and thereafter removing the top half shell in essentially the radial direction;rotationally fixedly connecting an auxiliary tool to the rotor of the turbomachine;connecting the auxiliary tool to the bottom half shell via axially displaceable adapter slides arranged on said auxiliary tool;axially displacing the bottom half shell to release the bottom half shell from axial connecting contours;rotating the bottom half shell with the rotor by approximately 180° until the bottom half shell assumes essentially the position of the removed top half shell; andreleasing the bottom half shell and removal of said bottom half shell.

8. The method as claimed in claim 11, further comprising: sequentially dismantling the outer carrier, the front plate, and the inner segment carrier.

9. The turbomachine as claimed in claim 1, comprising a gas turbine.

10. The turbomachine as claimed in claim 1, wherein at least one of the connecting contours comprises an axially open circumferential groove and a circumferential tongue configured and arranged to mate with the circumferential groove.

11. The method as claimed in claim 7, where said element comprises an outer carrier, an inner segment carrier, and a front plate.

12. A method of dismantling an element of a turbomachine, the method comprising: providing a turbomachine in accordance with claim 1;opening the turbomachine casing in the region of the combustion chamber;releasing the top half shell from the bottom half shell;axially displacing the top half shell and thereafter removing the top half shell in essentially the radial direction;rotationally fixedly connecting an auxiliary tool to the rotor of the turbomachine;connecting the auxiliary tool to the bottom half shell via axially displaceable adapter slides arranged on said auxiliary tool;axially displacing the bottom half shell to release the bottom half shell from axial connecting contours;rotating the bottom half shell with the rotor by approximately 180° until the bottom half shell assumes essentially the position of the removed top half shell; andreleasing the bottom half shell and removal of said bottom half shell.