Abstract: A turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion between the protrusion and the recess. The flexible portion has a bent cross-section perpendicular to the parting line. An outer surface of the bent cross-section contacts an inner surface of the recess. An inner surface of the bent cross-section contacts an outer surface of the protrusion. Sealing a parting line between two parts of a diffuser in a gas turbine system includes disposing a flexible portion between a protrusion and a recess of the two parts, contacting an outer surface of the bent cross-section with an inner surface of the recess, contacting an inner surface of the bent cross-section with an outer surface of the protrusion, and pressurizing the diffuser.

Abstract: This application provides exhaust frame cooling systems for use with gas turbine engines. Example systems may include an exhaust system for use with a gas turbine engine. The exhaust system may include a strut positioned between an inner barrel and an outer barrel. The strut may include an inner body and an outer body. The exhaust system may include at least one strut hole formed in the inner body, where the at least one strut hole forms a first cooling path for cooling flow in a first direction, a cavity between the inner body and the outer body, where the cavity forms a second cooling path for the cooling flow in a second direction, and a purge outlet to purge the cooling flow at the inner barrel.

Abstract: A turbine or turbine system includes a compressor, a combustor, a turbine section, a diffuser with a parting line between two components, and a seal along the parting line. The seal includes a protrusion, a recess, and a flexible portion between the protrusion and the recess. The flexible portion has a bent cross-section perpendicular to the parting line. An outer surface of the bent cross-section contacts an inner surface of the recess. An inner surface of the bent cross-section contacts an outer surface of the protrusion. Sealing a parting line between two parts of a diffuser in a gas turbine system includes disposing a flexible portion between a protrusion and a recess of the two parts, contacting an outer surface of the bent cross-section with an inner surface of the recess, contacting an inner surface of the bent cross-section with an outer surface of the protrusion, and pressurizing the diffuser.

Abstract: A system is provided including a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an outer structure having an outer casing and an outer exhaust wall disposed along the exhaust flow path. An inner structure of the turbine exhaust section includes an inner exhaust wall disposed along the exhaust flow path. A strut extends between the outer structure and the inner structure, and the strut is configured to convey a flow of fluid from the inner structure toward the outer structure. The strut includes a plurality of cooling fins to facilitate heat transfer from the strut to the flow of fluid.

Abstract: A clearance control system for a turbine having a stator assembly and a rotor assembly includes a hydraulic or pneumatic controller that axially drives, through a shaft, one or more actuators connected to the stator assembly casing. The controller causes relative movement between the stator and rotor assemblies to adjust the clearances between portions of the stator and rotor in accordance with the varying operating conditions of the turbine. More particularly, the controller moves the stator relative to the rotor in first and second axial directions to compensate for thermal expansion and contraction during the operating conditions of the turbine.

Abstract: A seal end attachment is provided and includes a vessel through which a working fluid flows, the vessel being formed to define a recess with a mating surface therein, a seal contacting the mating surface and a pressing member being more responsive to a high temperature condition associated with the flow of the working fluid than the vessel and being disposed within the recess to press the seal against the mating surface responsive to the condition being present.

Abstract: A turbomachine seal assembly includes a base member, a rocker arm pivotally mounted to the base member, and a seal element fixedly mounted to the rocker arm. The seal element is configured and disposed to selectively shift relative to the base member.

Abstract: A dual flow steam turbine includes coolant passageways which extract coolant steam from the main steam flow paths at locations downstream from the inlet. The coolant passageways conduct the coolant steam through portions of the dual flow steam turbine which are subjected to a high temperature flow. In some cases, the passageways conduct the coolant steam through first stage nozzle boxes and an inlet assembly of the dual flow steam turbine. In some cases, the inlet assembly of the steam turbine includes an annular diaphragm, and a coolant passageway passes through the annular diaphragm to help cool the annular diaphragm.

Abstract: The present application provides a rotor coupling guard for use with removing a flow of air about a rotor coupling of a turbo-machine. The rotor coupling guard may include an inner cover with a number of apertures surrounding the rotor coupling and an outer cover surrounding the inner cover. Rotation of the rotor coupling forces the flow of air through the apertures in the inner cover and away from the rotor coupling.

Abstract: In accordance with one embodiment, a system includes a turbine engine including an axial-radial diffuser section disposed about a first longitudinal axis downstream in an exhaust flow path from a turbine section. The system also includes an exhaust plenum including a first plenum portion disposed about the axial-radial diffuser section, wherein the first plenum portion includes a curved wall portion that diverges away from a circumference of the axial-radial diffuser section. The exhaust plenum also includes a second plenum portion extending away from the first plenum portion downstream along a second longitudinal axis of the exhaust plenum approximately crosswise to the first longitudinal axis.

