Abstract: A seal system between a row of buckets supported on a machine rotor and a surrounding stationary casing or stator includes a tip shroud secured at radially outer tips of each of the buckets, the tip shroud formed with a radially-projecting rail. A cellular seal structure is supported in the stationary stator in radial opposition to the tip shroud and the rail. The seal structure has an annular array of individual cells formed to provide continuous, substantially horizontal flow passages devoid of any radial obstruction along substantially an entire axial length dimension of the cellular seal structure to prevent flow about the tip shroud from turning radially inwardly.

Abstract: A seal is provided for preventing axial leakage through a radial gap between a stationary structure and a rotating structure. The radial gap is defined by an inner radial surface opposing an outer radial surface across the radial gap. The seal includes at least one land disposed on one of the inner radial surface and outer radial surface. At least one first tooth and at least one second tooth project from the other of the radial surfaces. The second tooth is shorter than the first tooth. At least one of the first tooth and second tooth, is configured to extend at an angle upstream. This angle is defined between a radial surface from which the first or second tooth projects and an upstream surface of the same tooth. The angle is less than or equal to about 80 degrees.

Abstract: An exhaust gas diffuser is provided and includes a peripheral body, a center body, formed to define an interior and disposed within the peripheral body to define an annulus between the peripheral body and the center body through which a first fluid flows along a main flow direction, a plurality of first members, each of which is respectively coupled to the peripheral body and the center body, to support the center body within the peripheral body and a plurality of second members, each of which extends across the annulus from the peripheral body to the center body downstream from the plurality of the first members relative to the main flow direction, to transport a second fluid to the center body interior. The plurality of the second members is circumferentially clocked relative to the plurality of the first members.

Abstract: A low pressure steam turbine is disclosed including a rotor having: a rotor body; and a plurality of bucket stages disposed axially along the rotor body, the plurality of bucket stages including a last bucket stage; and a nozzle assembly at least partially surrounding the rotor, the nozzle assembly including a plurality of nozzle stages corresponding to the plurality of bucket stages, wherein a nozzle in a nozzle stage axially upstream of the last bucket stage is adjustable to modify a fluid flow within the last bucket stage during operation of the low pressure steam turbine.

Abstract: A steam turbine includes a final turbine stage, a flow diffuser receiving a main flow from the final turbine stage, a diverging wall in the axial or radial flow diffuser that extends from a diffuser inlet to a diffuser exit, and a centerbody in the axial or radial flow diffuser. An opening is provided in the diverging wall and an opening is provided in the centerbody for fluidically actuating the main flow. The openings are located downstream from the diffuser inlet and upstream from a point where boundary layer separation would occur along the walls in a diffuser without the openings. A plurality of openings are provided in the diverging wall, and an end packing seal is positioned adjacent an end portion of the final turbine stage. An annular manifold collects fluid from leakage flow from the end packing seal and distributes the leakage flow to the openings.

Abstract: An exhaust arrangement for a turbine is provided having an inner turbine casing, a condenser, an exhaust arrangement structure, and a bearing cone. The inner turbine casing includes a plurality of last stage buckets. A steam flow passes through the inner turbine casing and out of the plurality of last stage buckets. The condenser for receives the steam flow. The exhaust arrangement structure has a diffuser, a lower section and an upper section. The lower section has an exhaust section. The lower section receives the steam flow from the last stage buckets of the inner turbine casing through the diffuser and guides the steam flow out of the exhaust section in a direction generally towards the condenser. The upper section has a receiving section and a guiding section.

Abstract: A turbine exhaust diffuser for use adjacent a last stage row of buckets fixed to a turbine rotor includes an annular inner diffuser ring and an annular outer diffuser ring defining a flow path for steam exiting a last stage row of buckets in a first substantially axial direction at a diffuser inlet, and turning substantially ninety degrees to a diffuser outlet. The outer diffuser ring has a curved steam guide surface extending between the diffuser inlet and the diffuser outlet including a first portion extending away from the diffuser inlet and a second portion extending to said diffuser outlet, the second portion shaped to extend beyond vertical and back toward the diffuser inlet so as to establish a flow component in a second opposite axial direction. The second portion is also provided with a plurality of turbulators to minimize flow separation along the steam guide surface.

Abstract: An apparatus is provided and includes a first member with a flow diverting member extending from a surface thereof and a second member disposed proximate to the first member with a clearance gap area defined between a surface of the second member and a distal end of the flow diverting member such that a fluid path, along which fluid flows from an upstream section and through the clearance gap area, is formed between the surfaces of the first and second members. The second member is formed to define dual vortex chambers at the upstream section in which the fluid is directed to flow in vortex patterns prior to being permitted to flow through the clearance gap area.

Abstract: An exhaust hood for an axial steam turbine that includes a radial channel, downstream from the normal flow pattern. The radial channel guides the exhaust steam flow in upper half of the hood in the flow momentum direction. Due to this pattern of flow direction, vortex generation in upper exhaust hood is reduced and increased flow diffusion results. The geometric arrangement can eliminate the outer casing of the exhaust hood over the axial length of the turbine inner casing, allowing the turbine inner casing to be supported directly by a foundation for the steam turbine.

