Abstract: An electrical machine is disclosed that has a stator and a rotor. The rotor, spaced apart radially from the stator, is configured to rotate about a longitudinal axis. An air gap extends between the rotor and the stator. The rotor has a rotor shaft having two end faces and a surface. A plurality of permanent magnets is connected to the rotor shaft and adjoin the air gap. The rotor shaft has, spaced apart radially from the air gap, a plurality of cooling channels that extend in the longitudinal direction between the end faces of the rotor shaft.

Abstract: A monitoring apparatus for mechanical damage, in particular fracture, of a rotating shaft which is driven by a gas turbine and transmits a torque to a generator, wherein a converter apparatus coupled to the generator generates direct current, characterized by a first measuring apparatus for at least one electrical variable of the generator and/or of the converter apparatus during operation, wherein the torque proportionally depends on the electrical variable, and a second measuring apparatus for the behaviour of the speed of the generator during operation, a control apparatus which captures the electrical variable and the speed as measurement variables and, if at least one predefinable criterion for the mechanical damage, in particular the fracture, of the shaft, in particular threshold values for the measurement variables, is exceeded or undershot, outputs at least one control signal to the gas turbine. The invention also relates to a monitoring method.

Abstract: A shroud device of a jet engine, including a radially internal shroud appliance and a radially external shroud appliance. The internal shroud appliance is embodied with a radially internal ring-shaped shroud part and a radially external ring-shaped shroud part. The internal shroud appliance includes multiple blades that extend substantially in the radial direction between the internal shroud part and the external shroud part. The radially external shroud appliance is embodied with a radially internal ring-shaped shroud part and a radially external ring-shaped shroud part. The external shroud appliance includes multiple blades that extend substantially in the radial direction between the internal shroud part and the external shroud part. The internal shroud appliance is embodied as a first one-piece cast structural component and the external shroud appliance is embodied as a second one-piece cast structural component.

Abstract: A shroud device of a jet engine, including a radially internal shroud appliance and a radially external shroud appliance. The internal shroud appliance is embodied with a radially internal ring-shaped shroud part and a radially external ring-shaped shroud part. The internal shroud appliance includes multiple blades that extend substantially in the radial direction between the internal shroud part and the external shroud part. The radially external shroud appliance is embodied with a radially internal ring-shaped shroud part and a radially external ring-shaped shroud part. The external shroud appliance includes multiple blades that extend substantially in the radial direction between the internal shroud part and the external shroud part. The internal shroud appliance is embodied as a first one-piece cast structural component and the external shroud appliance is embodied as a second one-piece cast structural component.