A supersonic diffuser for use in turbomachinery adapted to impart thermal energy to a process fluid is provided. The diffuser includes a vaned zone configured to define a passageway having a flow area to pass a flow of a process fluid at supersonic velocity. The vaned zone is configured to define a step-change to the flow area of the passageway at a given location, such as where the flow of the process fluid exits the vaned zone. The diffuser further includes a shock zone coupled to the vaned zone to pass the flow of the process fluid that exits the vaned zone. The shock zone is configured to support a system of shock waves that increases static temperature of the process fluid downstream of the system of shock waves. A mixing and subsonic diffusion is configured to decelerate process fluid from the shock zone to a reduced subsonic speed prior to discharge of the process fluid through an exit of the diffuser.
An inlet valve system (10), as may be used for a cylinder chamber (20) of a compressor, such as a reciprocating compressor, is disclosed. A plurality of inlet valves (250) is movable between an open position and a closed position. The plurality of inlet valves is arranged between an unloader chamber (120) and a cylinder chamber (20) of the compressor. A control valve (270, 270') is coupled to a controller (300) and is movable between a first position and a second position to close the inlet valves. A check valve (260, 260') is movable between a first position and a second position to open the inlet valves. The check valve and the control valve are respectively fluidly coupled to a control chamber (252), which is decoupled from any pressure control external to cylinder chamber (20).
F04B 39/10 - Adaptation ou aménagement des organes de distribution
F04B 7/00 - "Machines" ou pompes à piston caractérisées par un entraînement desmodromique des organes du mécanisme de distribution
F04B 7/02 - "Machines" ou pompes à piston caractérisées par un entraînement desmodromique des organes du mécanisme de distribution le mécanisme de distribution étant actionnés par un fluide
F04B 49/03 - Commande d'arrêt, de démarrage, de décharge ou de ralenti par clapets
An unloader valve includes a seat including a plurality of inlet apertures spaced apart from one another and extending through the seat along one of a plurality of parallel inlet axes. A manifold plate is fixedly connected to the seat and includes a plurality of outlet apertures, each spaced apart from one another and extending through the manifold plate along one of a plurality of parallel outlet axes. The unloader valve also includes a plurality of plug holes, a control chamber formed in the manifold plate, and a control space fully defined by the manifold plate and arranged to fluidly connect the control chamber and each of the plug holes to one another. The unloader valve also includes a control member disposed within the control chamber and movable between a first position in which the control space is exposed to a pressure source, and a second position in which the control space is isolated and a plurality of plugs, each positioned within one of the plug holes and movable between a closed position in which each plug closes one of the inlet apertures and an open position in which the plurality of inlet openings are in fluid communication with the plurality of outlet openings.
A compressor valve assembly is disclosed. The valve assembly includes a guide having a cylindrical cup portion and a cylindrical stem portion that extends axially in a socket where the guide can be removably affixed to a stop plate. The disclosed valve assembly is conducive to user-friendly serviceability while realizing an increased flow area with operational capability at relatively higher pressures and practically no susceptibility to bending stresses.
Compressor rotor structure for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from sealing sleeves that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by the compressor. The sealing sleeves may be affixed to adjoining structures (e.g., adjoining impeller bodies) by way of a slip fit connection to one of the adjoining structures and an interference fit connection with respect to the other adjoining structure, which is conducive to a user-friendly assembly of the sealing sleeves with the adjoining structures.
Rotor structure for a turbomachine, such as a centrifugal compressor is provided. Disclosed embodiments make use of venting/sealing arrangements effective for venting a tie bolt rotor so that, for example, an incipient leakage of a process fluid can be monitored. Additionally, in operation disclosed embodiments are effective to, for example, convey to the tie bolt a pressurized sealing fluid effective for reducing the likelihood of process fluid escaping to the atmosphere.
A reciprocating compressor includes a compressor cylinder defining a cylinder wall, a valve bore formed in the cylinder wall, and a compressor valve assembly arranged in the compressor cylinder. The compressor valve assembly includes a valve liner having a liner body and a liner flange disposed at an end of the liner body. The liner body is disposed in the valve bore. The liner flange is positioned in contact with the compressor cylinder. A valve seat is coupled to an inner surface of the liner body. The valve seat has a seating surface formed at an end of the valve seat. A compressor valve is positioned on the seating surface of the valve seat. A valve cage is positioned on the compressor valve. A valve cover is coupled to the valve cage to apply a bias force to retain the compressor valve on the seating surface of the valve seat.
A pumped heat energy storage (PHES) system, involving an annular ducting arrangement is provided. Disclosed embodiments are believed to resolve the issue of containing a high temperature working fluid at elevated pressure by appropriately compartmentalizing by way of the annular ducting arrangement the functions of temperature management and pressure containment in a cost-effective and reliable manner.
F02C 1/04 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de gaz chauds ou de gaz sous pression non chauffés, comme fluide de travail le fluide de travail étant chauffé indirectement
F02C 6/14 - Ensembles fonctionnels de turbines à gaz comportant des moyens pour emmagasiner l'énergie, p. ex. pour faire face à des pointes de charge
F28D 20/02 - Appareils ou ensembles fonctionnels d'accumulation de chaleur en généralAppareils échangeurs de chaleur de régénération non couverts par les groupes ou utilisant la chaleur latente
A non-contact seal assembly for sealing a circumferential gap between a first machine component and a second machine component which is rotatable relative to the first machine component about a longitudinal axis is provided. The non-contact seal assembly includes a seal carrier, a primary seal that includes a plurality of shoes, a mid plate, a secondary seal, and a front plate. The secondary seal may comprise a plurality of sealing segments. The non-contact seal also includes a plurality of damping elements to damp vibrations of the primary seal during operation.
An improved inlet valve system for a cylinder chamber of a reciprocating compressor and a method for utilizing a high pressure gas source to control an inlet valve system for a cylinder chamber of a reciprocating compressor is disclosed. The inlet valve system may include an unloader, a valve assembly including a cylindrical valve body circumferentially disposed about a central axis of the inlet valve system, and a control valve actuator including a control valve body. The valve assembly may include a plurality of inlet valve elements disposed respectively in valve element ports fluidly connected to a control valve passage. A high pressure gas source is utilized to hold open and close the inlet valve elements via the control valve passage in order to control the capacity of the reciprocating compressor.
F04B 39/10 - Adaptation ou aménagement des organes de distribution
F04B 49/03 - Commande d'arrêt, de démarrage, de décharge ou de ralenti par clapets
F04B 49/24 - Commande des "machines", pompes ou installations de pompage ou mesures de sécurité les concernant non prévues dans les groupes ou présentant un intérêt autre que celui visé par ces groupes par clapets de dérivation
A compressor valve assembly is presented. The compressor valve assembly includes a seat and a guard attached to each other. The seat includes an inlet hole. The guard includes a spring. The guard includes a guide pin attached to the bottom of the guard and extends out the spring internally. The guard includes a seal element attached to the guide pin. The seal element includes a socket to receive the guide pin and a spring landing area residing on top of the spring. The guide pin internally guides a movement of the seal element to move toward the inlet hole when the spring extends and to move away from the inlet hole when the spring is compressed.
