Abstract: A turbo-machine is provided having at least one turbo-machine stage, wherein overload protection of the rotating shaft is provided by the method and, to protect the rotating shaft against overload, a measurement of a torsional stress of the rotating shaft is carried out during operation of the rotating shaft. The torsional stress is measured via a measurement of the torque of the rotating shaft. The torque is preferably measured magneto-elastically. By using the measured torque of the rotating shaft, the development of the torque is forecast. On the basis of the forecast produced, the turbo-machine stage or operating parameters of the turbo-machine is/are regulated. Further a turbo-machine is provided comprising at least one turbo-machine stage which has at least one rotating shaft, wherein the turbo-machine has a device for carrying out the method.

Abstract: A turbo-machine, which can be operated in an optimized driving range is provided. To this end, a method for operating a turbo-machine having at least one turbo-machine stage, which has at least one rotary shaft is disclosed. According to the method, the following method steps are carried out: a) determining a desired efficiency characteristic value ?soll of the turbomachine stage; b) determining an actual efficiency characteristic value ?ist of the turbo-machine-stage; c) determining a comparison efficiency characteristic value of the turbo-machine stage by comparing the actual efficiency characteristic value ?ist and the desired efficiency characteristic value ?soll to one another; and d) changing at least one operating parameter of the turbo-machine stage subject to the comparison efficiency characteristic value ?vgl, wherein in order to determine the actual efficiency characteristic value ?ist, a measuring of a torque of the rotary shaft of the turbo-machine-stage is carried out.

Abstract: A turbo-machine is provided having at least one turbo-machine stage, wherein overload protection of the rotating shaft is provided by the method and, to protect the rotating shaft against overload, a measurement of a torsional stress of the rotating shaft is carried out during operation of the rotating shaft. The torsional stress is measured via a measurement of the torque of the rotating shaft. The torque is preferably measured magneto-elastically. By using the measured torque of the rotating shaft, the development of the torque is forecast. On the basis of the forecast produced, the turbo-machine stage or operating parameters of the turbo-machine is/are regulated. Further to a turbo-machine is provided comprising at least one turbo-machine stage which has at least one rotating shaft, wherein the turbo-machine has a device for carrying out the method.

Abstract: A turbo-machine, which can be operated in an optimized driving range is provided. To this end, a method for operating a turbo-machine having at least one turbo-machine stage, which has at least one rotary shaft is disclosed. According to the method, the following method steps are carried out: a) determining a desired efficiency characteristic value ?soll of the turbomachine stage; b) determining an actual efficiency characteristic value ?ist of the turbo-machine-stage; c) determining a comparison efficiency characteristic value of the turbo-machine stage by comparing the actual efficiency characteristic value ?ist and the desired efficiency characteristic value ?soll to one another; and d) changing at least one operating parameter of the turbo-machine stage subject to the comparison efficiency characteristic value ?vgl, wherein in order to determine the actual efficiency characteristic value ?ist, a measuring of a torque of the rotary shaft of the turbo-machine-stage is carried out.

Abstract: A shaft seal includes more than one sealing module, at least one fluid supply and a fluid discharge, and a main seal which is subject to a greatest partial pressure difference. A second main seal is a radial double seal, which includes two gas seals, each gas seal having a rotating sealing surface and a stationary sealing surface, wherein the two sealing surface pairs are located opposite each other in a sealing plan, and wherein the two sealing planes have substantially radial extension to the shaft.

Abstract: A turbomachine, particularly a steam turbine, is provided. The turbomachine includes a machine housing and a shaft, which is guided through and guided out of the machine housing, at least on one side, wherein at least one annular gap present between the shaft and the machine housing is sealed by way of a shaft sealing assembly, wherein the shaft sealing assembly includes at least one radial double seal having two pairs of sealing surface pairs, which are spaced apart substantially radially and between which an annular sealing liquid chamber is formed, which can be supplied with sealing liquid via a sealing liquid feed line, wherein each sealing surface pair has an annular rotating sealing surface and an annular non-rotating sealing surface, which are arranged substantially axially opposite of each other and prestressed with respect to each other.

Abstract: A shaft seal for sealing a gap between a shaft and a casing is provided. The shaft seal includes a plurality of sealing modules, at least one fluid supply and one fluid drain, and a first main seal on which a major partial pressure difference occurs. Conventional shaft seals of the above type require significant amounts of additional barrier fluid in regular intervals to ensure suitable pressure gradients. In the presently proposed shaft seal, the first main seal is designed as a radial double seal which is defined by two gas seals having respective rotating sealing surfaces and stationary sealing surfaces, the pair of sealing surfaces being opposite each other in a respective sealing plane. The sealing planes extend in a substantially radial manner relative to the shaft.

Abstract: A shaft seal includes more than one sealing module, at least one fluid supply and a fluid discharge, and a main seal which is subject to a greatest partial pressure difference. A second main seal is a radial double seal, which includes two gas seals, each gas seal having a rotating sealing surface and a stationary sealing surface, wherein the two sealing surface pairs are located opposite each other in a sealing plan, and wherein the two sealing planes have substantially radial extension to the shaft.

Abstract: A turbomachine, particularly a steam turbine, is provided.

Abstract: A shaft seal for sealing a gap between a shaft and a casing is provided. The shaft seal includes a plurality of sealing modules, at least one fluid supply and one fluid drain, and a first main seal on which a major partial pressure difference occurs. Conventional shaft seals of the above type require significant amounts of additional barrier fluid in regular intervals to ensure suitable pressure gradients. In the presently proposed shaft seal, the first main seal is designed as a radial double seal which is defined by two gas seals having respective rotating sealing surfaces and stationary sealing surfaces, the pair of sealing surfaces being opposite each other in a respective sealing plane. The sealing planes extend in a substantially radial manner relative to the shaft.