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: An acoustic resonator assembly may include a first acoustic liner and a second acoustic liner. The first acoustic liner may define a first plurality of openings extending between first and second surfaces thereof. The second acoustic liner may be rotatably coupled to the first acoustic liner and at least one of the first acoustic liner and the second acoustic liner may be configured to rotate relative to each other to attenuate one or more frequencies of acoustic energy generated by working fluid flowing past the acoustic resonator assembly. The second acoustic liner may define a second plurality of openings extending between first and second surfaces thereof. A number of degrees of freedom of the acoustic resonator assembly may be varied by rotating the first acoustic liner and/or the second acoustic liner.

Abstract: A system and method for rapid pressurization of a motor compartment and cooling system during a shutdown, a surge, and/or other situations in which the suction pressure significantly varies. A motor/compressor arrangement includes a seal gas system fluidly communicating with the motor compartment via a motor pressurization line, with the outlet of the compressor, and with a shaft seal. A motor pressurization valve is coupled to the motor pressurization line and a controller is configured to open the motor pressurization valve at start-up of the motor-compressor to supply seal gas to the motor compartment and to pressurize the motor compartment when a difference between the seal gas supply pressure and the suction pressure is indicative of the seal gas supply pressure being insufficient.

Abstract: An adjustable seal and method for varying a radial distance between the adjustable seal and a rotor of a turbomachine are provided. The adjustable seal may include a first annular member defining a plurality of radial channels, and a second annular member defining a plurality of slots at least partially extending therethrough. The second annular member may be concentric with the first annular member and configured to rotate relative to the first annular member. The adjustable seal may also include a plurality of seal segments interposed between the first annular member and the second annular member. Each seal segment of the plurality of seal segments may be slidably disposed in a respective radial channel of the plurality of radial channels and may have an axial projection slidably disposed in a respective slot of the plurality of slots.

Abstract: A shut-off valve for a turbine of an oscillating water column may include a plurality of guide vanes configured to control a fluid flow into a flow passage defined by the turbine. The plurality of guide vanes may be at least partially disposed within the flow passage and may include a plurality of fixed guide vanes and a plurality of movable guide vanes. The plurality of fixed guide vanes and the plurality of movable guide vanes may be sequentially disposed in an alternating pattern in the flow passage.

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: A system and method for producing liquefied natural gas are provided. The method may include compressing a process stream containing natural gas in a compression assembly to produce a compressed process stream. The method may also include removing non-hydrocarbons from the compressed process stream in a separator, and cooling the compressed process stream with a cooling assembly to thereby produce a cooled, compressed process stream containing natural gas in a supercritical state. The method may further include expanding a first portion and a second portion of the natural gas from the cooled, compressed process stream in a first expansion element and a second expansion element to generate a first refrigeration stream and a second refrigeration stream, respectively. The method may further include cooling the natural gas in the cooled, compressed process stream to a supercritical state with the first and second refrigeration streams to thereby produce the liquefied natural gas.

Abstract: A gas turbine nozzle can be refurbished to reduce downstream deflection. The outer shroud of the gas turbine nozzle is held in a fixture, and then the nozzle is heated. The heated nozzle is then reshaped by a force exerted upon the inner shroud of the gas turbine, reducing the downstream deflection of the nozzle. After the deformation of the nozzle, an aft hook of the nozzle that has been adjusted by previous refurbishment efforts can be rebuilt to remove the previous adjustments.

Abstract: A compression system may include a compressor having first and second sides separated by a division wall, first and second shafts, and first and second radial bearings. The first and second shafts may be axially connected to each other at respective first ends via a rotor portion of an intermediate radial bearing. The rotor portion may include a plurality of laminations stacked between first and second plates fastened to each other. The first radial bearing may be disposed on a first side of the intermediate radial bearing and may be proximate a second end of the first shaft. The first radial bearing may be configured to support the first shaft. The second radial bearing may be disposed on a second side of the intermediate radial bearing and may be proximate a second end of the second shaft. The second radial bearing may be configured to support the second shaft.

Abstract: A support assembly and method for supporting an internal assembly in a casing of a turbomachine are provided. The support assembly may include a support member that may be slidably disposed in a recess formed in the internal assembly and configured to engage an inner surface of the casing. A biasing member may be disposed in a pocket extending radially inward from the recess. The biasing member may at least partially extend into the recess and may be configured to apply a biasing force to the support member disposed therein.

Abstract: A gas turbine may include a rotatable shaft, a compressor disposed about the rotatable shaft and configured to output compressed air, and a combustor disposed about the rotatable shaft. The combustor may be configured to receive the compressed air and output high temperature compressed gas. The gas turbine may further include a power turbine disposed about the rotatable shaft and configured to receive the high temperature compressed gas, and a first liner defining a plurality of holes and disposed around the combustor. The power turbine may be configured to expand the high temperature compressed gas and rotate the rotatable shaft. The first liner may have a first end and a longitudinally opposite second end. The first end may be coupled to an inner surface of the casing at or adjacent an upstream end of the combustor and the second end may be substantially free from any connection with the casing.