Abstract: A turbomachine includes a housing having an outer surface and an inner surface that defines an interior portion. The housing includes a fluid plenum. A rotating member is arranged within the housing. The rotating member includes at least one bucket having a base portion and a tip portion. A stationary member is mounted to the inner surface of the housing adjacent the tip portion of the at least one bucket. At least one fluid passage passes through at least a portion of the stationary member. The at least one fluid passage includes a fluid inlet fluidly coupled to the fluid plenum and a fluid outlet exposed to the interior portion. The fluid outlet being configured and disposed to direct a flow of fluid toward the tip portion of the at least one bucket.

Abstract: A method of assembling a sealing assembly for use in a turbomachine includes providing a rotatable element that includes an end portion with a plurality of grooves partially extending circumferentially about a portion of an outer surface of the end portion of the rotatable element. The method also includes providing a stationary portion that includes an upper section and a lower section. The method further includes inserting at least a portion of the end portion of the rotatable element into the lower section. The method also includes coupling the upper section to the lower section, thereby defining a rotor shaft cavity. The end portion of the rotatable element at least partially extends through the rotor shaft cavity, thereby defining a clearance between the end portion of the rotatable element and the stationary portion.

Abstract: The present application provides a diffuser for an exhaust hood of a steam turbine. The diffuser may include a first end adjacent to a last bucket and a second end downstream of a steam guide and adjacent to a bearing cone. An exhaust flow path extends therethrough. The second end may include an axial extension enlarging the exhaust flow path.

Abstract: A labyrinth seal system is disclosed, including a stationary component having a plurality of radially inwardly projecting, axially spaced teeth extending therefrom; and a rotor having a plurality of radially outwardly projecting, axially spaced protrusions, each protrusion having a low pressure side and a high pressure side, wherein the low pressure side of at least one protrusion extends farther in a radial direction than the high pressure side.

Abstract: A seal is provided for preventing axial leakage through a radial gap between a stationary structure and a rotating structure. The radial gap is defined by an inner radial surface opposing an outer radial surface across the radial gap. The seal includes at least one land disposed on one of the inner radial surface and outer radial surface. At least one first tooth and at least one second tooth project from the other of the radial surfaces. The second tooth is shorter than the first tooth. At least one of the first tooth and second tooth, is configured to extend at an angle upstream. This angle is defined between a radial surface from which the first or second tooth projects and an upstream surface of the same tooth. The angle is less than or equal to about 80 degrees.

Abstract: A seal system between a row of buckets supported on a machine rotor and a surrounding stationary casing or stator includes a tip shroud secured at radially outer tips of each of the buckets, the tip shroud formed with a radially-projecting rail. A cellular seal structure is supported in the stationary stator in radial opposition to the tip shroud and the rail. The seal structure has an annular array of individual cells formed to provide continuous, substantially horizontal flow passages devoid of any radial obstruction along substantially an entire axial length dimension of the cellular seal structure to prevent flow about the tip shroud from turning radially inwardly.

Abstract: An exhaust hood for an axial steam turbine that includes a radial channel, downstream from the normal flow pattern. The radial channel guides the exhaust steam flow in upper half of the hood in the flow momentum direction. Due to this pattern of flow direction, vortex generation in upper exhaust hood is reduced and increased flow diffusion results. The geometric arrangement can eliminate the outer casing of the exhaust hood over the axial length of the turbine inner casing, allowing the turbine inner casing to be supported directly by a foundation for the steam turbine.

Abstract: A cover of an airfoil having opposing pressure and suction sides of a rotatable turbine stage to prevent fluid from crossover-flowing from a pressure side of a leading airfoil to a suction side of a trailing airfoil is provided. The cover includes pressure and suction side edge portions, one of which having a shape that is discontinuous relative to that of a complementary one of suction and pressure side edge portions of an aft cover of a corresponding one of a trailing and a leading airfoil, respectively.

Abstract: An apparatus is provided and includes a first member with a flow diverting member extending from a surface thereof and a second member disposed proximate to the first member with a clearance gap area defined between a surface of the second member and a distal end of the flow diverting member such that a fluid path, along which fluid flows from an upstream section and through the clearance gap area, is formed between the surfaces of the first and second members. The second member is formed to define dual vortex chambers at the upstream section in which the fluid is directed to flow in vortex patterns prior to being permitted to flow through the clearance gap area.

Abstract: A turbomachine includes a housing having an inner surface, a compressor, a turbine and a rotary member including a plurality of blade members configured as part of one of the compressor and the turbine. Each of the plurality of blade members includes a base portion and a tip portion. The turbomachine also includes a honeycomb seal member mounted to the inner surface of the housing adjacent the rotary member. The honeycomb seal member includes a contoured surface having formed therein a deformation zone. The deformation zone includes an inlet zone and an outlet zone. The inlet zone is spaced a first distance from the tip portion of each of the plurality of blade members and the outlet zone is spaced a second distance from the tip portion of each of the plurality of blade members. The second distance being substantially equal to or less than the first distance.