Abstract: A compressor rotor for turbomachinery, such as a centrifugal compressor, is provided. Disclosed embodiments include a tie bolt and a rotor shaft that cooperates with the tie bolt to define a chamber therebetween. A seal assembly is positioned to separate the chamber from a first space and a leak detector in fluid communication with the first space and operable to generate a signal indicative of leakage of a fluid from the chamber to the first space.

Abstract: A compressor rotor for turbomachinery, such as a centrifugal compressor, is provided. Disclosed embodiments include a tie bolt and a rotor shaft that cooperates with the tie bolt to define a chamber therebetween. A seal assembly is positioned to separate the chamber from a first space and a leak detector in fluid communication with the first space and operable to generate a signal indicative of leakage of a fluid from the chamber to the first space.

Abstract: Rotor structure for a turbomachine, such as a centrifugal compressor, is provided. Disclosed embodiments make use of structural and/or operational relationships (e.g., distinct axially-extending zones in the radially-inner contour of respective impeller bodies configured to balance mass distribution about a rotor axis) designed to control relative radial and/or axial growth between corresponding interface locations along the rotor axis at which corresponding faces of respective hirth couplings mesh with one another. The ability to control relative radial and/or axial growth between corresponding interface locations may be effective for reducing rotor vibration and/or to establish more reliable contact patterns and reduced levels of mechanical stresses and distortion (e.g., angular distortion) at the hirth coupling interfaces.

Abstract: Compressor rotor structure and methodology for harmonizing compressor aerodynamics and rotordynamics are provided. Disclosed embodiments benefit from a compressor design effective for improving rotordynamics (e.g., stiffer rotor structure) without reducing a usable aerodynamics range of the compressor. This design may involve variation of the rotor structure along the rotor axis to locate respective surfaces defined by respective inlets of the one or more impellers at a varying distance relative to the rotor axis based on respective ratios selected for the configuration of the impeller bodies. This arrangement may be effective for improving rotordynamics while satisfactorily meeting the respective varying aerodynamics requirements at the various compression stages by the impeller bodies.

Abstract: Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from sealing sleeves that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by the compressor. The sealing sleeves may be affixed to adjoining structures (e.g., adjoining impeller bodies) by way of a slip fit connection to one of the adjoining structures and an interference fit connection with respect to the other adjoining structure, which is conducive to a user-friendly assembly of the sealing sleeves with the adjoining structures.

Abstract: Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments may involve a flow loop that at least in part flows through the interior of the tie bolt or by way of a venting arrangement that at least in part extends through one of the rotor shafts of the rotor structure. Disclosed embodiments may further benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of the process fluid being processed by the compressor. In operation, the flow loop may be appropriately pressurized to keep any residual seal leakage that may develop in one or more of the seal elements from travelling onto the hirth couplings.

Abstract: A compressor rotor for turbomachinery, such as a centrifugal compressor, is provided. Disclosed embodiments benefit from a seal assembly including one or more seal members positioned within a Hirth coupling to inhibit passage of process fluid being processed by the compressor. A circumferentially extending groove is arranged in a toothed meshing interface of the Hirth coupling to receive and securely hold the one or more seal members within the Hirth coupling. The groove may be configured with features, such as may define a dovetail groove, to facilitate assembly of certain seal members into the groove. Disclosed embodiments can make use of any of various sealing modalities for the seal member within the Hirth coupling based on the needs of a given application.

Abstract: A compressor rotor for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by the compressor. A seal element may be affixed to adjacent rotor components (e.g., adjacent impeller bodies) by way of a slip or interference fit connection to one of the adjacent components and may be affixed to the other adjacent rotor component by way of a elastically flexible frustoconical inner surface of the seal element that permits the seal element to be placed in a spring-loaded condition, which generates a biasing force to circumferentially clamp onto a frustoconical outer surface of the other adjacent rotor component. This arrangement is conducive to user-friendly assembly/disassembly of the seal elements with respect to the adjacent rotor components.

Abstract: Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments may involve a flow loop that at least in part flows through the interior of the tie bolt or by way of a venting arrangement that at least in part extends through one of the rotor shafts of the rotor structure. Disclosed embodiments may further benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of the process fluid being processed by the compressor.

Abstract: Rotor structure for a turbomachine, such as a centrifugal compressor, is provided. Disclosed embodiments make use of structural and/or operational relationships (e.g., distinct axially-extending zones in the radially-inner contour of respective impeller bodies configured to balance mass distribution about a rotor axis) designed to control relative radial and/or axial growth between corresponding interface locations along the rotor axis at which corresponding faces of respective hirth couplings mesh with one another. The ability to control relative radial and/or axial growth between corresponding interface locations may be effective for reducing rotor vibration and/or to establish more reliable contact patterns and reduced levels of mechanical stresses and distortion (e.g., angular distortion) at the hirth coupling interfaces.

Abstract: Compressor rotor structure and methodology for harmonizing compressor aerodynamics and rotordynamics are provided. Disclosed embodiments benefit from a compressor design effective for improving rotordynamics (e.g., stiffer rotor structure) without reducing a usable aerodynamics range of the compressor. This design may involve variation of the rotor structure along the rotor axis to locate respective surfaces defined by respective inlets of the one or more impellers at a varying distance relative to the rotor axis based on respective ratios selected for the configuration of the impeller bodies. This arrangement may be effective for improving rotordynamics while satisfactorily meeting the respective varying aerodynamics requirements at the various compression stages by the impeller bodies.

Abstract: A compressor rotor for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by the compressor. A seal element may be affixed to adjacent rotor components (e.g., adjacent impeller bodies) by way of a slip or interference fit connection to one of the adjacent components and may be affixed to the other adjacent rotor component by way of a elastically flexible frustoconical inner surface of the seal element that permits the seal element to be placed in a spring-loaded condition, which generates a biasing force to circumferentially clamp onto a frustoconical outer surface of the other adjacent rotor component. This arrangement is conducive to user-friendly assembly/disassembly of the seal elements with respect to the adjacent rotor components.

Abstract: Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from sealing sleeves that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by the compressor. The sealing sleeves may be affixed to adjoining structures (e.g., adjoining impeller bodies) by way of a slip fit connection to one of the adjoining structures and an interference fit connection with respect to the other adjoining structure, which is conducive to a user-friendly assembly of the sealing sleeves with the adjoining structures.

Abstract: A rotor for a turbomachine, includes a plurality of axially adjacently arranged rotor segments which are each provided with a central opening, an individual tie rod extending through the openings of the rotor segments, and two holding devices which are arranged on axially opposing ends of the tie rod and hold the rotor segments together, the rotor segments forming at least two rotor segment groups between which at least one other holding device is arranged.

Abstract: A rotor for a turbomachine, includes a plurality of axially adjacently arranged rotor segments which are each provided with a central opening, an individual tie rod extending through the openings of the rotor segments, and two holding devices which are arranged on axially opposing ends of the tie rod and hold the rotor segments together, the rotor segments forming at least two rotor segment groups between which at least one other holding device is arranged.