Abstract: A method operates a gas turbine that includes a compressor section, a turbine section and an extraction cooling system. The method includes monitoring an operation of the gas turbine, directing a cooling air flow through the extraction cooling system from the compressor section to the turbine section in response to normal operation of the gas turbine, and directing a warming air flow through the extraction cooling system to the compressor section and the turbine section in response to shutdown of the gas turbine.

Abstract: A method for sealing a gas turbine engine includes coupling a turbine bucket to a rotor wheel and forming an interface region therebetween. A cooling air passage is defined in a portion of the rotor wheel and a cooling air manifold is defined in a portion of the turbine bucket. The method also includes inserting a seal tube within at least a portion of the cooling air passage. The method further includes coupling the cooling air passage, the seal tube, and the cooling air manifold in flow communication to at least partially define a turbine bucket cooling system. The method also includes operating the gas turbine engine such that the rotor wheel and the turbine bucket are rotated, thereby inducing a pressure on the seal tube to substantially decrease air flow discharged from the turbine bucket cooling system through the interface region.

Abstract: A seal assembly for a gas turbine engine including a seal member and an interstage seal ring including an axially forward member coupled to a first radially inward surface of a first disk and an axially aft member coupled to a second radially inward surface of a second disk, wherein the seal ring is configured to move in an axial direction while the upstream and downstream arms are coupled to the first and second disk respectively.

Abstract: A casing includes an inner shell and an outer shell that surrounds the inner shell and comprises a plurality of inflection points. An annular flange is between the inner shell and the outer shell, and a plurality of joints attach the inner shell to the annular flange. A connector is between the annular flange and the outer shell at each of the plurality of inflection points. A method for assembling a casing includes joining a plurality of curved sections to one another to generally define an arcuate inner shell and surrounding the arcuate inner shell with an outer shell. The method further includes attaching the arcuate inner shell to an annular flange at first attachment points and connecting the annular flange to the outer shell at second attachment points spaced approximately equidistantly from the first attachment points.

Abstract: In accordance with one embodiment, a system includes a multi-stage turbine including a first turbine stage including a first wheel having multiple first slots spaced circumferentially about the first wheel, and multiple first blade segments each coupled to at least one of the multiple first slots. The multi-stage turbine also includes a second turbine stage including a second wheel having multiple second slots spaced circumferentially about the second wheel, and multiple second blade segments each coupled to at least one of the multiple second slots. The multi-stage turbine further includes a one-piece interstage seal extending axially between the first and second turbine stages, wherein the one-piece interstage seal comprises a first radial support coupled to the first wheel and a second radial support coupled to the second wheel, and the one-piece interstage seal extends circumferentially across at least two of the multiple first slots or at least two of the multiple second slots.

Abstract: An apparatus for restricting fluid flow in a turbo-machine is disclosed. The apparatus includes: a first inter-stage sealing member configured to be located between a first rotating airfoil stage and a second rotating airfoil stage attached to a rotor shaft, the first inter-stage sealing member including a segmented structure that includes a plurality of segments forming a circumferential surface, the first inter-stage sealing member including: a first base portion including a securing mechanism configured to at least substantially radially and tangentially secure the inter-stage sealing member to an inter-stage support structure; a first axial retention mechanism; and a first axially extending sealing portion configured to be outwardly radially loaded against at least one of the first rotating airfoil stage and the second rotating airfoil stage.

Abstract: A method for assembling a rotating machine includes providing a rotating element including a plurality of rotor wheels. The method also includes positioning the rotating element such that at least a portion of a stationary portion extends at least partially about the rotating element. The method further includes assembling an interstage seal mechanism including coupling at least a portion of a first hook device to the rotating element, and also including coupling at least a portion of a second hook device to the first hook device. The first hook device and the second hook device are radially inboard of at least a portion of the stationary portion.

Abstract: A cooling system for a turbine includes a blower configured to generate a cooling gas flow to be passed through a rotor cavity of the turbine; piping configured to deliver the cooling gas flow to the turbine; and at least one valve configured to control the cooling gas flow. The piping is operatively connected to the rotor of the turbine. A method of cooling a turbine includes generating a cooling gas flow with a blower to be passed through a rotor cavity of the turbine; and delivering the cooling gas flow to the turbine.

Abstract: An actuating device includes: at least one first elongated member having a first coefficient of thermal expansion (CTE); and at least one second elongated member having a second CTE different from the first CTE, the second elongated member being nested within the first elongated member, the device being configured to displace a portion of the device a selected distance along a major axis of the device based on a relationship between the first CTE and the second CTE in response to a change in temperature.

