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 piston assembly may include a piston rod and a piston disposed on the piston rod. The piston may include a frame end cap defining a through-bore for receiving the piston rod, and the frame end cap may form a first end of the piston. The piston may include an outer end cap defining a through-bore for receiving the piston rod, and the outer end cap may form a second end of the piston. The piston may also include a center support defining a through-bore for receiving the piston rod. The center support may be disposed between the frame end cap and the outer end cap, and an outer surface of the piston rod and an inner circumferential surface of the center support may define a radial gap.

Abstract: A turbomachine component and method for fabricating the turbomachine component are provided. The turbomachine component may include a matrix material and carbon nanotubes combined with the matrix material. The matrix material may include a metal or a polymer. The carbon nanotubes may be contacted with the metal to form a metal-based carbon nanotube composite, and the metal-based carbon nanotube composite may be processed to fabricate the turbomachine component.

Abstract: A method of operating a compressed air energy storage (CAES) system includes operating a compressor train of the CAES system, thereby compressing air. The method further includes, while operating the compressor train: inter-cooling a first portion of the compressed air; further compressing the inter-cooled first portion; after-cooling the further compressed first portion; supplying the after-cooled first portion to a storage vessel; supplying a second portion of the compressed air to a combustor; combusting the second portion; and operating a turbine train of the CAES system using the combusted second portion.

Abstract: An unloader assembly and method for unloading a compressor, with the unloader assembly including one or more fingers configured to engage one or more valve elements of a suction valve of the compressor. The unloader assembly also includes a biasing member coupled to the one or more fingers and configured to bias the one or more fingers downward such that the one or more fingers follow the one or more valve elements, and an actuating rod coupled to the one or more fingers and extending longitudinally therefrom. The unloader assembly further includes a first reservoir containing a smart fluid and adapted to receive the actuating rod, and a coil disposed at least one of proximal to and within the first reservoir, with the coil being configured to produce a field when an electrical current is supplied to the coil, to change one or more viscoelastic properties of the smart fluid.

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: Apparatus and methods for supporting a compression system are provided. The apparatus includes a compressor support coupled to a compressor, and a motor support coupled to a motor, the motor and the compressor being stand-alone units and having a shaft extending therebetween. The apparatus also includes a subframe connector coupled to the compressor support and the motor support and configured to prevent radial and axial misalignment of the shaft.

Abstract: A system and method for repairing a turbine. The method includes applying a coating on an outer surface of a tenon that extends from a stator vane. The tenon may be inserted at least partially into an opening defined by an inner shroud segment of the turbine. A bushing may be inserted at least partially into the opening in the inner shroud segment of the turbine such that the tenon becomes at least partially disposed within an opening defined by the bushing. A bolt may be inserted through the opening in the bushing and at least partially into an opening defined by the tenon. The bolt may be threadably engaged with the tenon.

Abstract: A system and method for producing liquefied natural gas from a natural gas source is provided. The method may include feeding natural gas provided by the natural gas source to a liquefaction module. The method may also include flowing the natural gas through a product stream of the liquefaction module. The method may further include flowing a process fluid through a liquefaction stream of the liquefaction module to cool at least a portion of the natural gas flowing through the product stream to produce the liquefied natural gas.

Abstract: A multistage separation system is provided. The multistage separation system may include a rotary shaft configured to drive a compressor. A rotating separation system may be coupled with the rotary shaft and may have an outlet in fluid communication with an inlet of the compressor. A static separation system may be coupled with a front end portion of the rotating separation system. The static separation system may include an axial inlet configured to receive a fluid and a static separation curve fluidly coupled with and disposed radially outward of the axial inlet. The static separation curve may include an outlet fluidly coupled with an inlet of the rotating separation system.

Abstract: A system and method of counterbalancing an aerodynamic thrust force generated by the impellers of a centrifugal compressor is disclosed. A rotor assembly includes a rotatable shaft disposed within a housing, and having a plurality of impellers axially-spaced from each other and coupled to the rotatable shaft for rotation therewith. Adjacent impellers along the rotatable shaft are each separated from each other with a stationary wall having one or more magnets coupled thereto. The magnets are disposed axially-adjacent a hub-side of each impeller such that the one or more magnets magnetically-attract each impeller toward the adjacent stationary wall, thereby reducing a net impeller thrust of the rotor assembly.

