Abstract: A rotor of a gas turbine having two adjacent rotor discs, on each of which moving blades are fastened, an annular rotor component being arranged between the rotor discs and having at its opposite ends circumferential annular grooves, in each of which a circumferential fastening projection on the respective rotor disc engages. When the rotor is stationary a first outer flank of the first annular groove rests under pressure against a first outer flank of the first fastening projection and there is play between a first inner flank of the first annular groove and a first inner flank of the first fastening projection.

Abstract: A gas turbine including a plurality of hook elements disposed one inside the other and designed substantially in the form of hollow cones or hollow cylinders, and including a stator blade support, is intended to enable an especially high efficiency while maintaining the greatest possible operating safety and operating life. To this end, at least one of the hook elements or the stator blade support has a substantially elliptical cross-sectional contour.

Abstract: A gas turbine including a plurality of hook elements disposed one inside the other and designed substantially in the form of hollow cones or hollow cylinders, and including a stator blade support, is intended to enable an especially high efficiency while maintaining the greatest possible operating safety and operating life. To this end, at least one of the hook elements or the stator blade support has a substantially elliptical cross-sectional contour.

Abstract: A turbine guide vane support for an axial-flow gas turbine is provided. The support includes a tubular wall having an inflow-side end and an outflow-side end for a hot gas flowing in the interior of the turbine guide vane support in a flow path of the gas turbine. Cooling channels for a coolant are provided in the wall. The cooling channels extend from a coolant inlet to a coolant outlet, respectively. At least one of the cooling inlets and one of the cooling outlets, respectively, is disposed at the outflow-side end of the turbine guide vane support, wherein the cooling channel associated with the respective inlet and outlet extends up to the inflow-side end of the turbine guide vane support and transitions to a redirecting area from which the respective cooling channel further extends to the outflow-side end.