Clamping composite assembly

A clamping composite rotor for a gas turbine, comprising:

• a first component with a first flange having first radial webs and first recesses between each of two neighboring first webs in the circumferential direction;
• a second component with a second flange having second radial webs and second recesses between each of two neighboring second webs in the circumferential direction;
• and
• a third component having a third flange;
• wherein the first component is a cone, and the second component is a configured and arranged to support rotating blades of the gas turbine and the third component is configured and arranged to support rotating blades of the gas turbine;
• wherein the first and the second component are configured and arranged that, in an initial installation position, the first and second component form a first angular position relative to each other around an installation and/or longitudinal rotational axis of the clamping composite rotor and by an axial displacement of the first and second components relative to each other and parallel to this axis;
• wherein the second webs pass through the first recesses and the first webs pass through the second recesses in the axial direction;
• wherein, in the installed clamping composite assembly, the first and second components have a second angular position relative to one another around the installation and/or longitudinal rotational axis of the clamping composite rotor, in which the second webs at least partially overlap the first webs in the circumferential direction;
• and
• the second webs are arranged in the axial direction between the first webs and the third flange and are clamped by a separate tension rod device of the rotor;
• wherein the tension rod device passes through the first component, second component and third component in the axial direction and is supported in the axial direction directly or indirectly on one of the sides of the first component facing away from the third component.