Abstract: 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.

Abstract: 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.

Abstract: A cooling arrangement for a gas turbine engine includes a discharge channel for airflow from a compressor, a first cooling channel, and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel or the power output of the gas turbine engine. The restrictor device may be a boreplug, which may be a two-way shape memory alloy.

Abstract: A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.

Abstract: Embodiments of the present application include a gas turbine system. The system may include a rotor wheel and one or more impeller vanes radially disposed on the rotor wheel. The system may also include one or more fluid passages defined by adjacent impeller vanes. The one or more fluid passages may be radially disposed across the rotor wheel. Moreover, the system may include one or more shape memory alloy valves disposed within each of the fluid passages. The one or more shape memory alloy valves may be configured to change shape to control a flow of fluid through the fluid passages.

Abstract: A turbine shroud arrangement for a turbine system includes a first region of a tip shroud, the first region disposed in close proximity to an adjacent tip shroud. Also included is a second region of the tip shroud, the second region disposed in close proximity to the adjacent tip shroud, the second region comprising a temperature sensitive material configured to engage the second region and the adjacent tip shroud in contact over a first operating condition of the turbine system and configured to provide a second region gap over a second operating condition of the turbine system.

Abstract: A turbine bucket shroud arrangement for a turbine system includes a contact region of a tip shroud, wherein the contact region is in close proximity to an adjacent tip shroud. Also included is a negative thermal expansion material disposed proximate the contact region, the contact region comprising a first volume during a startup condition and a shutdown condition of the turbine system and a second volume during a steady state condition of the turbine system, wherein the second volume is less than the first volume.

Abstract: Various embodiments include a turbomachine with a plasma seal system. The turbomachine can include: a diaphragm section having: an axially facing diaphragm wall; and a discourager seal protruding axially from the axially facing diaphragm wall; a rotor section having: a bucket having an axially facing bucket wall opposing the axially facing diaphragm wall; and a seal member extending from the axially facing bucket wall, wherein the seal member axially overlaps a portion of the discourager seal of the diaphragm section leaving a radial gap between the seal member and the discourager seal; and a plasma generator coupled to the diaphragm section for generating a plasma which reduces the radial gap between the seal member and the discourager seal.

Abstract: A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.

Abstract: Embodiments of the present application include a gas turbine system. The system may include a rotor wheel and one or more impeller vanes radially disposed on the rotor wheel. The system may also include one or more fluid passages defined by adjacent impeller vanes. The one or more fluid passages may be radially disposed across the rotor wheel. Moreover, the system may include one or more shape memory alloy valves disposed within each of the fluid passages. The one or more shape memory alloy valves may be configured to change shape to control a flow of fluid through the fluid passages.

Abstract: A near flow path seal for a turbomachine includes a support member having a first end portion that extends to a second end portion through an intermediate portion, and an arm member extending from the first end portion of the support member. The arm member includes a first end that extends to a second end, a first surface extending between the first and second ends, and a second, opposing surface extending between the first and second ends. The second surface includes a plurality of surface features that extend from about the first end toward the second end.

Abstract: A connection ring assembly and connection ring support system for a dynamoelectric machine is provided. The connection ring assembly includes a plurality of connection rings, and a clamp element disposed around a portion of the connection rings. The clamp element provides axial and tangential support to the plurality of connection rings. The connection ring support system includes one or more primary spring bars connected to the connection ring assembly. The primary spring bars permit radial and tangential movement of the connection ring assembly. One or more secondary spring bars are connected to the primary spring bars, and permit axial movement of the connection ring assembly.

Abstract: Embodiments of the invention relate generally to lead path configurations in generator rotors and, more particularly, to a support apparatus for a main lead and generator rotors incorporating such a support apparatus. In one embodiment, the invention provides a generator rotor comprising: a rotor shaft including an internal conductive bore; a main terminal electrically connected to the conductive bore; a plurality of rotor coil windings, including a plurality of coil end straps; a non-metallic support channel comprising: an elongate, axially-oriented channel; and at least one protrusion extending from the elongate, axially-oriented channel to a position between two of the plurality of coil end straps; and a main lead extending from the main terminal, through the elongate, axially-oriented channel of the non-metallic support channel, to at least one of the plurality of coil end straps.

Abstract: Embodiments of the invention relate generally to lead path configurations in generator rotors and, more particularly, to a support apparatus for a main lead and generator rotors incorporating such a support apparatus. In one embodiment, the invention provides a generator rotor comprising: a rotor shaft including an internal conductive bore; a main terminal electrically connected to the conductive bore; a plurality of rotor coil windings, including a plurality of coil end straps; a non-metallic support channel comprising: an elongate, axially-oriented channel; and at least one protrusion extending from the elongate, axially-oriented channel to a position between two of the plurality of coil end straps; and a main lead extending from the main terminal, through the elongate, axially-oriented channel of the non-metallic support channel, to at least one of the plurality of coil end straps.

Abstract: Embodiments of the invention relate generally to lead path configurations in generator rotors and, more particularly, to a support apparatus for a main lead and generator rotors incorporating such a support apparatus. In one embodiment, the invention provides a support apparatus for a main lead of a generator rotor, the support apparatus comprising: a cross-sectionally L-shaped body having: a first portion; and a second portion substantially perpendicular to the first portion, wherein the first portion includes an arcuate first surface for interfacing with a centering ring of the generator rotor and an arcuate second surface adapted to be substantially parallel to a rotor shaft of the generator rotor; a main lead passage extending along the arcuate first surface of the first portion and through the second portion.

Abstract: A connection ring assembly and connection ring support system for a dynamoelectric machine is provided. The connection ring assembly includes a plurality of connection rings, and a clamp element disposed around a portion of the connection rings. The clamp element provides axial and tangential support to the plurality of connection rings. The connection ring support system includes one or more primary spring bars connected to the connection ring assembly. The primary spring bars permit radial and tangential movement of the connection ring assembly. One or more secondary spring bars are connected to the primary spring bars, and permit axial movement of the connection ring assembly.

Abstract: Embodiments of the invention relate generally to lead path configurations in generator rotors and, more particularly, to a support apparatus for a main lead and generator rotors incorporating such a support apparatus. In one embodiment, the invention provides a support apparatus for a main lead of a generator rotor, the support apparatus comprising: a cross-sectionally L-shaped body having: a first portion; and a second portion substantially perpendicular to the first portion, wherein the first portion includes an arcuate first surface for interfacing with a centering ring of the generator rotor and an arcuate second surface adapted to be substantially parallel to a rotor shaft of the generator rotor; a main lead passage extending along the arcuate first surface of the first portion and through the second portion.