A pre-combustion chamber system (100) is presented. The pre- combustion chamber system (100) includes a pre-combustion chamber housing (112) defining a pre-combustion chamber (120), a cooling chamber housing (110) surrounding the pre-combustion chamber housing (112), a cooling chamber (150) defined between the pre-combustion chamber housing (112) and the cooling chamber housing (110). The pre-combustion chamber system (100) includes a flow agitator (122) arranged in the pre-combustion chamber housing (112) protruding into the pre-combustion chamber (120). The flow agitator (122) increases flow disturbance in the pre-combustion chamber (120) for improving mixture of fuel and air.
F02B 19/10 - Moteurs caractérisés par des chambres de précombustion avec introduction partielle du combustible dans la chambre de précombustion et introduction partielle dans le cylindre
F02B 19/12 - Moteurs caractérisés par des chambres de précombustion avec allumage commandé
F02B 19/16 - Forme ou structure des chambres non spécifiques des groupes
A turbine (10) includes a disk (25) having a plurality of protrusions (120) arranged such that any two adjacent protrusions (120) define an axial entry fir tree space (125), each protrusion (120) defining an outermost lobe (165) having an outermost surface (150) and an axial length. A turbine blade (30) includes an airfoil (170), a platform (175), and a blade root (180) having a fir tree arranged to engage a leading protrusion (135) and a trailing protrusion (140). The blade root (180) and the leading protrusion (135) cooperate to define a leading gap (200), and the blade root (180) and the trailing protrusion (140) cooperate to define a trailing gap (215). A leading plug (220) is disposed in the leading gap (200) and a trailing plug (225) is disposed in the trailing gap (215). Each of the leading plug (220) and the trailing plug (225) have a plug (220) length that is at least as great as the axial length.
A platform seal and damper assembly for turbomachinery (100), such as fluidized catalytic cracking (FCC) expanders or gas turbine engines; and methodologies for forming such assembly are provided. An axially-extending groove (160) is arranged on a side (162) of a respective platform. Groove (160) is defined by a radially-outward surface (168) at an underside of the platform and a surface (170) extending with a tangential component (T) toward radially-outward surface (168). A seal and damper member (152) is disposed in groove (160), where the body of seal and damper member has adjoining surfaces (190, 188) configured to respectively engage, in response to a camming action, with the surfaces (168, 170) that define the axially-extending groove. The camming action being effective to produce an interference fit of the seal and damper member (152) with the side of the respective platform (162) and an opposed side (163) of an adjacent platform.
F01D 5/30 - Fixation des aubes au rotorPieds de pales
F01D 5/22 - Connections aube à aube, p. ex. par emboîtement
F01D 5/26 - Dispositifs antivibratoires non limités à la forme ou à la structure des pales ou aux connections aube à aube
F01D 25/06 - Systèmes antivibratoires pour empêcher la vibration des aubes
F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages
15.
BEARING AND/OR SEAL ASSEMBLY INCLUDING PERMEABLE BODY WITH FEATURES ENGINEERED TO FORM A DESIRED DISTRIBUTION PATTERN FOR A PRESSURIZED GAS CONVEYED THERETHROUGH
A bearing and/or seal assembly (10) where pressurized gas (e.g., air) may be arranged to produce a contact-free bearing and/or seal is provided. The assembly includes a permeable body (12) including structural features (13) selectively engineered to convey a pressurized gas (Ps) from an inlet side (20) side of the permeable body to an outlet side (22) of the permeable body to form an annular film of the pressurized gas relative to the rotatable shaft. Disclosed embodiments may be produced by way of three-dimensional (3D) Printing/Additive Manufacturing (AM) technologies with practically no manufacturing variability; and may also cost-effectively and reliably benefit from the relatively complex geometries and the features and/or conduits that may be involved to, for example, form the desired distribution pattern or impart a desired directionality to the pressurized gas conveyed through the permeable body of the bearing and/or seal assembly.
F16C 33/74 - Dispositifs d'étanchéité pour paliers à contact lisse
F16C 32/06 - Paliers non prévus ailleurs comprenant un élément mobile supporté par un coussinet de fluide engendré, au moins en grande partie, autrement que par la rotation de l'arbre, p. ex. paliers hydrostatiques à coussinet d'air
F16C 17/08 - Paliers à contact lisse pour mouvement de rotation exclusivement pour charges axiales uniquement pour porter la partie extrême d'un arbre ou d'un autre organe, p. ex. crapaudines
F16C 33/12 - Composition structuraleEmploi de matériaux spécifiés ou de traitement particulier des surfaces, p. ex. contre la rouille
F16C 33/14 - Procédés particuliers de fabricationRodage
A turbomachine type chemical reactor for processing a process fluid is presented. The turbomachine type chemical reactor includes at least one impeller section and a stationary diffuser section arranged downstream. The impeller section accelerates the process fluid to a supersonic flow. A shock wave is generated in the stationary diffuser section that instantaneously increases static temperature of the process fluid downstream the shock wave for processing the process fluid. Static pressure of the process fluid is simultaneously increased across the shock wave. The turbomachine type chemical reactor significantly reduces residence time of the process fluid in the chemical reactor and improves efficiency of the chemical reactor.
Process fluid flow in the primary flow passage (70) of a compressor (20) is altered by selective inclusion of one or more tooth-like, annular circumferential flanges (48) in its secondary flow passage (72). The compressor's secondary flow passage is defined between opposing surfaces of a hub (40) of the impeller (26) and the opposing hub side (64) of the housing (21). The annular circumferential flange is coupled to the hub of the impeller and/or the hub side of the compressor housing within the secondary flow passage. A compressor incorporating one or more of the annular circumferential flanges in its secondary flow passage achieves more uniform flow velocity flow within the primary flow passage.
A valve unloader assembly (10) for a reciprocating compressor and method for manufacturing the valve unloader assembly are provided. A branched support structure (11) may be disposed about a longitudinal axis of the valve unloader assembly. A plurality of struts (14) may be connected to a face of the branched support structure, and a plurality of actuating pins (16) extending from a respective distal end of a respective strut of the plurality of struts. Three-dimensional (3D) Printing/Additive Manufacturing (AM) technologies may be conducive to cost-effectively making disclosed valve unloader assemblies as may involve complex geometries and features effective to reduce pressure losses and/or vortex formation in a process fluid being compressed by the reciprocating compressor.
F04B 39/08 - Entraînement des organes de distribution
F04B 49/24 - Commande des "machines", pompes ou installations de pompage ou mesures de sécurité les concernant non prévues dans les groupes ou présentant un intérêt autre que celui visé par ces groupes par clapets de dérivation
B33Y 80/00 - Produits obtenus par fabrication additive
19.
TURBOMACHINE CHEMICAL REACTOR AND METHOD FOR CRACKING HYDROCARBONS IN A PROCESS FLUID
Chemical reactors (10) and methods crack hydrocarbons in process fluids by accelerating the process fluid to a velocity greater than Mach 1 with an axial impulse impeller (40) and generating a shock wave (90) in the process fluid by decelerating it in a static diffuser (70) having diverging diffuser passages (72). Temperature increase of the process fluid downstream of the shockwave cracks the entrained hydrocarbons in a single pass, through a unidirectional flow path (F), within a single stage, without recirculating the process fluid for another pass through the same stage. In some embodiments, the turbomachine chemical reactor (110) has multiple successive stages of one or more axial impulse impellers (40A, 40B), paired with a diverging passage, static diffuser (70). Successive stages crack additional hydrocarbons by successively raising temperature of the flowing process fluid.
