Abstract: Systems and devices configured to reduce thermal design clearances (e.g., between stationary nozzles connected to the inner casing and rotor buckets connected to the rotor) in turbines by actively controlling casing movements and/or locations during turbine operation are disclosed. In one embodiment, a clearance management system includes: a first inner casing support arm shaped to connect to an inner casing of a turbine and extend through an outer casing of the turbine; a seal system disposed about the first inner casing support arm and configured to connect to the outer casing; and a set of actuators disposed on a turbine foundation of the turbine and connected to the first inner casing support arm, the set of actuators located external to the outer casing and configured to adjust a position of the inner casing relative to the outer casing via manipulation of the first inner casing support arm.

Abstract: A turbine assembly is disclosed herein. The turbine assembly may include a rotor with at least one bucket extending radially therefrom. The turbine assembly also may include a stator assembly positioned adjacent to the at least one bucket. Moreover, the turbine assembly may include a seal assembly. The seal assembly may include a first flange extending in a substantially axial direction from the at least one bucket. The seal assembly also may include a second flange extending from the stator assembly in the substantially axial direction opposite the first flange. The second flange may include at least one protuberance projecting towards the first flange.

Abstract: A seal assembly for sealing a stationary component and a rotating component including a seal tooth mating surface for mating with a seal tooth, the seal tooth mating surface including a plateau portion for sealingly receiving the seal tooth during a steady-state operation of the seal assembly and a first concave portion adjacent to the plateau portion for receiving the seal tooth with a clearance during a first non-steady-state operation of the seal assembly, wherein the seal tooth is coupled to one of the stationary component and the rotating component and the seal tooth mating surface is coupled to the other of the stationary component and the rotating component.

Abstract: Certain embodiments of the invention may include systems, methods and apparatus for providing a labyrinth seal. In an example embodiment, a method is provided for sealing a flow path between a stationary element and a rotating element of a turbomachine. The method can include disposing at least one fixture on an inner surface of a stationary element associated with the turbomachine; disposing a packing ring linked via a spring element to the fixture wherein the packing ring comprises at least one bore; and disposing, according to a predetermined profile, a plurality of interdigitated packing ring teeth and rotor teeth intermediate to the packing ring and the rotating element; wherein the bore, packing ring teeth, and rotor teeth, cooperate to counter a moment associated with one or more axial forces.

Abstract: A paliperidone double-layered osmotic pump controlled release tablet and the preparation method thereof are disclosed. The double-layered osmotic pump controlled release tablet comprises a rigid membrane, a push layer, a drug layer, an isolation layer and an aesthetic coating, wherein the rigid membrane contains a semi-permeable polymer, a porogen and/or a plasticizer and has one or more drug release orifices on one end, the push layer comprises an expanding material, an osmotic agent, a binder, a colorant and a lubricant, the drug layer contains a pharmaceutically active ingredient, a hydrophilic polymer, an osmotic agent, a colorant, a lubricant and an antistatic agent, the isolation layer is located between the inner surface of the rigid membrane and the push layer, and contains a hydrophilic polymer. The paliperidone double-layered osmotic pump controlled release tablet shows an increasing drug release rate at early stage and keeps a constant drug release rate at later stage.

Abstract: A brush seal and brush seal segment for use in a rotary device are provided. In one embodiment, the invention provides a brush seal comprising: a plurality of brush seal segments, each segment including: an arcuate fence; an arcuate backplate substantially circumferentially coextensive with the arcuate fence, the arcuate backplate including a first end and a second end; and a plurality of brush seal bristles between the arcuate backplate and the arcuate fence, the plurality of brush seal bristles being angled with respect to a radial axis of the arcuate backplate and at least one of the first end and the second end of the arcuate backplate; and a static member to which at least one of the plurality of brush seal segments is affixed.

Abstract: Systems and devices for substantially fluidly isolating portions of a rotary machine are disclosed. In one embodiment, a seal assembly for a rotary machine includes: a complementary set of seal segments configured relative one another so as to form a substantially continuous body with butt gaps between the seal segments, the segments including: a head flange; and an axial neck connected to the head flange, wherein the axial neck extends radially inboard and includes an axial slot formed substantially there through; and at least one butt gap seal element, wherein the at least one butt gap seal element includes an axial flange and a radial flange, the axial flange disposed within the axial slots of adjacent seal segments; and the radial flange extending radially inboard from the axial slots to a proximity of the rotary machine substantially forming a barrier to axial flow through the butt gap.

Abstract: The present application provides for a brush seal system for use about a rotor of a rotary machine. The brush seal system may include a number of brush seal segments, with each of the brush seal segments having a number of bristles, and one or more of the brush seal segments including an elliptical profile so as to vary a clearance between the brush seal segments and the rotor.

Abstract: A system includes a brush seal segment. The brush seal segment includes a movable support including a head, an extension, and a seal surface, wherein the head is configured to mount in a chamber. The brush seal segment also includes a brush coupled to the movable support along the seal surface, wherein the seal surface consists essentially of the brush. The brush seal segment also includes a biasing element coupled to the movable support, wherein the biasing element is configured to bias the movable support from a first position to a second position to increase a brush clearance in a space between the brush and a rotor, and the movable support is configured to move from the second position to the first position to decrease the brush clearance in response to a fluid flow from the space to the chamber.