Abstract: A clearance control system for a turbine having a stator assembly and a rotor assembly includes a hydraulic or pneumatic controller that axially drives, through a shaft, one or more actuators connected to the stator assembly casing. The controller causes relative movement between the stator and rotor assemblies to adjust the clearances between portions of the stator and rotor in accordance with the varying operating conditions of the turbine. More particularly, the controller moves the stator relative to the rotor in first and second axial directions to compensate for thermal expansion and contraction during the operating conditions of the turbine.

Abstract: An adverse pressure gradient seal mechanism for use with variable speed components. The adverse pressure gradient seal mechanism may include a number of labyrinth teeth positioned on a component and an adverse pressure gradient seal positioned between a pair of the labyrinth teeth. The adverse pressure gradient seal may include a number of strips with each of the strips having an angled end.

Abstract: A system and device for controlling fluid flow through a gas turbine exhaust. One gas turbine exhaust may include a strut of the gas turbine exhaust having a first opening configured to permit a fluid to flow between an interior portion of the strut and an exterior portion of the strut. The gas turbine exhaust also may include a moveable plate coupled to the strut and configured to control an amount of the fluid flowing through the first opening.

Abstract: A dual flow steam turbine includes coolant passageways which extract coolant steam from the main steam flow paths at locations downstream from the inlet. The coolant passageways conduct the coolant steam through portions of the dual flow steam turbine which are subjected to a high temperature flow. In some cases, the passageways conduct the coolant steam through first stage nozzle boxes and an inlet assembly of the dual flow steam turbine. In some cases, the inlet assembly of the steam turbine includes an annular diaphragm, and a coolant passageway passes through the annular diaphragm to help cool the annular diaphragm.

Abstract: An apparatus is provided and includes a plenum into which a fluid is exhausted, the plenum including a wall toward which the exhausted fluid is directed, the wall including first sections, second sections interposed between the first sections and a flow splitter interposed between the second sections, and a plane of the second sections being recessed from a plane of the first sections and the flow splitter protruding from the plane of the second sections.

Abstract: A turbomachine seal assembly includes a base member, a rocker arm pivotally mounted to the base member, and a seal element fixedly mounted to the rocker arm. The seal element is configured and disposed to selectively shift relative to the base member.

Abstract: A seal end attachment is provided and includes a vessel through which a working fluid flows, the vessel being formed to define a recess with a mating surface therein, a seal contacting the mating surface and a pressing member being more responsive to a high temperature condition associated with the flow of the working fluid than the vessel and being disposed within the recess to press the seal against the mating surface responsive to the condition being present.

Abstract: A turbine is provided and includes a spacer having an annular body formed with opposing outward and inward surfaces and an orifice extending through the body from the outward to the inward surface, an assembly to secure the spacer around a rotor axially between sequential buckets of a forward turbine stage and an aft turbine stage, the spacer forming an annular passage around the rotor into which a fluid flows through the orifice and a circuit fluidly coupled to the annular passage to deliver the fluid from between the sequential buckets of the forward turbine stage and the aft turbine stage to an axial location forward of the forward turbine stage.

Abstract: A turbomachine bucket includes a base portion having a first end that extends to a second end, and an airfoil portion extending from the first end of the base portion. The airfoil portion includes a first end section that extends to a tip section. A plurality of cooling channels extend through the turbomachine bucket from the first end of the base portion to the tip portion, and a cooling flow control member is arranged in one of the plurality of cooling channels. The cooling flow control member creates at least a partial flow restriction in the one of the plurality of cooling channels to modify cooling flow passing through the turbomachine bucket.

Abstract: Systems for shielding a shaft from contaminants are disclosed. In one embodiment, a contaminant shield system for a shaft includes: a fluid seal disposed circumferentially about the shaft, the fluid seal substantially fluidly isolating an inner portion of the shaft from atmospheric air; an oil deflector ring disposed circumferentially about the inner portion of the shaft, the oil deflector ring having an inner surface facing a portion of the shaft exposed to a lubricating oil and an outer surface facing the fluid seal; and a fluid conduit interposed between the fluid seal and the outer surface of the oil deflector ring, the fluid conduit for receiving a fluid and releasing the fluid between the fluid seal and the outer surface of the oil deflector ring creating a positive pressure differential.