An electrical connector (10) for making electrical contact with at least one lead (48) of an electronic device. The connector (10) includes a mounting flange portion (12) and a connector housing portion (14). The connector (10) also includes at least one conductor (38) having a pin end (40) and a terminal end (42), wherein the terminal end (42) includes a lead opening (44) that receives the lead (48) and a fastener hole (46) oriented substantially transverse to the lead opening (44). A fastening element (50) is used to engage the fastener hole (46) and contacts the lead (48) to form electrical contact between the conductor (38) and the lead (48). The connector (10) further includes a conductor carrier (28) that extends through the connector housing (14) and mounting flange (12). The conductor carrier (28) includes a base portion (32) and at least one extended portion (34) that extends from the base portion (32) to form a staggered arrangement. The base (32) and extended (34) portions each include a plurality of channels (36) wherein each channel (36) includes a conductor (38).
H01R 4/36 - Conducteurs logés sous l'extrémité d'une vis
H01R 13/502 - SoclesBoîtiers composés de différentes pièces
H01R 13/504 - SoclesBoîtiers composés de différentes pièces les différentes pièces étant moulées, collées, soudées, p. ex. par soudage à ultrasons, ou réunies par estampage
H01R 13/405 - Fixation d'une manière non démontable, p. ex. par moulage, rivetage
21.
RECIPROCATING COMPRESSOR WITH IMPROVED VALVE CYLINDER ASSEMBLY
A reciprocating compressor (10) with an improved valve assembly (20) is disclosed. Compressor (10) includes a cylinder block (12) having a cylinder that defines a cylindrical bore (14) extending longitudinally along a bore axis (16). Cylinder block (12) includes a hollow chamber (15) extending longitudinally along a chamber axis (18), which is non-intersecting relative to the bore axis (16). Valve assembly (20) is disposed in hollow chamber (15). Valve assembly is made up of an axially-stacked arrangement of components extending along chamber axis (18). The axially-stacked arrangement of components is spaced apart from a wall (22) that forms a perimeter of the cylinder and is thus free from mechanical interference with the perimeter of the cylinder.
A centrifugal compressor (20), with a shaftless impeller (50), is rotatively mounted on a journal. The journal is incorporated within a stationary journal shaft (40) that spans the impeller hub (52), or in a journal stub (80) that projects into at least one of the axial ends of the impeller hub, or in a pair of opposed, first and second journal stubs (142, 146). A magnetic bearing (60) is interposed between the journal and a hollow hub of the impeller. The journal and magnetic bearing support and position the impeller hub within an impeller cavity of the compressor casing (22). An independent impeller drive (151) rotates the impeller. A drive shaft (150), which is independent of the journal, is coupled to the impeller. Respective drive motor (300), rotor and stator permanent magnets, and/or electromagnetic coils are embedded within the respective, opposing journal and hub.
Single-and multi-stage compressors independently drive impellers in each compressor stage with one or more electric motors that are incorporated in the compressor casing. In multi-stage embodiments, impellers in respective compressor stages are capable of being driven at different rotational speeds. In some embodiments, the electric motor is a ring-type electric motor, where the rotor is coupled to a circumscribing impeller. The rotor in turn circumscribes the stator. In other embodiments, the electric motor is a flat or pancake-type electric motor, where its rotor is coupled to an axial sidewall of the impeller, and its stator is disposed axially outboard of and in opposed relationship with the rotor body. In some embodiments, the compressor stage incorporates a pair of flat or pancake-type electric motors. In some embodiments, rotors of the electric motors have permanent magnet-type rotor magnets, while in other embodiments the rotor magnets are electromagnetic rotor magnets.
A linear motor for moving a piston rod of a reciprocating compressor. The motor includes a guidance assembly having a moveable secondary carrier that is attached to the piston rod. The motor also includes at least one permanent magnet attached to the secondary carrier and at least one primary winding attached to the guidance assembly. In addition, the motor includes a controller that controls power supplied to the primary winding to generate a magnetic field that interacts with a magnetic field generated by the permanent magnet to provide a force that moves the permanent magnet, the secondary carrier and the piston rod in a reciprocating linear motion.
F04B 35/04 - Pompes à piston spécialement adaptées aux fluides compressibles et caractérisées par les moyens d'entraînement de leurs organes de travail ou par leur combinaison avec les machines motrices ou moteurs qui les entraînent ou bien par leurs adaptations à cet effet, non prévues ailleurs les moyens étant électriques
25.
CENTRIFUGAL COMPRESSOR ACHIEVING HIGH PRESSURE RATIO
An acoustic attenuator for a turbomachine and methodology for additively manufacturing the acoustic attenuator are provided. The acoustic attenuator includes an annular body (202) having an outer surface (204) and an inner surface (206). The inner surface of the annular body may define a bore (208) extending along a longitudinal axis (209) of the acoustic attenuator between a first end and a second end of the acoustic attenuator. The annular body may be formed by a plurality of axially-successive cross-sectional layers (e.g., 632, 634, 636) unitized between the first end and the second end of the acoustic attenuator. The plurality of axially-successive cross-sectional layers may be transversely disposed relative to the longitudinal axis of the acoustic attenuator. At least some axially-successive cross-sectional layers of the plurality of axially-successive cross-sectional layers (e.g., 632, 634, 636) defining a pocket (214) disposed between the outer surface and the inner surface of the annular body. At least a segment of a periphery of the pocket comprises two sides (2, 3) arranged to join at a common end point to form an apex (5) of the pocket.
F02C 7/045 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs destinés à supprimer le bruit
A pumped heat energy storage (PHES) system (100) including a charging circuit and a discharging circuit effective to balance or split a total heat rejection of the PHES system between the charging circuit and the discharging circuit. The charging circuit may include thermal storage vessels (102, 104) to store thermal energy generated from a first compressor (110). A first heat rejection system (128) is fluidly coupled with the thermal storage vessels to remove thermal energy from the charging circuit. The discharging circuit may include a first turbine (146) fluidly coupled with the thermal storage vessels to extract thermal energy stored in the thermal storage vessels and convert the thermal energy to mechanical energy via an expansion of a second working fluid. A second heat rejection system (156) is fluidly coupled with the thermal storage vessels and the first turbine to remove thermal energy from the discharging circuit.
F02C 6/14 - Ensembles fonctionnels de turbines à gaz comportant des moyens pour emmagasiner l'énergie, p. ex. pour faire face à des pointes de charge
F28D 20/00 - Appareils ou ensembles fonctionnels d'accumulation de chaleur en généralAppareils échangeurs de chaleur de régénération non couverts par les groupes ou
A seal apparatus (58) for a casing (12) of a turbomachine (10). The seal apparatus (58) may include an annular body (60) having first (66) and second (88) annular body portions and an appendage (94). The second annular body portion may extend axially from the first annular body portion (66) and may have an outer annular surface (88) radially offset from an outer annular surface (72) of the first annular body portion (66). The appendage (94) may extend axially from the first annular body portion (66) and may have an outer annular surface (96) and an inner annular surface (98). The inner annular surface (98) of the appendage (94) and the outer annular surface (88) of the second annular body portion (86) may define an annular cavity (116) therebetween, and at least a portion of the appendage (94) may be configured to be displaced radially outward in order to maintain contact with first (20) and second (22) inner cylindrical surfaces of the casing (12) during radial expansion of the casing (12).