Abstract: A method of attaching two rotor discs in a turbine engine, the method comprising the steps of: forming a first rotor disc that includes a first axial extension and a disc flange; forming a second rotor disc that includes a second axial extension and a weld surface; forming a bridge, the bridge that includes a bridge flange at one end and a weld surface at the other end, and, along an outer radial surface, the bridge comprises means for sealing; attaching the bridge to the second rotor disc via welding the weld surfaces of the bridge and the second axial extension; and attaching the first rotor disc to the bridge via removably securing the disc flange to the bridge flange.

Abstract: A rotor includes a first rotor segment having a first outer surface and a second rotor segment having a second outer surface. A mechanical joint is between the first and second rotor segments, and a cavity is radially outward of the mechanical joint and beneath the first and second outer surfaces. A weld bead is between the first and second outer surfaces. A method for manufacturing a rotor includes machining a first rotor segment having a first concentric axis of rotation and machining a second rotor segment having a second concentric axis of rotation. The method further includes aligning the first rotor segment to the second rotor segment radially using a mechanical joint and applying a weld bead over a portion of the first and second rotor segments to connect the first rotor segment to the second rotor segment.

Abstract: A system to support a rotor and a stator of a rotating machine disposed upon a support base, the system including at least one support leg in operable communication with a bearing of the rotor and with the support base; and at least one strut in operable communication with the at least one support leg and with the stator.

Abstract: A retaining system is provided for circumferential entry rotor dovetails inserted into dovetail slot in a rotor. A plurality of rotor blade dovetails are circumferentially slidable into and along the dovetail slot, with each rotor blade dovetail having a neck and a pair of oppositely oriented lobes. A plurality of rail segments are circumferentially slid into channels in the dovetail slot between the dovetail lobes and the respective disk hoops. The rail segments define a first pressure face that engages against an outward pressure face of the dovetail lobes, and a second pressure face that engages against an inward pressure face of the respective disk hoop component.

Abstract: A system is disclosed that includes a turbine engine having a first rotary component having a first annular coupling disposed about a rotational axis of the engine. The first annular coupling has an axially converging surface relative to the rotational axis. The system also includes a second rotary component having a second annular coupling disposed about the rotational axis of the turbine engine, wherein the second annular coupling comprises an axially diverging surface such that the axially converging surface of the first annular coupling mates with the axially diverging surface.

Abstract: A method for sealing a gas turbine engine includes coupling a turbine bucket to a rotor wheel and forming an interface region therebetween. A cooling air passage is defined in a portion of the rotor wheel and a cooling air manifold is defined in a portion of the turbine bucket. The method also includes inserting a seal tube within at least a portion of the cooling air passage. The method further includes coupling the cooling air passage, the seal tube, and the cooling air manifold in flow communication to at least partially define a turbine bucket cooling system. The method also includes operating the gas turbine engine such that the rotor wheel and the turbine bucket are rotated, thereby inducing a pressure on the seal tube to substantially decrease air flow discharged from the turbine bucket cooling system through the interface region.

Abstract: A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body.

Abstract: A seal assembly for a gas turbine engine including a seal member and an interstage seal ring including an axially forward member coupled to a first radially inward surface of a first disk and an axially aft member coupled to a second radially inward surface of a second disk, wherein the seal ring is configured to move in an axial direction while the upstream and downstream arms are coupled to the first and second disk respectively.

Abstract: A method operates a gas turbine that includes a compressor section, a turbine section and an extraction cooling system. The method includes monitoring an operation of the gas turbine, directing a cooling air flow through the extraction cooling system from the compressor section to the turbine section in response to normal operation of the gas turbine, and directing a warming air flow through the extraction cooling system to the compressor section and the turbine section in response to shutdown of the gas turbine.

Abstract: A cooling system for a turbine includes a blower configured to generate a cooling gas flow to be passed through a rotor cavity of the turbine; piping configured to deliver the cooling gas flow to the turbine; and at least one valve configured to control the cooling gas flow. The piping is operatively connected to the rotor of the turbine. A method of cooling a turbine includes generating a cooling gas flow with a blower to be passed through a rotor cavity of the turbine; and delivering the cooling gas flow to the turbine.

Abstract: A system for adjusting a clearance in a gas turbine including a turbine rotor and a plurality of buckets is disclosed. The system includes: a shroud assembly including at least one shroud segment, the at least one shroud segment being disposed in an interior of a turbine shell; and an elongated member extending from the turbine shell. The at least one shroud segment is attached to an end of the elongated member, the elongated member configured to move in response to a temperature change to move the shroud segment and change a clearance between the shroud segment and at least one of the plurality of buckets.