Abstract: The present invention relates to a pump, which comprises a pump body, a pair of check rings and a pneumatic control valve. When the pneumatic control valve is operated, a main shaft in the pump body is enabled to reciprocally move in a shaft hole, thereby enabling two diaphragms to be stretched and compressed at the same time for performing the compressing and the sucking stroke for the liquid; when subject to the hydraulic pressure, an arc-shaped convex ring of each of the check rings is deformed, and a contract ring is contracted for enclosing the main shaft thereby forming a liquid checking effect; when each of the check rings is not subject to the hydraulic pressure or the air pressure, the arc-shaped convex ring is not deformed thereby forming a slit between the contract ring and the main shaft.

Abstract: A pump fitting has an inlet adaptor (10) for connection to an outlet (39) of a container (38) of fluid and including an inlet passage (10), an outlet passage (11) for fluid and a pump housing (12) between the inlet passage (10) and the outlet passage (11). The pump housing (12) contains a rotor (17) rotatably received in an interior surface of the housing (12). The rotor (17) includes a housing-engaging surface (23, 24) co-operating with the interior surface of the housing (12) to form a seal therebetween and also including at least one shaped surface (21, 22) radially inwardly of the housing-engaging surface and forming with the interior surface of the housing a chamber (25, 26) for conveying fluid from the inlet passage (10) to the outlet passage (11) on rotation of the rotor (17).

Abstract: A vehicular fluid power transmitting device has a pump impeller, a turbine runner, damper device, an annular set member and a bearing assembly. The pump impeller has a pump shell. The damper device is provided between a drive source and the pump shell in an axial direction of an output shaft, and has a damper input member that is connected to the drive source, and a damper output member that is connected to the pump shell. The damper output member is connected to the annular set member that is fixed to the pump shell. The damper input member is relatively rotatably supported via the bearing assembly by the annular set member.

Abstract: The proposed rotary pump for transporting liquids containing solids is composed of a pump housing (1) and an impeller (2) disposed on a rotating driven shaft. The pump housing (1) encloses a flow space having an intake region (4) and having a pressure region (5) surrounding the periphery of the impeller (2), as well as also a back space (6) of the impeller. According to the invention, the gap (3) relative to the back space (6) of the impeller is completely sealed opposite the flow space relative to the transported liquid with the solids contained therein, wherein, however, there is provided a connection of the back space (6) of the impeller to the pressure region (5), by which its aeration and venting are made possible.

Abstract: The energy-storing and power-generating system comprises an energy-storing system and a power-generating system. The energy-storing system comprises a high pressure gas generator, a water storage apparatus and a water turbine. The high pressure gas generator comprises at least one sealed high pressure gas tank (2) and an air compressor (1) cooperating therewith. The water storage apparatus comprises at least one sealed water tank (3). The air compressor is in communicated with the high pressure gas tank via a gas inlet pipe (4), while the high pressure gas tank is in communication with the water tank via a gas outlet pipe (5). The water tank is connected to a water inlet of the water turbine (10) via a water outlet pipe. Blades (102) of the water turbine are connected to the power generator via main gears.

Abstract: A seal arrangement for a gas turbine engine comprises a seal support having a hub portion and a peripheral rim portion. A seal member is mounted to a radially inner surface of the hub portion. A first set of circumferentially spaced-apart channel segments project from the peripheral rim portion of the seal support. A second set of circumferentially spaced-apart channel segments projects from a mating stationary structure of the gas turbine engine. The first and second sets of circumferentially spaced-apart channel segments circumferentially may be aligned to complementary form a circumferentially extending channel. A retaining ring may be mounted in the circumferentially extending channel for retaining the seal support on the mating stationary structure of the engine. The seal support may be provided with a diaphragm to provide flexibly between the seal member and the point of attachment of the seal support to the mating structure of the engine.

Abstract: A turbomachine includes a compressor having a cartridge that is configured to slide in and out of an external casing. The turbomachine further includes an electrical motor having a motor shaft configured to be connected to the compressor shaft. A conduit is configured to extend through the statoric part of the compressor or the motor, from a first magnetic bearing to the second magnetic bearing. The conduit includes conduit electrical cables provided inside the conduit and extending from a first end of the conduit to a second end of the conduit; and electrical cables connecting one of the first and second magnetic bearings to an external connector via the conduit electrical cables of the conduit.