An inlet duct (106) for a gas turbine wherein the inlet duct (106) may include a gas turbine inlet interface assembly (124) and a plurality of walls (126a-d) defining a first portion (128a) of an inlet flow channel (128a, 128b). The gas turbine inlet interface assembly (124) may include a mounting plate (148) pivotably connected to a first wall of the plurality of walls (126a-d) and defining a plate opening (156). The gas turbine inlet interface assembly (124) may also include an annular duct having a first end (152) coupled to or integral with the mounting plate (148), and a first end (152) configured to sealingly connect with an inlet component (116) of the gas turbine. The annular duct may define a second portion of the inlet flow channel (128b) extending from the plate opening (156). The first portion (128a) and the second portion (128b) of the inlet flow channel (128a, 128b) may be configured to fluidly couple a motive gas source with the gas turbine.
An active radial magnetic bearing assembly for a rotating machine. The active radial magnetic bearing assembly may include a housing comprising a center axis, a stator coupled to the housing, a rotor, a first target, a second target, and a plurality of sensors. At least a portion of the rotor may be configured to rotate about the center axis within the stator. The first target may be a portion of a rotor outer surface and the second target may be coupled to or formed by the rotor. The plurality of sensors may be coupled to the stator and adjacent a stator inner surface. Each sensor of the plurality of sensors may detect at least one of a radial position and an axial position of the rotor via the first target or the second target.
A system and method are provided for blending a first fuel from a first fuel source with a second fuel from a second fuel source. The system may include a controller communicatively coupled with each of a plurality of sensors, a first plurality of valves including a first progressive valve, and a second plurality of valves including a second progressive valve. The first and second plurality of valves may be configured to selectively enable fluid communication between the first and second fuel sources and a power generation unit. The controller may be configured to receive a detected operating parameter from a sensor, compare the detected operating parameter to another operating parameter, and based on the comparison, transmit an instruction to at least one of the first progressive valve and the second progressive valve to enable the first fuel to blend with the second fuel before entering the power generation unit.
F02D 19/08 - Commande des moteurs caractérisés par l'emploi de combustible non liquide, de combustibles multiples ou de substances non combustibles ajoutées au mélange carburant particulière aux moteurs fonctionnant avec des combustibles multiples, p. ex. alternativement du fuel léger et du fuel lourd, et autres que les moteurs indifférents au combustible utilisé utilisant simultanément des combustibles multiples
An exhaust system (102) for a gas turbine (100) may include a housing (120a-c), a first diffuser section (110), a second diffuser section (112), and a plurality of turning vanes (138). The first diffuser section (110) may include an annular exhaust system inlet (130). The second diffuser section (112) may be fluidly coupled to the first diffuser section (110) and may include an exhaust system outlet (136) and a longitudinal axis (114) disposed perpendicular to a longitudinal axis (116) of the first diffuser section (110). An exhaust flow passage (134a-c) may extend through the housing (120a-c) from the annular exhaust system inlet (130) to the exhaust system outlet (136). The plurality of turning vanes (138) may be disposed in a cascading arrangement and extend into the exhaust flow passage (134c) from the housing (120a-c).
A balanced switching amplifier for a magnetic bearing assembly may include a first switching amplifier configured to drive a first load of an electromagnet of the magnetic bearing assembly via a first plurality of lead wires. The balanced switching amplifier may also include a second switching amplifier configured to drive a second load of the electromagnet via a second plurality of lead wires. The first switching amplifier and the second switching amplifier may be configured to operate in tandem such that respective voltages in the first plurality of lead wires and the second plurality of lead wires substantially neutralize one another, thereby reducing electromagnetic emissions from each of the first plurality of lead wires and the second plurality of lead wires.
A fluid distribution system (208) is provided for a reactor vessel (200) defining a reaction chamber (202). The fluid distribution system (208) may include a radial distribution component (224) positionable within the reaction chamber (202) and adjacent a vessel inlet (212) at an end portion of the reactor vessel (200). The radial distribution component (224) may include one or more annular distribution conduits (230) configured to receive a fluid mixture provided to the reactor vessel (200). The fluid distribution system (208) may also include an axial distribution component (226) positionable within the reaction chamber (202) to extend from the radial distribution component (224) along a longitudinal axis of the reactor vessel (200). The axial distribution component (230) may include a plurality of helical conduits (236) fluidly coupled with the one or more annular distribution conduits (230) and configured to receive the fluid mixture from the one or more annular distribution conduits (230) and to disperse the fuel mixture uniformly within the reaction chamber (202).
A hydraulic fracturing system that includes a fixed-speed gas turbine assembly (18) having a gas generator and power turbine, both mounted to a semi-trailer. The system further includes a hydraulic pump (28) mounted to the semi-trailer and connected to an output shaft of the power turbine and a hydraulically-driven fracturing fluid pump (30) mounted to the semi-trailer and being in fluid communication with the hydraulic pump (28), the hydraulic pump (28) supplying fluid pressure to the hydraulically-driven fracturing fluid pump (30). The system is configured such that the hydraulically- driven fracturing fluid pump (30) receives fracturing fluid containing chemicals and proppants and pressurizes the fracturing fluid to a pressure sufficient for injection into a wellbore to support a hydraulic fracturing operation.
A drainage system for a stage of a turbine. The drainage system includes at least one annular recess (148) defined in the inner surface (150) of the casing (104) of the turbine and configured to accumulate liquid therein. An axial slot (142) and a radial slot (156) are formed in a diaphragm (112) of the turbine, the axial slot (142) extending between the upstream and downstream faces (134,138) of the diaphragm. The drainage system further includes a tubular member (162) including an axially extending tubular portion (164) disposed in the axial slot (142) and a radially extending tubular portion (166) disposed in the radial slot (156). The radially extending tubular portion (166) is sized and configured to fluidly couple the at least one annular recess (148) and the axially extending tubular portion (164), such that liquid in the at least one annular recess is drained therefrom and discharged from the stage of the turbine via the axially extending tubular portion (164).
A poppet valve assembly including a valve seat defining at least one inlet port configured to receive a working fluid, a valve guard coupled to or integral with the valve seat and defining at least one outlet port configured to discharge the working fluid therefrom, and a valve member disposed in a guide pocket defined in the valve guard. The valve member may include a primary impact surface configured to contact a planar surface of the valve guard facing the valve seat. The valve member may also include a secondary impact surface configured to contact a bottom portion of the valve guard within the guide pocket after a structural failure of the primary impact surface prevents substantially all of the primary contact surface from contacting the planar surface.
An inlet valve system for a cylinder chamber of a reciprocating compressor and a method for unloading the inlet valve system are provided. The inlet valve system may include an unloader, a valve assembly including a cylindrical valve body circumferentially disposed about a central axis of the inlet valve system, and a control valve actuator including a control valve body circumferentially disposed about the central axis of the inlet valve system. A control valve passage of the control valve body may extend along the central axis of the inlet valve system, a control valve element may be disposed in the control valve passage, and a control pressure source may be fluidly coupled to the control valve passage.
F04B 49/03 - Commande d'arrêt, de démarrage, de décharge ou de ralenti par clapets
F04B 49/24 - Commande des "machines", pompes ou installations de pompage ou mesures de sécurité les concernant non prévues dans les groupes ou présentant un intérêt autre que celui visé par ces groupes par clapets de dérivation
A maintenance access system for a gas turbine. The maintenance access system includes an enclosure and an inlet wall assembly coupled to the enclosure by a pivotal connector. The maintenance access system further includes a pair of rails and a dolly disposed on the pair of rails within the enclosure. The dolly includes a frame, a plurality of wheel units, and a turbine support structure, and the dolly is configured to support the gas turbine on the turbine support structure and move along the pair of rails.
