Abstract: A compressor or pump stage is provided. The compressor or pump stage at least comprising a central shaft and at least one rotor, wherein an axis of rotation of the at least one rotor is the central shaft, wherein at least two axial thrust bearings are arranged axially remote from each other and being associated with each of the at least one rotor and at least two radial bearings arranged between the at least two axial thrust bearings and the at least one rotor comprises a number, n, of rows of impellers arranged at an outer perimeter of the at least one rotor with an axial distance between neighbouring rows of impellers, where n={2, 3, 4 . . .

Abstract: A compressor or pump stage is provided. The compressor or pump stage at least comprising a central shaft (8) and one rotor (3), where the axis of rotation of the rotor (3) is the central shaft (8) and where the rotor comprises a number, n, of rows of impellers (5) arranged at an outer perimeter of the rotor with an axial distance between neighbouring rows of impellers (5), where n={2, 3, 4 . . . }.

Abstract: A compressor or pump stage is provided. The compressor or pump stage at least comprising a central shaft (8) and one rotor (3), where the axis of rotation of the rotor (3) is the central shaft (8) and where the rotor comprises a number, n, of rows of impellers (5) arranged at an outer perimeter of the rotor with an axial distance between neighbouring rows of impellers (5), where n={2, 3, 4...}.

Abstract: A compressor or pump stage is provided. The compressor or pump stage at least comprising a central shaft (8) and one rotor (3), where the axis of rotation of the rotor (3) is the central shaft (8) and where the rotor comprises a number, n, of rows of impellers (5) arranged at an outer perimeter of the rotor with an axial distance between neighbouring rows of impellers (5), where n={2, 3, 4 . . . }.

Abstract: According to one aspect of the present disclosure, a turbomachine (100) is provided. The turbomachine includes: a rotor extending in an axial direction and comprising a driven side configured to be connected to a driving unit and a second side opposite the driven side; a housing extending around at least a portion of the rotor, wherein a main flow path for a process fluid extends between the rotor and the housing; a sealing arrangement, particularly a dry gas seal, configured for sealing a gap between the rotor and the housing at the driven side of the rotor; and a first magnetic bearing supporting the second side of the rotor. A fluid passage for a portion of the process fluid extends from the main flow path through a bearing gap of the first magnetic bearing. According to a further aspect, a method of operating a turbomachine is described.

Abstract: A compressor includes a compressor bundle and an outer casing. Between the outer casing and the compressor bundle a thermal shield is provided, for reducing thermal stress and visco-plastic deformation of the casing under severe operating conditions.

Abstract: The present invention discloses a compressor or pump stage at least comprising a central shaft (8) and one rotor (3), where the axis of rotation of the rotor (3) is the central shaft (8) and where the rotor comprises a number, n, of rows of impellers (5) arranged at an outer perimeter of the rotor with an axial distance between neighbouring rows of impellers (5), where n={2, 3, 4 . . . }.

Abstract: The turbomachine comprises a stationary component, a rotary component, rotatingly supported in the stationary component, and a sealing arrangement between the rotary component and the stationary component. A cooling arrangement is further provided, which is configured and designed for delivering a cooling fluid to the sealing arrangement and removing heat therefrom.

Abstract: According to one aspect of the present disclosure, a turbomachine (100) is provided. The turbomachine includes: a rotor extending in an axial direction and comprising a driven side configured to be connected to a driving unit and a second side opposite the driven side; a housing extending around at least a portion of the rotor, wherein a main flow path for a process fluid extends between the rotor and the housing; a sealing arrangement, particularly a dry gas seal, configured for sealing a gap between the rotor and the housing at the driven side of the rotor; and a first magnetic bearing supporting the second side of the rotor. A fluid passage for a portion of the process fluid extends from the main flow path through a bearing gap of the first magnetic bearing. According to a further aspect, a method of operating a turbomachine is described.

Abstract: A multi-stage compressor is described, comprising a rotor having a plurality of axially stacked impellers and a tie rod extending through the stacked impellers and holding the impellers together. A gas compression path extends from a compressor inlet to a compressor outlet and through the impellers. A flow channel is provided between the tie rod and the stacked impellers. The flow channel develops along at least a portion of the tie rod. Hot gas is diverted from the compression path and flows through the flow channel to heat the tie rod during startup of the compressor.

Abstract: A centrifugal compressor including: a casing; at least one impeller supported for rotation in the casing and provided with a hub, a shroud and an impeller eye; an impeller-eye sealing arrangement, for sealing the impeller in the region of said impeller eye. The centrifugal compressor further includes at least one cooling-medium portlocated at the impeller-eye sealing arrangement, arranged for delivering a cooling medium around the impeller eye.

Abstract: The turbomachine comprises a stationary component, a rotary component, rotatingly supported in the stationary component, and a sealing arrangement between the rotary component and the stationary component. A cooling arrangement is further provided, which is configured and designed for delivering a cooling fluid to the sealing arrangement and removing heat therefrom.

Abstract: A compressor includes a compressor bundle and an outer casing. Between the outer casing and the compressor bundle a thermal shield is provided, for reducing thermal stress and visco-plastic deformation of the casing under severe operating conditions.

Abstract: A multi-stage compressor is described, comprising a rotor having a plurality of axially stacked impellers and a tie rod extending through the stacked impellers and holding the impellers together. A gas compression path extends from a compressor inlet to a compressor outlet and through the impellers. A flow channel is provided between the tie rod and the stacked impellers. The flow channel develops along at least a portion of the tie rod. Hot gas is diverted from the compression path and flows through the flow channel to heat the tie rod during startup of the compressor.

Abstract: A centrifugal compressor including: a casing; at least one impeller supported for rotation in the casing and provided with a hub, a shroud and an impeller eye; an impeller-eye sealing arrangement, for sealing the impeller in the region of said impeller eye. The centrifugal compressor further includes at least one cooling-medium portlocated at the impeller-eye sealing arrangement, arranged for delivering a cooling medium around the impeller eye.