Abstract: A rotor blade system, for example, of a gas turbine is provided. The rotor blade system includes a plurality of rotor blades which are arranged annularly on a rotor disk. A plurality of sealing plates are arranged on a side surface of the rotor disk. An individual sealing plate is formed from a plurality of metal sheets, wherein two of the metal sheets are arranged opposite each other a distance apart and parallel to a plane of the sealing plate, forming a gap for guiding of cooling air.

Abstract: A rotor section for a rotor of a gas turbine, a rotor blade, and a blocking element are provided. The rotor section includes a rotor disk including rotor blades that are inserted thereon in holding grooves and that are secured against sliding along the holding grooves by means of a sealing element arranged at the end face. In order to specify a reliable, simple, and easy-to-design construction for the circumferential fixing of the sealing elements, it is proposed that each sealing element be secured by one blocking element, which engages in a hole arranged at the end face in the rotor blade root.

Abstract: An axial turbomachine rotor is provided. The turbomachine includes a rotor body designed in a rotation symmetrical manner around the rotor axis, a rotor blade ring including rotor blades that are each fixed to the rotor body by the blade foot thereof and a sealing disc designed in a rotation symmetrical manner around the rotor axis that is arranged having the outer edge thereof radially inside, neighboring an axially extending protrusion of the blade foot, so that a hollow space is formed between the blade foot and the sealing disc, wherein a groove exists on the outer edge leading radially to the outside, wherein a sealing ring is mounted that may slide radially to the outside in the groove during operation of the rotor by centrifugal force until the sealing ring radially contacts the inside of the protrusion and thus seals the hollow space on the blade foot.

Abstract: A stator blade carrier for a gas turbine is provided. The stator blade carrier includes a plurality of axial segments. At least one axial segment is designed as a tubular lattice structure. This allows a simpler design technically and a more flexible adaptation to the temperature profile present on the stator blade carrier to maintain operational safety.