System and method for cooling an expander (100) rotor assembly. The system may include an annular body (148) disposed on a rotor disc (128) of the rotor assembly (118). The rotor disc (128) may also include a plurality of rotor blades (140) mounted thereto via respective roots (142). The annular body may define at least one fluid passageway fluidly coupling the roots (142) and the cooling source (112). The annular ring (148) may be configured to prevent mixing of the flue gas (F) with a coolant (C) provided by the cooling source (112) and flowing through the at least one fluid passageway and contacting at least one root (142). The system may also include a plurality of seal members (192, 292), each disposed between respective platforms (146) of adjacent rotor blades (140) and configured to prevent flue gas (F) flowing though the expander (100) from mixing with the coolant (C).
A trip valve for a steam turbine is provided and a method for upgrading the trip valve. The trip valve (200) includes a valve body (202) defining a cavity (204), a first port (206) and a second port (208). The first and second ports are fluidly coupled with the cavity. A ball (224) defining a passage (206) is disposed in the cavity and configured to selectively provide fluid communication between the first and second ports via the passage thereof. First (242) and second (244) valve seats are disposed in the cavity and configured to at least partially support the ball in the cavity. The first valve seat is disposed between the ball and the first port, and the second valve seat is disposed between the ball and the second port. The trip valve further includes a first biasing member (258) and a second biasing member (260) configured to urge the first valve seat and the second valve seat, respectively, toward the ball.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
F16K 5/00 - Robinets à boisseau consistant seulement en un dispositif obturateur dont au moins une des faces d'obturation a la forme d'une surface de solide de révolution plus ou moins complète, le mouvement d'ouverture et de fermeture étant essentiellement rotatif
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.
B01D 45/14 - Séparation de particules dispersées dans des gaz ou des vapeurs par gravité, inertie ou force centrifuge en utilisant la force centrifuge produite par des pales, disques, tambours ou brosses rotatives
F22B 37/32 - Dispositifs séparateurs de vapeur employant la force centrifuge
B04B 7/12 - Garnitures internes, p. ex. plaques de protection
B04B 1/04 - Centrifugeurs à tambours rotatifs à parois pleines pour la séparation de mélanges essentiellement liquides contenant ou non des particules solides avec cloisons intérieures
B01D 53/24 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par force centrifuge
B01D 46/00 - Filtres ou procédés spécialement modifiés pour la séparation de particules dispersées dans des gaz ou des vapeurs
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.
A piston plug includes a cylindrical body having a longitudinal axis and an outer cylindrical surface. The outer cylindrical surface extends longitudinally between a first surface and a second surface opposite the first surface. The outer cylindrical surface defines a hole extending radially inward. The hole has a central axis perpendicular to the longitudinal axis of the cylindrical body. A first channel and a second channel are defined by cylindrical body. The first channel is in fluidic communication with the first surface and the hole. The second channel is in fluidic communication with the second surface and the hole. The first channel, the second channel, and at least a portion of the hole form a non-collinear flowpath. The piston plug is disposed in a plug hole in a piston and is retained in the plug hole via an interference fit between the piston plug and the plug hole.
F04B 39/00 - Parties constitutives, détails ou accessoires de pompes ou de systèmes de pompage spécialement adaptés aux fluides compressibles, non prévus dans les groupes ou présentant un intérêt autre que celui visé par ces groupes
F04B 53/12 - ClapetsAgencement des clapets disposés dans ou sur des pistons
A support structure for rotating machinery is provided. The support structure may include a first main hollow support member and a second main hollow support member, each having a longitudinal axis and a square cross-section. The second main hollow support member may be coupled with the first main hollow support member such that the longitudinal axis of the second main hollow support member is substantially perpendicular to the longitudinal axis of the first main hollow support member. The support structure may also include a plurality of secondary support members, each coupled with the first main hollow support member, the second main hollow support member, or the first main hollow support member and the second main hollow support member, and configured to support the rotating machinery disposed on the support structure.
A motive air conditioning system for a gas turbine assembly is provided. The motive air conditioning system may include an inlet flow channel configured to be fluidly coupled with the gas turbine assembly. The motive air conditioning system may also include a filtration assembly fluidly coupled with the inlet flow channel and configured to filter motive air. The filtration assembly may include a plurality of filter modules disposed adjacent one another and further disposed circumferentially about a longitudinal axis of the inlet flow channel.
B01D 46/00 - Filtres ou procédés spécialement modifiés pour la séparation de particules dispersées dans des gaz ou des vapeurs
B01D 46/12 - Séparateurs de particules utilisant des plaques, des feuilles ou des tampons filtrants à surface plane, p. ex. appareils de précipitation de poussières disposés en batteries
F02C 7/05 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs pour empêcher la pénétration d'objets ou de particules endommageantes
F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
47.
DIFFUSER HAVING MULTIPLE ROWS OF DIFFUSER VANES WITH DIFFERENT SOLIDITY
A diffuser for a compressor includes an annular diffuser passageway defined by a hub wall and a shroud wall of a housing of the compressor. The annular diffuser passageway may be fluidly coupled with a centrifugal impeller configured to rotate with a rotary shaft of the compressor about a center axis. The diffuser may also include a plurality of low solidity diffuser vanes extending into the annular diffuser passageway from the hub wall or the shroud wall and arranged annularly about the center axis. The diffuser may further include a plurality of high solidity diffuser vanes disposed radially outward from the plurality of low solidity diffuser vanes and extending into the annular diffuser passageway from the hub wall or the shroud wall and arranged annularly about the center axis.
A balance piston for a compressor is provided. The balance piston may include an annular body and a seal extending from an axial surface of the annular body. The annular body may be configured to be disposed about and coupled with a rotary shaft of the compressor. The seal may be configured to form a sealing engagement with at least one component of the compressor to prevent a flow of a process fluid from an impeller of the compressor to a seal cavity of the compressor.
A compressor may include a casing defining a discharge cavity and a seal cavity. A rotary shaft may be disposed in the casing, and a shaft seal assembly may be disposed in the seal cavity and about the rotary shaft. An impeller may be coupled with and configured to be driven by the rotary shaft. A balance piston may be integral with the impeller and may define the discharge cavity and the seal cavity. A balance piston seal may be disposed about the balance piston such that the balance piston seal and the balance piston define a radial clearance therebetween. The radial clearance may be configured to provide fluid communication from the impeller to the discharge cavity. A heat shield may be disposed in the discharge cavity, and may be configured to prevent the conduction of heat from the discharge cavity to the seal cavity via the casing.
An impeller includes a hub mountable to a rotary shaft and configured to rotate about a center axis. The impeller may include a plurality of main blades and splitter blades arranged equidistantly and circumferentially about the center axis. A splitter blade having a leading edge and a trailing edge may be positioned between first and second adjacent main blades and canted such that the leading edge is displaced from a blade position equidistant the first and second adjacent main blades a first percentage amount of one half an angular distance between the first and second adjacent main blades. The trailing edge may be displaced from the blade position equidistant the first and second adjacent main blades a second percentage amount of one half the angular distance between the first and second adjacent main blades. The second percentage amount may be greater or less than the first percentage amount.
