Abstract: A retention device for maintaining a first rotary machine component axially loaded onto a second rotary machine component in a fixed axial position includes a lock block sized and configured to move between first and second aligned recesses in the first and second rotary machine components. The aligned recesses are shaped to prevent rotation of the lock block, and the lock block has a threaded bore extending therethrough. An actuator is threadably mounted in the bore, such that rotation of the actuator will, in use, move the lock block from the first aligned recess at least partially into the second aligned recess.

Abstract: Various embodiments include a method of displacing a turbomachine component from position in a first slot of a turbomachine spacer disk. The method can include detachably affixing a mounting member of a displacement apparatus to a second slot in the gas turbomachine spacer disk using an attachment device, rotating a displacement arm of the displacement apparatus until the displacement arm contacts the turbomachine component, and displacing the turbomachine component from the position within the first slot by linearly actuating the displacement arm with a linear actuator.

Abstract: A tool for removing a component from a turbomachine is provided. The tool includes a body having an alignment portion and a connection portion. The alignment portion defines a longitudinal axis and a cross sectional shape complementary to a slot defined in a rotor wheel of the turbomachine. When the tool is positioned in the slot, the connection portion is configured to contact the component. The tool additionally includes a force section connected to the body and configured to transfer a force to the connection portion in a direction substantially parallel to the longitudinal axis of the alignment portion.

Abstract: Various embodiments include methods adapted to displace turbomachine components from a location within a turbomachine. In some embodiments, a method of displacing a turbine bucket from a turbomachine wheel slot using a displacement apparatus, includes: detachably engaging an engagement arm of the displacement apparatus to the turbine bucket, the engagement arm attached to a linear actuator coupled to a body of the displacement apparatus, and the engagement arm adapted to be actuated in a first axial direction by the linear actuator; contacting the turbomachine wheel with at least two contacting portions of the body of the displacement apparatus; and displacing the turbine bucket from a position within a slot of the turbomachine wheel in the first axial direction by linearly actuating the engagement arm with the linear actuator.

Abstract: A mid-span shroud assembly for a turbine blade airfoil includes a pressure side shroud body which is associated with a pressure side wall of the airfoil and a suction side shroud body which is associated with a suction side wall of the airfoil. At least one of the pressure side shroud body and the suction side shroud body defines a coupling spar which is formed to extend at least partially through a bore hole defined within the airfoil of the turbine blade.

Abstract: Various embodiments include a method of displacing a turbomachine component from position in a first slot of a turbomachine spacer disk. The method can include detachably affixing a mounting member of a displacement apparatus to a second slot in the gas turbomachine spacer disk using an attachment device, rotating a displacement arm of the displacement apparatus until the displacement arm contacts the turbomachine component, and displacing the turbomachine component from the position within the first slot by linearly actuating the displacement arm with a linear actuator.

Abstract: Various embodiments include methods adapted to displace turbomachine components from a location within a turbomachine. In some embodiments, a method of displacing a turbine bucket from a turbomachine wheel slot using a displacement apparatus, includes: detachably engaging an engagement arm of the displacement apparatus to the turbine bucket, the engagement arm attached to a linear actuator coupled to a body of the displacement apparatus, and the engagement arm adapted to be actuated in a first axial direction by the linear actuator; contacting the turbomachine wheel with at least two contacting portions of the body of the displacement apparatus; and displacing the turbine bucket from a position within a slot of the turbomachine wheel in the first axial direction by linearly actuating the engagement arm with the linear actuator.

Abstract: Various embodiments include apparatuses adapted to displace components from a location within a turbomachine. In some embodiments an apparatus for displacing a component of a gas turbine from a first slot in a spacer disk includes a body including a mounting member configured to affixedly attach to a second slot of the spacer disk, a linear actuator coupled to the body and a displacement arm coupled to the linear actuator, the displacement arm actuatable in a first axial direction by the linear actuator to contact the component and displace the component relative to the first slot.

Abstract: Various embodiments include apparatuses adapted to displace turbomachine components from a location within a turbomachine. In some embodiments apparatuses for displacing a turbine bucket from a turbomachine wheel slot include a body having at least two contacting portions for contacting the turbomachine wheel, a linear actuator coupled to the body, and an engagement arm for engaging the turbine bucket, the engagement arm coupled to the linear actuator and adapted to be actuated in a first axial direction by the linear actuator.