Abstract: An air cycle machine includes a bearing housing with a shaft bore. A rotor shaft is arranged in the shaft bore and includes knife edges extending from the rotor shaft. A seal engages the shaft bore and includes an outer diameter and an inner diameter providing a seal land axially aligned with the knife edges. A radial clearance between the seal land and the knife edges is nominally 0.006 inch. The inner diameter is arranged between lateral sides of the seal that define a width. In one example, a tapered surface extending at an angle relative to the outer diameter from the lateral side to the seal land, the tapered surface facing the large end. The outer diameter to the inner diameter provides a first ratio of 1.25-1.28, and the inner diameter to the width provides a second ratio of 4.33-5.58.

Abstract: A turbine section having a plurality flow path components forming a plurality of guide vane rings and ring segments arranged in axial succession to define a boundary of a hot gas duct. A vane carrier located around the gas duct, and sealing elements extend radially between circumferentially extending grooves in the vane carrier and respective grooves in the flow path components. The sealing elements include radially inner and outer edges, and at least one axially facing side defining a chamfered portion extending to one of the edges to accommodate axial movement of the sealing element about the one edge within a respective groove.

Abstract: A device for detecting the axial position of a rotary shaft of a rotary machine comprises a target of ferromagnetic material placed at the end of the rotary shaft, an induction coil associated with a stationary magnetic circuit and placed facing the target while leaving an airgap, and a power supply circuit. The power supply circuit comprises an AC voltage source connected between a first end of the induction coil and a zone situated at a reference voltage, at least one capacitor connected between the ends of the induction coil, and a detector device interposed between a second end of the induction coil and the zone situated at the reference voltage, in order to deliver on a line information about the magnitude of the current flowing between the second end and the zone situated at the reference voltage.

Abstract: A bearing foil assembly includes a top foil, an intermediate foil, and a bump foil. The bump foil is provided with corrugations at circumferentially spaced locations. The bump foil has an end that is bent radially outwardly from a center of the foil assembly. The top foil has a bent portion extending radially outwardly and adjacent to the bent end of the bump foil. A first radius of curvature is defined to a curved portion leading into the bent portion at a first end adjacent to the bent end. A second radius of curvature is defined at an end of the bent portion on an end opposed to the bent end. A ratio of the first radius of curvature to the second radius of curvature is between 0.6 and 10. A bearing assembly, a shaft sub-assembly, an air machine, and a method of assembling a bearing into an air machine are also disclosed.

Abstract: A turbine housing comprises an exhaust port flange, a turbine discharge flange, a crossover flange, and a bearing support ring. The exhaust port flange is configured for mechanically coupling the turbine housing to a mating structure providing a source of working fluid. The turbine discharge flange is configured for mechanically coupling the turbine housing to an exhaust system. The crossover flange is configured for mechanically coupling the turbine housing to a crossover duct. The bearing support ring is configured for mechanically supporting a bearing, on which a turbine output shaft is supported. The turbine housing defines an inlet plenum, a turbine shroud, and a discharge vent. The exhaust port flange defines an inlet port configured to provide fluid communication between the inlet plenum and the source of working fluid. The turbine shroud defines a fluid expansion flow path for expansion of the stream of working fluid.

Abstract: A seal assembly for rotary machine is provided. The seal assembly includes multiple compliant plates disposed between a stationary component and a rotary component of the rotary machine, and coupled circumferentially along the stationary component. Each compliant plate comprises a tip configured to be disposed facing the rotary component, and at least one plate slot extending from the stationary component towards the rotary component. The seal assembly also includes at least one annular resistance member configured to be coupled to the stationary component and disposed in the at least one plate slot in the compliant plates and one or more rotor slots or grooves located circumferentially on a surface of the rotary component proximate the tip of each of the plurality of compliant plates.

Abstract: A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance.

