A balancing weight mountable within a balance hole of a rotary component includes a cylindrical body having a desired weight. An opening is formed in a portion of the body to define a hollow passageway and a mechanism couples the cylindrical body within an interior of the balance hole.

An airfoil and shroud assembly includes an airfoil including a root end, a free end and a tenon extending from the free end, the tenon including a base and an externally threaded stud extending from the base. A shroud includes an opening configured to receive the base of the tenon. A nut is configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil to couple the shroud to the airfoil.

An example rotary machine includes a motor including a rotor and a stator, and a cooling jacket disposed around the stator. The cooling jacket includes an inner body part being cylindrical and in contact with the stator, an outer body part being cylindrical and surrounding the inner body part, and a groove through which a cooling medium passes, the groove circling helically around an outer circumference of the inner body part at least once. The groove has a pair of side surfaces opposed in a direction of an axis of rotation of the rotor, and a bottom surface connected to each of the pair of side surfaces. Each of the pair of side surfaces is formed having a draft angle inclined away from each other, the draft angle inclined relative to a release direction orthogonal to the axis of rotation.

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of a segregated impeller shroud in a turbine engine. The system comprises a driving mechanism coupled to a portion of a segregated impeller shroud. The driving mechanism comprises a driving arm and threaded axial member configured to translate motion of an actuator ring into axially forward and aft motion of the portion of the segregated impeller shroud.

A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly in an industrial gas turbine engine is presented. The locking spacer assembly includes a first side piece, a second side piece, a mid piece and a bolt. The bolt is disposed into the mid piece to position the mid piece in a radial position in an assembled state. The mid piece contacts the first side piece and the second side piece in the assembled state to prevent axial movements of the first and second side pieces in the disk groove. The bolt prevents a radial movement of the mid piece.

A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly, a blade assembly and a method for installing a locking spacer assembly into a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly are presented. The locking spacer assembly includes a first side piece, a second side piece, a bolt and a mid piece. The mid piece includes a hollow cylindrical body to receive the bolt and a top platform to flush with top surfaces of the first and second side pieces and a middle platform disposed at bottom of the hollow cylindrical body. At least two pins are radially inserted through apertures of the first and second side pieces respectively extending toward the middle platform of the mid piece to prevent radial movement of the mid piece.

A system and method for coupling cases associated with an engine of an aircraft. A first case includes a first plurality of threads. A second case includes a second plurality of threads. A coupler includes a third plurality of threads and a fourth plurality of threads. An interface is configured to align the first case and the second case before the first plurality of threads engage the third plurality of threads or the second plurality of threads engage the fourth plurality of threads.

An inner structure is within an outer structure. A shield mount of a shield is attached to the outer structure. A sleeve of the shield extends from the shield mount through an aperture in the outer structure to a distal end of the shield. The sleeve is mated with the port at the distal end through a slip joint interface where a cylindrical sleeve surface of the sleeve contacts a cylindrical port surface of a port of the inner structure. The fluid transfer tube extends from an inner tube end through a bore of the shield and at least into the port to an outer tube end. An inner coupling is disposed at the inner tube end and mated with the inner structure through a cone seal interface. An outer coupling is disposed at the outer tube end and attached to the outer structure.

An airfoil and shroud assembly includes an airfoil including a root end, a free end and a tenon extending from the free end, the tenon including a base and an externally threaded stud extending from the base. A shroud includes an opening configured to receive the base of the tenon. A nut is configured to be threadably coupled to the externally threaded stud on the tenon on the airfoil to couple the shroud to the airfoil.

A closing assembly for closing a blade ring inserted into a circumferential T-groove of a blade support of a turbomachine, having two insertion elements, each has a C-shaped basic form having a resting leg, retention leg, and connection leg connecting the resting leg and the retention leg and is designed to reach around a ridge of the T-groove. The resting leg reaches over the ridge and the retention leg reaches under the ridge, and an intermediate element, is positioned between the insertion elements to prevent the insertion elements from moving to the center of the T-groove. The intermediate element reaches below the retention legs of the insertion elements in the assembled state, and a positioning element is associated with the intermediate element, which is supported between the groove base of the T-groove and the intermediate element and to position the intermediate element at a desired distance from the groove base.