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The invention relates to a turbo-machine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbo-machine. The aim of said invention is to develop a device and a method for the turbo-machine making it possible to

The invention relates to a turbo-machine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbo-machine. The aim of said invention is to develop a device and a method for the turbo-machine making it possible to reduce the size of a radial split of the turbo-machine in order to obtain greater degree of efficiency. The inventive turbo-machine comprises a rotor rotationally mounted in the case of the turbo-machine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing said fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and an actuating device dependent on centrifugal force is provided.

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The invention claimed is: 1. A turbo-machine, comprising: a rotor rotatably mounted in a casing of the turbo-machine, the rotor comprising a rotor shaft and a plurality of moving-blade wheels arranged on the rotor shaft, wherein the plurality of moving-blade wheels comprise a plurality of moving bl

The invention claimed is: 1. A turbo-machine, comprising: a rotor rotatably mounted in a casing of the turbo-machine, the rotor comprising a rotor shaft and a plurality of moving-blade wheels arranged on the rotor shaft, wherein the plurality of moving-blade wheels comprise a plurality of moving blades arranged thereon; a feed passage arranged in the rotor for providing a fluid; and a plurality of discharge passages arranged in the rotor for discharging the fluid; and an actuating arrangement for influencing a flow of the fluid, the actuating arrangement in fluid connection with the plurality of discharge passages via gaps formed between the plurality of moving-blade wheels and elements projecting axially through the rotor shaft of the rotor; wherein the plurality of discharge passages open into a flow passage between the plurality of moving-blade wheels arranged on the rotor shaft to discharge the fluid from the rotor; wherein each of the plurality of discharge passages includes a throttle element for controlling an amount of fluid distributed into a respective one of the plurality of discharge passages; wherein a feeding opening of the feed passage is radially further on the inside than an outlet opening of the discharge passage; and wherein at least a portion of the plurality of throttle elements are configured to provide a decreased amount of fluid into a respective one of the plurality of discharge passages with increased axial distance from the actuating arrangement relative to an upstream throttle element. 2. The turbo-machine as claimed in claim 1, wherein the turbo-machine is designed as a gas turbine with a compressor and the feed passage is provided at a compressor-side end of the rotor shaft. 3. The turbo-machine of claim 1, wherein the fluid flow is influenced by a shutoff element that is actuated as a function of a speed of the rotor shaft.