Abstract: A method for operating a machine plant having a shaft train, including: a) determining the harmonic frequency of a torsional vibration mode of the shaft train and determining mechanical stresses arising during a vibration period of the torsional vibration mode; b) determining a correlation for each torsional vibration mode between a first stress amplitude, at a position of the shaft train that carries risk of stress damage, and a second stress amplitude, at a measurement location of the shaft train, using stresses determined for the respective torsional vibration mode; c) establishing a maximum first stress amplitude for the position; d) establishing a maximum second stress amplitude, corresponding to the maximum first stress amplitude, for the measurement location; e) measuring the stress of the shaft train while rotating; f) determining a stress amplitude at each harmonic frequency; g) emitting a signal when the stress amplitude reaches the maximum second stress amplitude.

Abstract: A method for operating a machine plant having a shaft train, including: a) determining the harmonic frequency of a torsional vibration mode of the shaft train and determining mechanical stresses arising during a vibration period of the torsional vibration mode; b) determining a correlation for each torsional vibration mode between a first stress amplitude, at a position of the shaft train that carries risk of stress damage, and a second stress amplitude, at a measurement location of the shaft train, using stresses determined for the respective torsional vibration mode; c) establishing a maximum first stress amplitude for the position; d) establishing a maximum second stress amplitude, corresponding to the maximum first stress amplitude, for the measurement location; e) measuring the stress of the shaft train while rotating; f) determining a stress amplitude at each harmonic frequency; g) emitting a signal when the stress amplitude reaches the maximum second stress amplitude.

Abstract: A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor.

Abstract: A rotor of a thermal fluid flow machine, especially a gas turbine, is provided. The rotor includes a plurality of rotor components that are held together by a common tie-bolt that extends through the center of the rotor components. The tie-bolt is fixed in at least one of the rotor components using at least one star spring that surrounds the tie-bolt in a circumferential direction.

Abstract: A gas turbine is provided. The gas turbine includes at least one rotor, having rotor blades arranged on the periphery of rotor disks in a plurality of radial planes, and a tie-bolt extending along slots in the rotor disks and holding the rotor disks together as a unit. At least one annular spacer for fixing the position of the tie-bolt in relation to the center line of the rotor disks is also provided. The spacer includes through-openings that are arranged radially in relation to the tie-bolt or to its center line and that extend coaxially.

Abstract: The invention relates to a method for inspecting especially a gas turbine installation or steam turbine installation. An actual condition of a component of the turbine installation is determined using a suitable system, the determined actual condition is compared with a predetermined desired condition of the component, and the result of comparison between the actual condition and the desired condition is used to determine whether an overall inspection of the turbine installation is required. The component is a guide vane whose angular position in relation to the direction of influx is the actual condition to be determined. The actual condition is determined by an imaging device. The invention also relates to a turbine inspection system for carrying out the method.

Abstract: An oscillation damping system for stator windings is provided which includes a supporting component of an end winding. The supporting component is equipped with damping elements, which are arranged asymmetrically in the circumferential direction in order to suppress excited natural oscillations. Masses or springs and screw-type restraints which connect the supporting component to the stator housing are suitable as damping elements.

Abstract: A rotor of a thermal turbomachine, particularly a gas turbine, is provided. The rotor includes a plurality of individual rotor components that are held together by a tie-bold and combined into a unit. The tie-bolt is supported by the assembly of the surrounding rotor components including the tie-bolt and the rotor disks. A hollow shaft which is made up of two tubular sections and a support wheel further support the rotor.

Abstract: A gas turbine is provided. The gas turbine includes at least one rotor, having rotor blades arranged on the periphery of rotor disks in a plurality of radial planes, and a tie-bolt extending along slots in the rotor disks and holding the rotor disks together as a unit. At least one annular spacer for fixing the position of the tie-bolt in relation to the center line of the rotor disks is also provided. The spacer includes through-openings that are arranged radially in relation to the tie-bolt or to its center line and that extend coaxially.

Abstract: A rotor of a thermal fluid flow machine, especially a gas turbine, is provided. The rotor includes a plurality of rotor components that are held together by a common tie-bolt that extends through the center of the rotor components. The tie-bolt is fixed in at least one of the rotor components using at least one star spring that surrounds the tie-bolt in a circumferential direction.

Abstract: An oscillation damping system for stator windings is provided which includes a supporting component of an end winding. The supporting component is equipped with damping elements, which are arranged asymmetrically in the circumferential direction in order to suppress excited natural oscillations. Masses or springs and screw-type restraints which connect the supporting component to the stator housing are suitable as damping elements.

Abstract: The invention relates to a method for inspecting especially a gas turbine installation or steam turbine installation. According to said method, an actual condition of a component of the turbine installation is determined using a suitable system, the determined actual condition is compared with a predetermined desired condition of the component, and the result of comparison between the actual condition and the desired condition is used to determine whether an overall inspection of the turbine installation is required. The component is a guide vane whose angular position in relation to the direction of influx is the actual condition to be determined. The actual condition is determined by means of an imaging device. The invention also relates to a turbine inspection system for carrying out the method.