An inlet guide vane assembly for a compressor is provided. The inlet guide vane assembly may include a hub configured to be disposed in an inlet of the compressor, and an inlet guide vane extending from the hub. The inlet guide vane may include a stationary section configured to be coupled with the inlet and a mobile section disposed adjacent the stationary section. The mobile section may include a rod configured to extend through an opening formed in the inlet. The inlet guide vane assembly may also include at least one biasing member disposed about the rod and configured to exert a biasing force on the mobile section to urge the mobile section radially outward.
A supersonic compressor including an inlet configured to receive and flow therethrough a process fluid. The supersonic compressor may further include a rotary shaft and a centrifugal impeller coupled therewith. The centrifugal impeller may be configured to impart energy to the process fluid received and to discharge the process fluid therefrom in at least a partially radial direction at an exit absolute Mach number of about one or greater. The supersonic compressor may further include a static diffuser circumferentially disposed about the centrifugal impeller and configured to receive the process fluid therefrom and convert the energy imparted. The supersonic compressor may further include a collector fluidly coupled to and configured to collect the process fluid exiting the diffuser, such that the supersonic compressor is configured to provide a compression ratio of at least about 8:1.
A mounting assembly for assembling a bundle of a compressor is provided. The mounting assembly may include a plurality of biasing members and a mechanical fastener. The plurality of biasing members may be disposed in a recess formed in a first annular body of the bundle, and may be configured to apply a biasing force to a second annular body of the bundle. The mechanical fastener may extend through a mounting flange of the second annular body and the plurality of biasing members. The mechanical fastener may be configured to couple the first annular body with the second annular body such that the first annular body and the second annular body define an axial gap therebetween.
A shroud for a compressor is provided. The shroud may include an inner annular member and an outer annular member. The inner annular member may include an abradable material disposed between a first end portion and a second end portion thereof. The inner annular member may further be contoured between the first end portion and the second end portion thereof. The inner annular member may be configured to be disposed proximal an impeller of the compressor such that the inner annular member and the impeller define a clearance therebetween. The outer annular member may extend axially from the second end portion of the inner annular member. The outer annular member may be configured to compliantly mount the shroud with a casing of the compressor.
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.
A compressor may include a casing defining a discharge cavity and a seal cavity. A rotary shaft may be disposed in the casing, and a shaft seal assembly may be disposed in the seal cavity and about the rotary shaft. An impeller may be coupled with and configured to be driven by the rotary shaft. A balance piston may be integral with the impeller and may define the discharge cavity and the seal cavity. A balance piston seal may be disposed about the balance piston such that the balance piston seal and the balance piston define a radial clearance therebetween. The radial clearance may be configured to provide fluid communication from the impeller to the discharge cavity. A heat shield may be disposed in the discharge cavity, and may be configured to prevent the conduction of heat from the discharge cavity to the seal cavity via the casing.
A non-contacting rotary member seal for a turbomachine is provided. The non-contacting rotary member seal may include an annular seal body having an inner annular surface extending axially from a first axial end to a second axial end. The inner annular surface may define a plurality of apertures extending into the annular seal body from the inner annular surface, where an aperture of the plurality of apertures has a first end portion at the inner annular surface and the aperture terminates at a second end portion axially offset, circumferentially offset, or both from the first end portion.
F02C 7/28 - Agencement des dispositifs d'étanchéité
F01D 11/02 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages par obturation non contact, p. ex. du type labyrinthe
An internally-cooled diaphragm for an internally-cooled compressor is provided. The internally-cooled diaphragm may include an annular body configured to cool a process fluid flowing through a fluid pathway of the internally-cooled compressor. The annular body may define a return channel of the fluid pathway, and a cooling pathway in thermal communication with the fluid pathway. The return channel may be configured to at least partially diffuse and de-swirl the process fluid flowing therethrough, and the cooling pathway may be configured to receive a coolant to absorb heat from the process fluid flowing through the return channel.
A method for fabricating a piston with a layering device via an additive manufacturing process is provided. The method may include forming a first layer of the piston on a substrate with a layering device, forming a second layer of the piston adjacent the first layer with the layering device, and binding the first layer with the second layer. The first layer of the piston may include a first material, and the second layer of the piston may include the first material and a second material.
B32B 1/00 - Produits stratifiés ayant une forme non plane
B32B 37/02 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par la séquence des opérations de stratification, p. ex. par addition de nouvelles couches à des postes successifs de stratification
B32B 37/14 - Procédés ou dispositifs pour la stratification, p. ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches
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.
F04B 39/00 - Parties constitutives, détails ou accessoires de pompes ou de systèmes de pompage spécialement adaptés aux fluides compressibles, non prévus dans les groupes ou présentant un intérêt autre que celui visé par ces groupes
F04B 53/14 - Pistons, tiges de piston ou liaisons piston-tige
A liquefaction system and method for producing liquefied natural gas (LNG) is provided. The liquefaction system may include a heat exchanger to cool natural gas to LNG, a first compressor to compress and combine first and second portions of a single mixed refrigerant from the heat exchanger, a first cooler to cool the single mixed refrigerant from the first compressor to a first liquid phase and a gaseous phase, and a first liquid separator to separate the first liquid phase from the gaseous phase. The liquefaction system may also include a second compressor to compress the gaseous phase, a second cooler to cool the compressed gaseous phase to a second liquid phase and the second portion of the single mixed refrigerant, a second liquid separator to separate the second liquid phase from the second portion of the single mixed refrigerant, and a pump to pressurize the first liquid phase.
F25J 1/00 - Procédés ou appareils de liquéfaction ou de solidification des gaz ou des mélanges gazeux
F25J 3/00 - Procédés ou appareils pour séparer les constituants des mélanges gazeux impliquant l'emploi d'une liquéfaction ou d'une solidification
F25J 3/02 - Procédés ou appareils pour séparer les constituants des mélanges gazeux impliquant l'emploi d'une liquéfaction ou d'une solidification par rectification, c.-à-d. par échange continuel de chaleur et de matière entre un courant de vapeur et un courant de liquide
62.
SYSTEM AND METHOD FOR LIQUEFIED NATURAL GAS PRODUCTION
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.
F25J 1/00 - Procédés ou appareils de liquéfaction ou de solidification des gaz ou des mélanges gazeux
F25J 3/02 - Procédés ou appareils pour séparer les constituants des mélanges gazeux impliquant l'emploi d'une liquéfaction ou d'une solidification par rectification, c.-à-d. par échange continuel de chaleur et de matière entre un courant de vapeur et un courant de liquide
F17C 7/00 - Procédés ou appareils pour vider les gaz liquéfiés, solidifiés ou comprimés contenus dans des récipients sous pression, non couverts par une autre sous-classe
F25B 1/053 - Machines, installations ou systèmes à compression à cycle irréversible à compresseur rotatif du type à turbine
F25B 9/06 - Machines, installations ou systèmes à compression dans lesquels le fluide frigorigène est l'air ou un autre gaz à point d'ébullition peu élevé utilisant des détendeurs
A metal article including an at least partially heat treated metal composition, and a method for treating the metal article are provided. The method for treating the metal article may include heating the metal article to a first holding temperature of about 690°C, and holding the metal article at the first holding temperature for at least about 10 hours. The method may also include cooling the metal article from the first holding temperature to a first cooling temperature of about 65°C or less. The method may further include heating the metal article to a second holding temperature of about 615°C, and holding the metal article at the second holding temperature for at least about 10 hours. The method may also include cooling the metal article from the second holding temperature to a second cooling temperature of about 65°C or less.