Abstract: A stator can for an electric motor of a motor-compressor is provided. The stator can may include an annular body configured to be disposed radially outward of a rotor of the electric motor. An inner radial surface of the annular body and an outer radial surface of the rotor may at least partially define a radial gap therebetween, and a first axial end portion of the annular body may at least partially define an inlet of the radial gap. The stator can may include a plurality of swirl breaks disposed about the first axial end portion of the annular body. The plurality of swirl breaks may be configured to reduce a swirling flow of the process fluid flowing to the inlet of the radial gap.

Abstract: An impeller may include a hub section, a plurality of blades, and a shroud. The hub section may be mounted on a rotatable shaft. The hub section may define a central opening for the rotatable shaft to extend therethrough and may define a plurality of holes disposed in a circular manner about the central opening. The plurality of blades may be connected to or integral with the hub section. The shroud may be connected to or integral with the hub section and the plurality of blades. The plurality of holes may be either through holes or partially drilled holes. A bottom of some or all of the partially drilled holes may be flat, conical, or rounded. Some or all of the partially drilled holes may have one or more bleed holes that may permit quenching material to flow therethrough and prevent the quenching material from stagnating therein.

Abstract: Methods for retrofitting a turbomachine are provided. A first trip cup of the turbomachine may be replaced with a second trip cup. The first trip cup may include a throw-out arm connected to a first trip cup spring. The second trip cup may include a plunger disposed in a hole defined by the second trip cup and a plunger spring encircling the plunger in the hole. The first trip cup may be removed from the turbomachine and the second trip cup installed such that a location of the plunger in the turbomachine is the same as a location of the throw-out arm in the turbomachine when the first trip cup was installed on the turbomachine. The tension in the plunger spring may be adjusted such that, when a speed of the turbomachine exceeds a predetermined value, the plunger actuates a trip paddle located adjacent the second trip cup.

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 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 balance piston seal assembly may also include a plurality of heaters in thermal communication with the balance piston seal and configured to heat and thermally expand the balance piston seal and thereby increase a radial length of the radial clearance.

Abstract: A non-contacting seal is provided, including a first sealing face formed on an end of a primary ring and a second sealing face formed on an end of a mating ring. Grooves may be formed in at least one of the first and second sealing faces, such that the grooves extend from one edge of the respective sealing face to an intermediate radius of the respective sealing face. At least one groove may include an entrance edge along the one edge of the respective sealing face and a dam wall opposite the entrance edge. The at least one groove may also include two symmetric side walls extending from the entrance edge to the dam wall. The two symmetric side walls may include a first convex curve extending from the entrance edge to a transition point and a second concave curve extending from the transition point to the dam wall.

Abstract: A system and method are provided for a compressed air energy storage (CAES) system. The system and method may include compressing a process gas with a compressor train to produce a compressed process gas. The compressed process gas may be directed to a compressed gas storage unit and stored therein. The compressed process gas from the compressed gas storage unit may be released to a heat recovery unit via a feed line. The heat recovery unit may heat the compressed process gas and direct the heated compressed process gas to an expansion assembly to generate a power output. Feed water from a feed water source may be heated in the heat recovery unit to produce steam for injection into a combustion turbine assembly. The combustion turbine assembly may heat the heat recovery unit via an exhaust line.

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 cooling system for a rotating machine, such as a centrifugal compressor. Specifically, the cooling system may be configured to cool radial and axial magnetic bearings in the rotating machine and the bearing control system that controls said bearings. The cooling system includes canned magnetic radial bearings on each end of the rotor and a canned bearing control system. The canned bearings and canned bearing control system may be filled with a dielectric cooling fluid and in fluid communication with each other via sealed conduits. Accordingly, the radial magnetic bearings and the bearing control system may be entirely immersed in the dielectric cooling fluid to regulate heat generation. An axial magnetic bearing may also be canned and fluidly coupled to the cooling system to immerse the axial magnetic bearing in the dielectric cooling fluid.

Abstract: A method for producing liquefied natural gas (LNG) is provided. The method may include feeding natural gas from a high-pressure natural gas source to a separator and removing a non-hydrocarbon from the natural gas. A portion of the natural gas from the separator may be precooled, and the precooled natural gas may be cooled in a first heat exchanger with a first refrigeration stream. A first portion of the cooled natural gas may be expanded in a turbo-expander to generate the first refrigeration stream. A second portion of the cooled natural gas may be cooled in a second heat exchanger with the first refrigeration stream and expanded in an expansion valve to produce a two-phase fluid containing the LNG and a vapor phase. The LNG may be separated from the vapor phase in a liquid separator and stored in a storage tank.