Abstract: A balance piston seal assembly for a balance piston of a compressor is provided. The balance piston seal assembly may include a balance piston seal, a stationary support, and a gripping assembly disposed between the balance piston seal and the stationary support. The balance piston seal may be configured to be disposed about the balance piston such that an inner radial surface of the balance piston seal and an outer radial surface of the balance piston define a radial clearance therebetween. The stationary support may be configured to be coupled or integral with a casing of the compressor. The gripping assembly may be configured to secure the balance piston seal with the stationary support and to maintain concentricity between the balance piston seal and the balance piston during thermal radial expansion of the balance piston seal relative to the balance piston.

Abstract: A method for operating a compressed air energy storage system is provided. The method can include compressing a process gas with a compressor train to produce a compressed process gas and storing the compressed process gas in a compressed gas storage unit. The method can also include extracting the compressed process gas from the compressed gas storage unit to an expansion assembly through a feed line. A valve assembly fluidly coupled to the feed line can be actuated to control a mass flow of the compressed process gas from the compressed gas storage unit to the expansion assembly. The method can further include heating the compressed process gas in a preheater fluidly coupled to the feed line upstream from the expansion assembly, and generating a power output with the expansion assembly.

Abstract: A collection apparatus for a separator. The collection apparatus including a housing at least partially encircling a flow separation passage and defining a chamber and a cutout, the chamber being in fluid communication with the flow separation passage to receive a separated flow therefrom, and the cutout extending outward from the chamber to at least partially deflect the separated flow.

Abstract: A separator method and apparatus that includes a rotatable drum defining an annular passageway therein, a plurality of blades coupled to the rotatable drum and located in the annular passageway, each of the plurality of blades including a leading section, a trailing section, a concave surface, and a convex surface, the concave and convex surfaces extending from the leading section to the trailing section, each of the plurality of blades disposed circumferentially adjacent to at least another one of the plurality of blades so as to define blade flowpaths therebetween, and a housing at least partially surrounding the rotatable drum and defining a fluid collection chamber fluidly communicating with the annular passageway.

Abstract: A system and method for controlling the acoustic signature of a turbomachine having a plurality of valves wherein an operating load is identified and an arc of admission across a plurality of nozzles is associated therewith. A valve sequencing scheme is selected and implemented to activate the arc of admission for a particular operating load so as to minimize valve noise by adjusting valves simultaneously rather than consecutively.

Abstract: A fluid processing device may include a rotatable shaft, a driver configured to drive the rotatable shaft, a separator installed on the rotatable shaft, and a supersonic compressor fluidly communicating with the separator.

Abstract: A seal for a turbomachine is disclosed. The seal assembly includes a rotatable shaft having a stepped outer circumferential surface that defines one or more annular protrusions axially-spaced thereon. A seal is radially-offset from the rotatable shaft and has one or more annular recesses that extend radially-outward from the inner circumferential surface of the seal. A plurality of holes are defined in both the inner circumferential surface and the one or more annular recesses of the seal, the one or more annular recesses being axially-spaced from each other and configured to receive the one or more annular protrusions in an interlocking fit.

Abstract: An annular seal may include a seal body configured for disposing around a rotor, a plurality of grooves and a plurality of projections formed on an inner circumferential surface of the seal body, and a plurality of dams circumferentially disposed on a first surface of the seal body. The first surface may extend radially from the inner circumferential surface of the seal body. The plurality of dams may be configured to increase a pressure of a working fluid contacting the plurality of dams such that the increase in the pressure may center the annular seal about the rotor.

Abstract: A shaft of a compressor may include a first shaft section defining a first cavity axially extending therein and a second shaft section defining a second cavity axially extending therein. A plurality of inlet holes may be defined on an outer surface of the first shaft section, and a plurality of outlet holes may be defined on an outer surface of the second shaft section. The plurality of inlet holes may be in fluid communication with the first cavity and the plurality of outlet holes may be in fluid communication with the second cavity. The first cavity and the second cavity may form a passageway fluidly coupling the plurality of inlet holes and the plurality of outlet holes.

Abstract: A fluid takeoff assembly for a motor-compressor is provided and includes an outer pipe having an inlet and an outlet, and an inner pipe defining a fluid passage extending from an open axial end toward a closed axial end thereof and a radial opening fluidly coupled with the fluid passage. The inner pipe may be disposed in the outer pipe such that the open axial end and the closed axial end are oriented toward the outlet and the inlet, respectively, and the inner and outer pipes define an annular space therebetween. A cross-flow member may be coupled with the inner pipe and may define a flowpath fluidly coupled with the fluid passage via the radial opening. A vane and the cross-flow member may be disposed in the annular space and configured to at least partially induce a swirling flow in a process fluid flowing through the annular space.

Abstract: A method for retrofitting a turbomachine is provided wherein a first trip cup of the turbomachine is replaced with a second trip cup and by replacing a mechanical flyweight governor with a mechanical-hydraulic governor. The second trip cup includes a plunger disposed in a hole defined by the second trip cup. The first trip cup is removed from the turbomachine and the second trip cup installed such that, when a speed of the turbomachine exceeds a predetermined value, the plunger actuates a trip paddle located adjacent the second trip cup. The mechanical flyweight governor is removed from the turbomachine and a first set of governor linkages coupling the mechanical flyweight governor to a steam source. The mechanical-hydraulic governor is installed in the turbomachine, the mechanical-hydraulic governor being coupled to a shaft of the turbomachine and being coupled to the steam source via a second set of governor linkages.