A method for fabricating a turbomachine component including a metal alloy with a layering device is provided. The method for fabricating the turbomachine component may include combining two or more elemental powders to form a powdered material. The method for fabricating the turbomachine component may also include forming a first metal alloy layer of the turbomachine component on a substrate. Forming the first metal alloy layer on the substrate may include melting a first portion of the powdered material to a first molten material with a heat source, mixing the first molten material with the heat source, and cooling the first molten material. The method for fabricating the turbomachine component may further include forming a second metal alloy layer of the turbomachine component on the first metal alloy layer, and binding the first metal alloy layer with the second metal alloy layer.
B22F 3/105 - Frittage seul en utilisant un courant électrique, un rayonnement laser ou un plasma
B22F 5/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser
B22F 7/02 - Fabrication de couches composites, de pièces ou d'objets à base de poudres métalliques, par frittage avec ou sans compactage de couches successives
A method for boosting a multiphase fluid is provided. The method may include separating the multiphase fluid into a liquid phase and a gaseous phase in a separator, compressing the gaseous phase in a compressor, and discharging the compressed gaseous phase from the compressor to the discharge line. The method may also include draining the liquid phase from the separator to a liquid reservoir, passively actuating an inlet control valve to flow the liquid phase from the liquid reservoir to a liquid tank, and actively actuating an inlet actuation valve to flow a motive gas from the compressor to the liquid tank to thereby pressurize the liquid phase contained therein. The method may further include passively actuating an outlet control valve to discharge the pressurized liquid phase from the liquid tank to the discharge line, and combining the compressed gaseous phase with the pressurized liquid phase in the discharge line.
F17D 1/14 - Transfert des liquides ou des produits visqueux par pompage
F17D 1/04 - Systèmes de canalisation pour gaz ou vapeurs pour la distribution du gaz
F17D 3/01 - Dispositions pour la surveillance ou la commande des opérations de fonctionnement pour commander, signaler ou surveiller le transfert d'un produit
F17D 3/14 - Dispositions pour la surveillance ou la commande des opérations de fonctionnement pour éliminer l'eau
A system for attenuating acoustic energy in machines is provided. The system may include an inner tube disposed about a central axis, an outer tube disposed about the inner tube and the central axis, and a middle tube disposed about the central axis and between the inner tube and the outer tube. The system may also include a first annular ring extending radially from the outer tube and configured to couple the outer tube to the middle tube. The system may further include a second annular ring extending radially from the inner tube and configured to couple the inner tube to the outer tube, such that an acoustic resonator may be formed by the first annular ring, the second annular ring, a portion of the inner tube, a portion of the outer tube, and a portion of the middle tube.
G10K 11/172 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général utilisant des effets de résonance
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-
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.
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.
A seal assembly for a dual-flow compressor is provided. The seal assembly may include an annular body disposed about a rotary shaft between a first compression assembly and a second compression assembly of the dual-flow compressor. An inner radial surface of the annular body and an outer radial surface of the rotary shaft may at least partially define a radial clearance therebetween. The annular body may have a first seal section and a second seal section at a first axial end portion and a second axial end portion thereof, respectively. The first and second seal sections may at least partially define a cavity therebetween. The seal assembly may also include a reference line communicably coupling the cavity with an inlet of the first compression assembly and configured to at least partially generate a pressure differential between the cavity and an outlet of the first compression assembly.
A method for producing liquefied natural gas (LNG) and separating natural gas liquids (NGLs) from the LNG is provided. The method may include compressing natural gas to compressed natural gas, removing a non-hydrocarbon from the compressed natural gas, and cooling the compressed natural gas to a cooled, compressed natural gas. The method may also include expanding a first portion and a second portion of the cooled, compressed natural gas 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 separating a third portion of the cooled, compressed natural gas into a methane lean natural gas fraction containing the NGLs and a methane rich natural gas fraction. The methane rich natural gas fraction may be cooled in a liquefaction assembly with the first and second refrigeration streams to thereby produce the LNG.
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.
F23R 3/46 - Chambres de combustion comprenant une disposition annulaire des tubes à flamme à l'intérieur d'une enveloppe annulaire commune ou d'enveloppes individuelles
F23R 3/06 - Disposition des ouvertures le long du tube à flamme
73.
Turbine with radial inlet and outlet and multi-element guide vanes for oscillating flows
b). 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.
A grid valve assembly for a steam turbine is provided. The grid valve assembly may include an annular stationary member disposed between an upstream stage and a downstream stage of the steam turbine. The annular stationary member may define a plurality of stationary member openings extending radially therethrough from an outer circumferential surface to an inner circumferential surface thereof. The grid valve assembly may also include an annular rotatable member rotatably disposed about the outer circumferential surface of the annular stationary member. The annular rotatable member may define a plurality of rotatable member openings extending radially therethrough.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
75.
SYSTEM AND METHOD FOR THE PRODUCTION OF LIQUEFIED NATURAL GAS
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 thereby produce the liquefied natural gas.
A solenoid valve for a pre-chamber of an internal combustion engine is provided. The solenoid valve may include a valve body defining an inlet port fluidly coupled with a fuel line, an outlet port fluidly coupled with the pre-chamber, and a passage fluidly coupling the inlet port with the outlet port. A valve stem may be slidably disposed in the passage between a first position and a second position. The valve stem may be configured to engage the outlet port in the first position to thereby prevent fluid communication therethrough. A biasing member may be disposed in the passage and configured to actuate the valve stem to the first position. A solenoid may be coupled with the valve body and configured to actuate the valve stem to the second position to thereby allow fluid communication therethrough.
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.
F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
A closure device for monitoring leakage of a process fluid through a bore of a compressor casing is provided. The closure device may include a body configured to be detachably coupled with the compressor casing about the bore of the compressor. The body may define a fluid passage and a plurality of grooves. The plurality of grooves may be defined about an outer circumferential surface of the body and may be axially spaced from one another. The closure device may also include a plurality of seals at least partially disposed in respective grooves of the plurality of grooves. The plurality of seals may be configured to engage an inner surface of the compressor casing such that adjacent seals of the plurality of seals at least partially define an annular gap therebetween fluidly coupled with the fluid passage and configured to contain the leakage of the process fluid.
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.
B04B 7/12 - Garnitures internes, p. ex. plaques de protection
B01D 46/00 - Filtres ou procédés spécialement modifiés pour la séparation de particules dispersées dans des gaz ou des vapeurs
B01D 17/038 - Séparation de liquides non miscibles par force centrifuge
F22B 37/32 - Dispositifs séparateurs de vapeur employant la force centrifuge
B01D 45/14 - Séparation de particules dispersées dans des gaz ou des vapeurs par gravité, inertie ou force centrifuge en utilisant la force centrifuge produite par des pales, disques, tambours ou brosses rotatives
B01D 53/24 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par force centrifuge
B04B 1/04 - Centrifugeurs à tambours rotatifs à parois pleines pour la séparation de mélanges essentiellement liquides contenant ou non des particules solides avec cloisons intérieures
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.
F01D 11/02 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages par obturation non contact, p. ex. du type labyrinthe
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.
A compressor and a method for reducing acoustic energy generated in the compressor are provided. The compressor may include a housing defining a fluid pathway and a shunt hole fluidly coupling the fluid pathway with another component of the compressor. The compressor may also include an impeller at least partially disposed in the fluid pathway and coupled with a rotary shaft. The impeller may be configured to rotate with the rotary shaft to direct a process fluid through the fluid pathway of the compressor. A disk may be disposed between the fluid pathway and the shunt hole. The disk may define a plurality of openings fluidly coupling the fluid pathway with the shunt hole and configured to reduce acoustic energy generated in the compressor.
