Abstract: A blade in a turbine of a gas turbine engine that includes: an outer surface bending along an edge at an angle greater than about 120° so to define a first outer surface to a first side of the edge and a second outer surface to a second side of the edge; an internal flow passage; and a forked cooling channel configured so to fluidly connect the internal flow passage to a first film cooling port and a second film cooling port formed to each side of the edge.

Abstract: An inner shell assembly for a steam turbine includes an inner shell with a plurality of grooves of preset dimensions, and a plurality of nozzle carriers respectively securable in the plurality of grooves. Each of the nozzle carriers supports at least one nozzle and bucket for a turbine stage via a dovetail, where the inner shell, the plurality of nozzle carriers and the nozzles and buckets define a steam path. A radial position of the dovetails in the nozzle carriers within its corresponding grooves is selectable according to the steam path, and an axial width of each of the nozzle carriers is selectable according to the steam path.

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 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: Systems and devices adapted to retain dovetail components (e.g., buckets) in a turbine drum rotor and reduce rotor component displacement are disclosed. In one embodiment, a turbine bucket includes: a bucket base portion shaped to complement a bucket shank slot in a rotor of a turbine, the bucket base portion including: a forward portion shaped to extend upstream of a first stage circumferential slot of the rotor in to a first rotor post of the rotor; a circumferential protrusion formed in an aft end of the bucket base portion and shaped to connect to the rotor, and a set of axial protrusions formed on tangential sides of the bucket base portion and shaped to connect to the rotor; and a bucket platform extending radially outboard from the bucket base portion, the bucket platform configured to complement a vane.

Abstract: A system and method for measuring and adjusting rotor to stator clearances is disclosed, as well as a turbomachine embodying the system and method. In an embodiment, a turbomachine is assembled, including a stator having an upper and a lower stator shell, and a rotor disposed within the stator. A cold clearance between the rotor and the stator is determined at each of a plurality of clearance measurement points using an in situ clearance sensor system. Each of the clearance measurement points is axially spaced from each other clearance measurement point. The cold clearance between the rotor and the stator is adjusted based on the determined cold clearances, by displacing one of the upper stator shell or the lower stator shell relative to a foundation, thereby changing a shape of the upper stator shell or the lower stator shell to accommodate a position of the rotor within the stator.

Abstract: A method and apparatus for determining axial clearance data between a rotor and a stator are disclosed. At least one radial clearance sensor is positioned on the stator and is configured to gather radial clearance data, i.e., measurements of a radial distance between the rotor and the stator taken at discrete time intervals. A computing device is operably connected with the at least one radial clearance sensor and is configured to use the radial clearance data to determine axial clearance data, i.e., an axial distance between the stator and the rotor. In one embodiment, the computing device uses, among other data points, an indication of a loss of signal from at least one radial clearance sensor to extrapolate the axial clearance data.

Abstract: A system for providing sealing in a turbine is provided. The sealing system includes a retaining channel oriented within a housing structure proximate a moving turbine component. A seal member is coupled within the retaining channel. A first end of the seal member is secured to the housing structure. A second end of the seal member is movable relative to the retaining channel between first and second positions corresponding to a transient operational mode and a steady state operational mode, respectively. The transient operational mode defines a first clearance between the seal member and the moving turbine component. The steady state configuration defines a second clearance that is smaller than the first clearance. A take-up device coupled to the second end of the seal member moves the second end between the first and second positions.

Abstract: An apparatus for measuring turbine rotor-to-stator clearances and a method for assembling a turbomachine based on the measured clearances are disclosed. In an embodiment, at least one clearance sensor is inserted into a stator of a turbomachine. Using the sensor, tops-on clearance between a rotor blade tip and an inner surface of a stator is measured while an upper stator shell, a rotor, a lower stator shell are assembled together; and a tops-off clearance is measured while the lower stator shell and a rotor are assembled together. A tops-on/tops-off shift, i.e., a difference between the tops-on clearance and the tops-off clearance, is determined. The turbine can be assembled by adjusting a relative position of the rotor and stator to account for the tops-on/tops-off shift.

Abstract: A steam turbine with a drum rotor utilizing individual nozzle ring assemblies in the IP section incased by a single shell. In one embodiment, a steam turbine has a high pressure (HP) section with a double shell drum and an intermediate pressure (IP) section with a single shell drum, with the IP section including a plurality of individual nozzle ring assemblies axially spaced along the single shell casing, such that each nozzle ring assembly surrounds the drum rotor. In other embodiments, a low pressure section (LP) of the steam turbine can have a single-flow or dual-flow connection to a condenser, and the condenser can be positioned to the side, vertically below, or axially aligned with the LP section.

