| 摘要 |
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.
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