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.
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.
F04B 35/04 - Pompes à piston spécialement adaptées aux fluides compressibles et caractérisées par les moyens d'entraînement de leurs organes de travail ou par leur combinaison avec les machines motrices ou moteurs qui les entraînent ou bien par leurs adaptations à cet effet, non prévues ailleurs les moyens étant électriques
F04B 39/06 - RefroidissementChauffagePrévention du gel
85.
INTERFACE FOR THE TRANSMISSION OF ELECTRICAL POWER TO A MOTOR-COMPRESSOR
An interface for transmitting electrical power to a motor of a motor-compressor is provided. The interface may include a receptacle having a first end portion coupled with a stator of the motor and a second end portion defining a hole at least partially extending therethrough. The interface may also include a plug configured to be detachably coupled with the receptacle. The plug may include a rigid, conductive rod having a first end portion configured to be coupled with a penetrator of the motor-compressor, and a second end portion configured to be at least partially disposed in the hole of the receptacle and detachably coupled therewith. The rigid, conductive rod may be configured to electrically couple the penetrator with the receptacle, and the receptacle may be configured to transmit the electrical power to the stator.
An interface for transmitting electrical power to a motor of a motor-compressor is provided. The interface may include a receptacle having a first end portion coupled with a stator of the motor and a second end portion defining a hole at least partially extending therethrough. The interface may also include a plug configured to be detachably coupled with the receptacle. The plug may include a rigid, conductive rod having a first end portion configured to be coupled with a penetrator of the motor-compressor, and a second end portion configured to be at least partially disposed in the hole of the receptacle and detachably coupled therewith. The rigid, conductive rod may be configured to electrically couple the penetrator with the receptacle, and the receptacle may be configured to transmit the electrical power to the stator.
F04B 45/06 - Pompes ou installations de pompage, ayant des organes de travail flexibles, spécialement adaptées pour fluides compressibles ayant des organes flexibles tubulaires
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.
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.
F02C 7/20 - Montage ou bâti de l'ensemble fonctionnelDisposition permettant la dilatation calorifique ou le déplacement
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02K 3/00 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant
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.
F16J 15/08 - Joints d'étanchéité entre surfaces immobiles entre elles avec garniture solide comprimée entre les surfaces à joindre exclusivement par garniture métallique
F01D 25/00 - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
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.
A fluid processing system and method are provided for separating a liquid portion from a multiphase fluid. The system and method may include a steam turbine assembly coupled with a rotary shaft, and a separator coupled with the rotary shaft and positioned upstream of the steam turbine assembly. The separator may include an inlet end configured to receive a multiphase fluid, an outlet end fluidly coupled with the steam turbine assembly, and a separation chamber extending from the inlet end to the outlet end. The separation chamber may be configured to separate a liquid portion from the multiphase fluid to thereby provide a substantially gaseous fluid to the steam turbine assembly.
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.
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.
F01D 11/04 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages par obturation non contact, p. ex. du type labyrinthe utilisant un fluide d'obturation, p. ex. de la vapeur
F16J 15/34 - Joints d'étanchéité entre deux surfaces mobiles l'une par rapport à l'autre par bague glissante pressée contre la face plus ou moins radiale d'une des deux parties
A compressor valve may include a guard and a seat affixed thereto. The seat may have an inlet surface and an outlet surface opposite the inlet surface. A reconditioning limit indicator may be defined by or adjacent the outlet surface. The reconditioning limit indicator may be indicative of a maximum amount of material of the seat removable from the outlet surface during reconditioning of the seat. The reconditioning limit indicator may be a groove defined by the outer cylindrical surface of the seat, a portion of the outer cylindrical surface of the seat adjacent the outlet surface and having an outer diameter smaller than the outer diameter of the seat, or a predetermined shape of a predetermined depth machined on the outlet surface of the seat.
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.
A method is provided for fabricating a carbon nanotube metal matrix composite. The method may include forming a molten mixture by combining carbon nanotubes with a molten solution. The carbon nanotubes combined with the molten solution may be dispersed therein. The method may also include transferring the molten mixture to a mold and applying a magnetic field to the molten mixture in the mold to substantially align at least a portion of the carbon nanotubes with one another. The method may further include solidifying the molten mixture in the mold to fabricate the carbon nanotube metal matrix composite, where at least a portion of the carbon nanotubes may be substantially aligned in the carbon nanotube metal matrix composite.
B22F 9/06 - Fabrication des poudres métalliques ou de leurs suspensionsAppareils ou dispositifs spécialement adaptés à cet effet par des procédés physiques à partir d'un matériau liquide
B22F 9/14 - Fabrication des poudres métalliques ou de leurs suspensionsAppareils ou dispositifs spécialement adaptés à cet effet par des procédés physiques en utilisant des décharges électriques
97.
PHYSICAL PROPERTY IMPROVEMENT OF IRON CASTINGS USING CARBON NANOMATERIALS
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.
B22D 19/16 - Coulée dans, sur, ou autour d'objets formant partie intégrante du produit final pour fabriquer des moulages composites à partir de métaux différents, p. ex. pour fabriquer des cylindres de laminoirs
B22D 1/00 - Traitement des métaux en fusion dans la poche ou dans les chenaux de coulée avant le moulage
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.
A system and method are provided for a compression system. The system and method may include a driver having a drive shaft extending therethrough. The driver may be configured to provide the drive shaft with rotational energy. The system and method may also include a first single-stage compressor and a second single-stage compressor, each having a rotary shaft coupled with or integral with the drive shaft. The first and second single-stage compressors may be configured to compress a high molecular weight process fluid to provide a compressed process fluid having a pressure ratio of about 10:1 or greater. The compressed process fluid may contain heat from the compression thereof. A heat recovery system may be fluidly coupled with the first and second single-stage compressors and may be configured to receive the compressed process fluid and absorb at least a portion of the heat contained in the compressed process fluid.
F04B 15/08 - Pompes adaptées pour travailler avec des fluides particuliers, p. ex. grâce à l'emploi de matériaux spécifiés pour la pompe elle-même ou certaines de ses parties avec des liquides près de leur point d'ébullition, p. ex. à une pression anormalement basse les liquides ayant une température d'ébullition peu élevée
A piston plug includes a cylindrical body having a longitudinal axis and an outer cylindrical surface. The outer cylindrical surface extends longitudinally between a first surface and a second surface opposite the first surface. The outer cylindrical surface defines a hole extending radially inward. The hole has a central axis perpendicular to the longitudinal axis of the cylindrical body. A first channel and a second channel are defined by cylindrical body. The first channel is in fluidic communication with the first surface and the hole. The second channel is in fluidic communication with the second surface and the hole. The first channel, the second channel, and at least a portion of the hole form a non-collinear flowpath. The piston plug is disposed in a plug hole in a piston and is retained in the plug hole via an interference fit between the piston plug and the plug hole.
F02F 3/24 - Pistons comportant des moyens pour guider les gaz dans les cylindres, p. ex. pour guider la charge de balayage dans les moteurs à deux temps
F16K 15/04 - Soupapes, clapets ou valves de retenue à corps de soupapes rigides guidés en forme de sphère