Abstract: A mounting system for an industrial compression system including a first component close-coupled to a second component includes a first support for the first component. The first support is configured to resist movement of the first component in a first direction substantially horizontal relative to the first component, a second direction substantially vertical relative to the first component, and an axial direction relative to the first component. The mounting system also includes a second support for the second component. The second support is configured to resist movement of the second component in a first direction substantially horizontal relative to the second component and a second direction substantially vertical relative to the second component, wherein the second support permits movement of the second component in an axial direction relative to the second component.

Abstract: An apparatus and method for protecting an inner radial surface of a radial member of a turbomachine from corrosion are provided. The method may include shaping the inner radial surface of the radial member and a corresponding outer radial surface of a corrosion-resistant liner. The method may also include heating the radial member to increase a diameter of the inner radial surface of the radial member, and inserting at least a portion of the corrosion-resistant liner into the radial member. The method may further include attaching the corrosion-resistant liner to the inner radial surface of the radial member to thereby protect the inner radial surface of the radial member of the turbomachine from corrosion.

Abstract: A clamping and support system for a turbine is disclosed. The clamping and support system may include a support bar coupled with a lower diaphragm portion of the turbine. The support bar may have a protuberance extending from a first end portion thereof that may at least partially extend into a slot formed in the lower diaphragm portion of the turbine. The clamping and support system may also include a clamping bar coupled with a second end portion of the support bar. The clamping bar may at least partially extend into a slot formed in an upper diaphragm portion of the turbine such that at least a portion of the lower diaphragm portion and at least a portion of the upper diaphragm portion are interposed between the clamping bar and the protuberance of the support bar, thereby coupling the lower diaphragm portion with the upper diaphragm portion.

Abstract: An oscillating water column (OWC) turbine and method of extracting energy therefrom is provided. The OWC turbine includes a shaft (101) rotatable about a central axis (103), and first and second ports (112, 114) disposed around the central axis. A flow passage (104) extends radially-inward from the ports and extends axially therebetween. Rotor blades (120) are coupled to the shaft, intersect the flow passage, and are offset from the central axis by a first distance. First guide vanes (116) intersect the flow passage and are disposed proximal the first port. The first guide vanes (116) include first and second stators (116a, b), the first stators (116a) being positioned between the first port (112) and the second stators (116b). Second guide vanes (118) intersect the flow passage and are disposed proximal the second port. The first and second guide vanes are offset from the central axis by a second distance that is greater than the first distance.

Abstract: A cooling system for a motor-compressor and a method for cooling the motor-compressor are provided. The cooling system may include a discharge assembly having a hub portion disposed radially outward of a rotary shaft of the motor-compressor. A plurality of arms may be fluidly coupled with and may extend generally tangential from the hub portion of the discharge assembly. The hub portion may define an annular volume fluidly coupled with the plurality of arms. The cooling system may also include a blower impeller disposed in the annular volume and coupled with the rotary shaft. The blower impeller may be configured to rotate with the rotary shaft and draw a cooling fluid into the discharge assembly.

Abstract: A turbine arrangement for a bi-directional reversing flow is provided. The turbine arrangement may include a rotor rotatably mounted to rotate about an axis of the turbine arrangement, and the rotor may have a plurality of rotor blades disposed circumferentially thereabout. A first set of guide vanes may be circumferentially disposed about the axis for directing the bi-directional reversing flow to and from the rotor blades via a first flow passaged defined by a first duct. A second set of guide vanes may be axially spaced from the first set of guide vanes and circumferentially disposed about the axis for directing the bi-directional reversing flow to and from the rotor blades via a second flow passage defined by a second duct. The guide vanes may be disposed at a greater radius than the rotor blades, such that the guide vanes are radially offset from the rotor blades.

Abstract: A grid valve may include an annular stationary plate having a first annular surface, and an annular rotatable plate disposed on the annular stationary plate and rotatable relative to the annular stationary plate. The annular rotatable plate may have a second annular surface, and each of the annular stationary plate and the annular rotatable plate may define a plurality of holes in the respective annular surfaces thereof. The grid valve may further include a first magnet disposed on the first annular surface and a second magnet disposed on the second annular surface such that the first magnet repels the second magnet.

Abstract: A seal assembly is disclosed that can be used to seal a bearing case in a turbine. The seal assembly has an annular seal plate seated within a groove defined in the bearing case and radially-offset from the turbine shaft. A seal retainer is mounted on the shaft axially-offset from the annular seal plate and defines a channel therein for receiving and seating a seal therein. The seal has a flexible lip that extends from the body of the seal and engages either the inside surface of the bearing case or a counterface of the annular seal plate, thereby preventing or substantially restricting the influx of contaminants into the bearing case.

Abstract: A tilt pad bearing may include a support structure having first and second support structure surfaces. A pivot may have first and second pivot surfaces, and the first pivot surface may be coupled to the second support structure surface. A pad may have first and second pad surfaces, and the first pad surface may be coupled to the second pivot surface. A path of fluid communication may extend from the first support structure surface, through the pivot, and to an opening in the second pad surface.