Abstract: The present invention relates to a gas turbine with a turbine stator wheel, which is fitted with stator vanes and includes a ring segment-shaped vane root, where the stator vanes are designed hollow and have a vane interior which can be supplied with cooling air, where a ring-shaped sealing element of an inter-stage seal is arranged radially on the inside, relative to an engine axis, on the vane root, where in the vane root at least one outflow duct is provided, characterized in that between the vane root and the sealing element an annular space extending substantially in the axial direction is formed, into which the outflow duct issues and which discharges into the area of the inter-stage seal.

Abstract: A method for balancing and assembling a turbine rotor 2 including at least one turbine disk 3 and a compressor rotor 15 of a gas turbine. A front cover disk 6 is fastened by connections 10 to the turbine disk 3, and the turbine disk 3 is balanced together with the cover disk 6. The turbine disk 3 and the cover disk 6 are braced by a clamping device 19, 20. The bolted connections 10 are then removed and the turbine disk 3 and the cover disk 6 are connected to the compressor rotor 15 by bolted connections 10. The clamping device 19, 20 is then removed.

Abstract: A method for balancing and assembling a turbine rotor 2 including at least one turbine disk 3 and a compressor rotor 15 of a gas turbine. A front cover disk 6 is fastened by connections 10 to the turbine disk 3, and the turbine disk 3 is balanced together with the cover disk 6. The turbine disk 3 and the cover disk 6 are braced by a clamping device 19, 20. The bolted connections 10 are then removed and the turbine disk 3 and the cover disk 6 are connected to the compressor rotor 15 by bolted connections 10. The clamping device 19, 20 is then removed.

Abstract: The present invention relates to a gas turbine with a turbine stator wheel, which is fitted with stator vanes and includes a ring segment-shaped vane root, where the stator vanes are designed hollow and have a vane interior which can be supplied with cooling air, where a ring-shaped sealing element of an inter-stage seal is arranged radially on the inside, relative to an engine axis, on the vane root, where in the vane root at least one outflow duct is provided, characterized in that between the vane root and the sealing element an annular space extending substantially in the axial direction is formed, into which the outflow duct issues and which discharges into the area of the inter-stage seal.