Abstract: According to one aspect of the invention, a turbine assembly includes a first stationary component, a second stationary component positioned radially outside the first stationary component, a first key feature on the first stationary component configured to mate to a second key feature on the second stationary component and a seal assembly positioned between the first and second key features to reduce fluid flow between the first and second key features. The seal assembly includes a V-shape member and a second member adjacent to the V-shape member, the second member and V-shape member having different rates of thermal expansion. The seal assembly also includes a latch feature coupled to the V-shape member configured to expand the seal assembly from a compressed state to an expanded sealing state when the seal assembly is subject to an elevated temperature.

Abstract: Various embodiments include a turbomachine including a swirl-inhibiting seal. In various particular embodiments, a turbomachine includes: a rotor section having sets of axially disposed blades; a diaphragm section at least partially surrounding the rotor section, the diaphragm section including a set of nozzles positioned between adjacent sets of axially disposed blades, wherein the set of nozzles includes at least one nozzle having: a base section coupled to the diaphragm section; a blade coupled to the base section; and a radial tip section coupled to a radial end of the blade, the radial tip section including an axially extending flange having a slot extending therethrough for controlling fluid flow within the turbomachine.

Abstract: A brush seal assembly for turbomachinery having a rotor can include a stationary seal component, a floating seal component coupled to the stationary seal component and circumferentially angled bristles arranged in a bristle pack, disposed in the floating seal component and extended axially with respect to the rotor.

Abstract: A seal assembly for a turbomachine includes a seal ring rotatable between a first position and a second position and having a plurality of tunnels. Also included is a back ring located adjacent the seal ring and having a plurality of apertures that align with more of the plurality of tunnels of the seal ring when at the second position than at the first position. Further included is a retention piece operably connecting the seal ring and the back ring.

Abstract: A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.

Abstract: A labyrinth seal design, an actuation control clearance strategy, and a method of operating a turbomachine. The labyrinth seal design including a plurality of features configured to open and close radial clearances in response to relative axial movement between a stationary component and a rotating component. The actuation control clearance strategy and method of operating a turbomachine effective to achieve relative motion between a rotating component and a stationary component of the turbomachine using active elements. Axial displacement of the rotating component relative to the stationary component provides an adjustment in a radial clearance at one or more sealing locations between the rotating component and the stationary component to suit a given operating condition of the turbomachine.

Abstract: A standard for supporting a turbine rotor and a turbine shell includes a bearing block including a housing enclosing bearing surfaces engageable by the turbine rotor. Turbine shell-arm supports are located on opposite sides of the housing, the turbine shell-arm supports each having a horizontal and one or more vertical surfaces adapted to be engaged by support arms of a turbine shell enclosing at least a portion of the turbine. An internal cooling/heating circuit is arranged to simultaneously cool or heat the bearing block and the turbine shell-arm supports to thereby reduce differential thermal growth characteristics of the turbine rotor and turbine shell.

Abstract: A brush seal assembly is provided, including a sealing surface, a side plate, a backing plate, a plurality of bristles, and a biasing member. The backing plate is selectively located in a stationary position and has at least one backing tooth and a backing tip. The backing tooth has a tooth surface and the backing tip has a tip surface. A tooth clearance is measured between the tooth surface and the sealing surface. A tip clearance is measured between the tip surface and the sealing surface. The tooth clearance is less than the tip clearance. The bristles are located between the side plate and the backing plate. The bristles include an end portion for sealing to the sealing surface. The biasing member exerts a biasing force upon the backing plate in a direction towards the sealing surface. The backing tooth is configured for selectively contacting the sealing surface.

Abstract: A system controls net thrust of a steam turbine having a stepped rotating shaft. A first leak off line fluidly couples a first stage of a turbine section to a packing near a stepped portion on the rotating shaft. A second leak off line fluidly couples a second stage of the turbine section that has a pressure different from the first stage to a step area immediately adjacent to the stepped portion, and a connection line fluidly couples the first leak off line to the second leak off line. The lines include control valves such that a controller can actively control the net thrust by regulating thrust pressure on the stepped portion using steam from the first and second stages of the turbine section. The controller may also prevent damage to an active retractable seal using the control valves.

Abstract: A shaft sealing system and method are disclosed for a high or intermediate pressure turbine section having a rotating member including a shaft and a stationary member surrounding the rotating member and defining a steam flow path. The shaft sealing system comprises at least one seal disposed about each of a first end and a second end of the shaft; and a connection line for conducting steam from the first turbine section to a downstream portion of the turbine. The downstream portion of the turbine is one of a low pressure section and a condenser, and has a lower pressure than both of the first turbine section and ambient pressure conditions.

Abstract: A shaft sealing system and method are disclosed for a low pressure turbine section having a rotating member including a shaft and a stationary member surrounding the rotating member and defining a steam flow path. The shaft sealing system comprises at least one seal disposed about each of a first end and a second end of the shaft; and a connection line for conducting steam from the first turbine section to a downstream portion of the turbine. The downstream portion of the turbine has a lower pressure than both of the first turbine section and ambient pressure conditions.