Method of dismantling a portion of a turbomachine

A method of dismantling an element of a turbomachine, the method comprising:

• providing a turbomachine comprising
• a rotor,
• 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 adjacent to 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, and
• wherein 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;
• opening the turbomachine casing adjacent to the combustion chamber;
• releasing the top half shell from the bottom half shell;
• axially displacing the top half shell from a position and thereafter radially removing the top half shell;
• rotationally fixedly connecting an auxiliary tool to the rotor;
• 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 and the rotor by approximately 180° until the bottom half shell assumes said position of the top half shell;
• and
• releasing the bottom half shell from the turbomachine and removing said bottom half shell.