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 valve member for a poppet valve is provided. The valve member may include a valve stem, a valve head, a face formed on the valve head, a sealing surface disposed between the face and the perimeter of the valve head, a tapered socket, and a bevel. The valve stem may include an outside surface defining a stem diameter. The valve head may include a maximum diameter greater than the stem diameter. The face may be formed on the valve head opposite the valve stem. The sealing surface may include a transition ring disposed between the perimeter of the face and the maximum diameter of the valve head. The tapered socket may be disposed in an end of the valve stem, defining an opening with a socket perimeter sized to receive a spring therein.

Abstract: A supersonic compressor including a rotor to deliver a gas at supersonic conditions to a diffuser. The diffuser includes a plurality of aerodynamic ducts that have converging and diverging portions, for deceleration of gas to subsonic conditions and then for expansion of subsonic gas, to change kinetic energy of the gas to static pressure. The aerodynamic ducts include vortex generating structures for controlling boundary layer, and structures for changing the effective contraction ratio to enable starting even when the aerodynamic ducts are designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of in excess of two to one, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct.

Abstract: An annular seal is provided for use in a turbomachine. The annular seal may form a generally rectangular cross-section and may include an outer radial surface forming an outer sealing surface and defining at least one annular groove and a plurality of slots spaced circumferentially about the outer radial surface. Each slot may have an end terminating in the at least one annular groove. The annular seal may also include a first axial sidewall forming a sidewall sealing surface and a recessed portion and a second axial sidewall opposing the first axial sidewall. At least one annular groove and the plurality of slots may be configured to maintain a low pressure environment across at least a portion of the outer radial surface. The second axial sidewall, the recessed portion, and the inner radial surface may be configured to maintain a high pressure environment there across during operation of the turbomachine.

Abstract: A turbomachine system and method, with the system including a slug detector coupled to a main line to detect a slug flow in a multiphase fluid in the main line. The system also includes a compressor fluidly coupled to the main line and disposed downstream of the slug detector, and a bypass line fluidly coupled to the main line upstream of the compressor and downstream of the compressor. The system further includes at least an upstream control valve fluidly coupled to the main line upstream of the compressor and communicably coupled to the slug detector. The upstream control valve is configured to actuate between a normal position, in which the upstream control valve directs fluid to the compressor, and a bypass position, in which the upstream control valve directs fluid to the bypass line, according to when the slug detector detects a slug flow.

Abstract: A rotary shaft and method for reducing non-uniform heating thereof are provided. The rotary shaft may include a tubular body having a longitudinal axis extending therethrough. An outer surface of the tubular body may define a groove at least partially extending radially inward from the outer radial surface toward the longitudinal axis of the tubular body to define a depth thereof. The rotary shaft may include a thermal barrier at least partially disposed in the groove and configured to absorb at least a portion of heat generated from rotation thereof.

Abstract: A radial magnetic bearing may include an annular housing including a radial outer wall disposed between radially outer ends of two annular axial end plates and an isolation sleeve which may include a helical arrangement of a plurality of ferromagnetic wires. The isolation sleeve may be an annular structure extending axially between the two annular axial end plates, and the isolation sleeve and the annular housing may define an isolation cavity therebetween. The radial magnetic bearing may also include an isolation sleeve retainer configured to maintain a position of the isolation sleeve between the two annular axial end plates. The radial magnetic bearing may further include a plurality of laminations disposed adjacent the isolation sleeve and about a shaft of the rotating machine. A gap may be defined between the plurality of laminations and the isolation sleeve.

Abstract: A method is provided for fabricating iron castings for metallic components. The method for fabricating the iron castings may include forming a molten solution by melting carbon and iron and combining carbon nanomaterials with the molten solution. A first portion of the carbon nanomaterials combined with the molten solution may be dispersed therein. The method may also include cooling the molten solution to solidify at least a portion of the carbon thereof to fabricate the iron castings. The first portion of the carbon nanomaterials may be dispersed in the iron castings.

Abstract: A journal housing including a series of housing threads defined on an outer radial surface. The series of housing threads may be adapted to threadably engage a series of casing threads defined on an inner radial surface of a casing. A shoulder may extend radially-outward from the outer radial surface, and the shoulder may be disposable axially-adjacent the casing and adapted to receive at least one first mechanical fastener.