Abstract: A mid-span shroud assembly for a turbine blade includes a pressure side shroud body defining a spar pocket and a fastener hole and a suction side shroud body defining a spar pocket and a fastener hole. The mid-span shroud assembly further includes a spar having a first end portion which extends within the spar pocket of the pressure side shroud body and a second end portion which extends within the spar pocket of the suction side shroud body. The spar is formed to extend through a bore hole of the turbine blade. A fastener is formed to extend through the fastener hole of the pressure side shroud body, a fastener orifice of the turbine blade and the fastener hole of the suction side shroud body to provide a clamping force to hold the pressure side and suction side shroud bodies against the airfoil.

Abstract: A mid-span shroud assembly for a turbine blade airfoil includes a pressure side shroud body which is associated with a pressure side wall of the airfoil and a suction side shroud body which is associated with a suction side wall of the airfoil. At least one of the pressure side shroud body and the suction side shroud body defines a coupling spar which is formed to extend at least partially through a bore hole defined within the airfoil of the turbine blade.

Abstract: Various embodiments include apparatuses adapted to displace turbomachine components from a location within a turbomachine. In some embodiments apparatuses for displacing a turbine bucket from a turbomachine wheel slot include a body having at least two contacting portions for contacting the turbomachine wheel, a linear actuator coupled to the body, and an engagement arm for engaging the turbine bucket, the engagement arm coupled to the linear actuator and adapted to be actuated in a first axial direction by the linear actuator.

Abstract: Various embodiments include apparatuses adapted to displace components from a location within a turbomachine. In some embodiments an apparatus for displacing a component of a gas turbine from a first slot in a spacer disk includes a body including a mounting member configured to affixedly attach to a second slot of the spacer disk, a linear actuator coupled to the body and a displacement arm coupled to the linear actuator, the displacement arm actuatable in a first axial direction by the linear actuator to contact the component and displace the component relative to the first slot.

Abstract: A tool for removing a component from a turbomachine is provided. The tool includes a body having an alignment portion and a connection portion. The alignment portion defines a longitudinal axis and a cross sectional shape complementary to a slot defined in a rotor wheel of the turbomachine. When the tool is positioned in the slot, the connection portion is configured to contact the component. The tool additionally includes a force section connected to the body and configured to transfer a force to the connection portion in a direction substantially parallel to the longitudinal axis of the alignment portion.

Abstract: A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin.

Abstract: A near flow path seal member for a turbomachine includes a seal body having a seal support member including a first end portion that extends to a second end portion through an intermediate portion. An arm member extends from the first end portion of the seal body. The arm member has a first end that extends to a second end to define an axial dimension of the arm member, a first edge that extends to a second, opposing edge to define a circumferential dimension of the arm member, and a surface having a profile that establishes a thickness variation of the arm member in each of the axial dimension and the circumferential dimension.

Abstract: A near flow path seal member for a turbomachine includes a seal body having a seal support member including a first end portion that extends to a second end portion through an intermediate portion. An arm member extends from the first end portion of the seal body. The arm member has a first end that extends to a second end to define an axial dimension of the arm member, a first edge that extends to a second, opposing edge to define a circumferential dimension of the arm member, and a surface having a profile that establishes a thickness variation of the arm member in each of the axial dimension and the circumferential dimension.

Abstract: A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin.

Abstract: A retention device for maintaining a first rotary machine component axially loaded onto a second rotary machine component in a fixed axial position includes a lock block sized and configured to move between first and second aligned recesses in the first and second rotary machine components. The aligned recesses are shaped to prevent rotation of the lock block, and the lock block has a threaded bore extending therethrough. An actuator is threadably mounted in the bore, such that rotation of the actuator will, in use, move the lock block from the first aligned recess at least partially into the second aligned recess.

Abstract: An airfoil for a stator vane having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I is provided. The profile is carried only to three decimal places wherein Z is a distance from a platform on which the airfoil is mounted and X and Y are coordinates defining the profile at each distance Z from the platform.