Abstract: A steam turbine nozzle vane arrangement includes a first nozzle vane comprising a first radially outer end and a first radially inner end, the first nozzle vane located in a steam turbine housing and operatively coupled to the steam turbine housing proximate the first radially outer end. Also included is a second nozzle vane operatively coupled to the steam turbine housing proximate a second radially outer end, the second nozzle vane located adjacent the first nozzle vane in a circumferentially aligned turbine stage. Further included is a first cover located proximate the first radially inner end and having a first hole. Yet further included is a second cover located proximate a second radially inner end of the second nozzle vane and having a second hole. Also included is a pin disposed within the first and second hole, the pin configured to fixedly couple the first and second nozzle vanes.

Abstract: Systems, methods and devices adapted to ease installation of turbine bucket assemblies about a rotor and to reduce related stress concentrations in the rotor are disclosed. In one embodiment, an insert includes: a base portion adapted to complement an entry slot in a rotor of a turbine; and a neck portion extending radially outboard from the base portion, the neck portion adapted to complement a post of the rotor to form a substantially continuous dovetail about the rotor.

Abstract: An apparatus for measuring turbine rotor-to-stator clearances and a method for assembling a turbomachine based on the measured clearances are disclosed. In an embodiment, at least one clearance sensor is inserted into a stator of a turbomachine. Using the sensor, tops-on clearance between a rotor blade tip and an inner surface of a stator is measured while an upper stator shell, a rotor, a lower stator shell are assembled together; and a tops-off clearance is measured while the lower stator shell and a rotor are assembled together. A tops-on/tops-off shift, i.e., a difference between the tops-on clearance and the tops-off clearance, is determined. The turbine can be assembled by adjusting a relative position of the rotor and stator to account for the tops-on/tops-off shift.

Abstract: An inner shell assembly for a steam turbine includes an inner shell with a plurality of grooves of preset dimensions, and a plurality of nozzle carriers respectively securable in the plurality of grooves. Each of the nozzle carriers supports at least one nozzle and bucket for a turbine stage via a dovetail, where the inner shell, the plurality of nozzle carriers and the nozzles and buckets define a steam path. A radial position of the dovetails in the nozzle carriers within its corresponding grooves is selectable according to the steam path, and an axial width of each of the nozzle carriers is selectable according to the steam path.

Abstract: Systems and devices adapted to retain dovetail components (e.g., buckets) in a turbine drum rotor and reduce rotor component displacement are disclosed. In one embodiment, a turbine bucket includes: a bucket base portion shaped to complement a bucket shank slot in a rotor of a turbine, the bucket base portion including: a forward portion shaped to extend upstream of a first stage circumferential slot of the rotor in to a first rotor post of the rotor; a circumferential protrusion formed in an aft end of the bucket base portion and shaped to connect to the rotor, and a set of axial protrusions formed on tangential sides of the bucket base portion and shaped to connect to the rotor; and a bucket platform extending radially outboard from the bucket base portion, the bucket platform configured to complement a vane.

Abstract: A system includes a creep indicating member on a rotating component, and a measurement device configured to measure a change in radial position of the creep indicating member. The system allows determination of, for example, rotating component life expectancy in a turbine, without exposing the rotating component.

Abstract: A creep indication system and a method for determining a creep amount are disclosed. The system includes a first creep indicating member on a first rotating component and a second creep indicating member on a second rotating component. The second creep indicating member has at least one different creep characteristic from the first creep indicating member. The system further includes at least one measurement device configured to measure a change in radial position of at least one of the first creep indicating member or the second creep indicating member. The method includes measuring a first creep amount of a first creep indicating member and measuring a second creep amount of a second creep indicating member. The method further includes estimating a temperature of a rotating component using the first creep amount and the second creep amount.

Abstract: The present invention relates to compositions, methods, kits and systems employing irradiation activated agents to improve or increase or prevent loss of toughness, work-to-fracture, post-yield toughness, fracture toughness and/or fatigue strength of a bone allograft on exposure to radiation. The irradiation activated agent can be an agent that increases crosslinking of collagen in bone during irradiation, for example ribose, 2-hydroxytetrahydropyran or ascorbate.

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: In one embodiment, an insert for a turbine cooling circuit includes: a radial cooling passage for receiving downstream fluid; an axial passage extending from the radial cooling passage within a lower portion of the insert; and a plurality of radial passages extending from the axial passage, each radial passage extending to a bottom of a partially circumferential dovetail slot of the insert. In another embodiment, an insert for a turbine cooling includes: a plurality of radial passages, each radial passage extending from a bottom of a partially circumferential dovetail slot of the insert; an axial passage extending from the plurality of radial passages within a lower portion of the insert; and an exhaust passage extending from the axial passage.