Abstract: A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface. The grooves are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

Abstract: A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane The grooves are arranged such that a circumferential space is defined between adjacent grooves During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

Abstract: A positive displacement pump is disclosed which includes a case that defines a pump cavity. A shaft and rotor, which are detachably connected together, are also included wherein the rotor is disposed within the pump cavity and the shaft passes through an opening in the proximal end of the case. The distal end of the shaft, in addition to being connected to the rotor, is also coupled to a fastener that couples a cover plate over the distal end of the shaft and over at least part of the base portion of the rotor. The opening in the proximal side of the case through which the shaft passes also accommodates a seal assembly. Access to the seal assembly is easily made by removing the head from the case and removing the rotor from the shaft. The seal assembly can be changed or serviced without removal of the shaft.

Abstract: A bearing housing (1) of an exhaust-gas turbocharger (2) having an oil inlet (3) which is connected to a connecting region (4) of an oil supply line (5), The connecting region (4) of the oil supply line (5) is in the form of a siphon (6).

Abstract: A turbine engine including a casing, a turbine engine shaft extending axially, a guide bearing for guiding the turbine engine shaft in the casing, the guide bearing including an inner circumferential ring rigidly connected to the turbine engine shaft, an outer circumferential ring fitted in a housing of the casing, and gripping rolling members, and a damping cavity configured to receive a damping fluid to form a damping fluid film for damping the guide bearing, the cavity being delimited radially between an outer surface of the outer ring and an inner surface of the housing. The outer surface of the outer ring and the inner surface of the housing are conical surfaces.

Abstract: A cover plate for a rotor disk in a gas turbine machine includes a cylindrical body having multiple outward facing snaps and multiple inward facing snaps.

Abstract: The disclosure includes a sealing assembly for a turbine system. In one embodiment, the sealing assembly is for a turbine having a rotor blade and a stator nozzle. The sealing assembly includes a pair of oppositely facing seal teeth including concave surfaces. The pair of oppositely facing seal teeth are positioned on one of the rotor blade and the stator nozzle, and are for sealingly engaging the other of the rotor blade and the stator nozzle during operation of the turbine.

Abstract: A sealing system for a wind turbine comprises first component and a second component positioned proximate the first component and movable relative thereto. An absorbent element is secured to the first component and comprises an oil-absorbent material. A contact member is secured to the absorbent element and comprises a non-absorbent material. The contact member abuts the second component so that lubricant leaking from between the first and second components is collected by the absorbent element. A method of maintain a clean environment in a wind turbine with such a sealing system is also disclosed.

Abstract: An assembly for a gas turbine engine includes a component, a seal element, and a seal cap. The component defines a pocket adapted to accept the seal element and the pocket allows for sliding movement of the component relative to the seal element. The seal cap overlying the pocket and the seal element.

Abstract: In a gas exhaust pump, there is provided a rotation mechanism that can ensure safe rotation and can greatly reduce the usage of a seal gas. A rotation mechanism of the present invention is formed of a rotating shaft and a seal housing. Between the rotating shaft and the seal housing, there is provided a predetermined gap. On at least one of an outer surface of the rotating shaft and an inner surface of the seal housing, there is provided a PFA film. As to a PFA film on a surface of at least one of the rotating shaft and the seal housing, after coating with PFA the wall surface of the rotation mechanism member defining at least the gap, followed by melting and remelting processes, the PFA film is formed to have a high smoothness on its free surface.

Abstract: A seal plate for an air cycle machine includes a substantially disk-shaped body having a first side configured to be coupled to a compressor housing of the air cycle machine and a second side configured to be coupled to a turbine housing of the air cycle machine. The seal plate also includes a timing pin slot configured to align the first side of the seal plate with the compressor housing. The seal plate further includes a plurality of fastener holes distributed radially in an asymmetric pattern. The plurality of fastener holes includes an alignment fastener hole configured to align the second side of the seal plate with the turbine housing. An angular offset between the alignment fastener hole and the timing pin slot is about 38.45 degrees.

Abstract: A centrifugal pump assembly with at least one impeller (8) and with a thrust bearing (44) which includes a rotating (50) and a stationary (48) bearing part. The rotating (50) as well as the stationary (48) bearing part are designed in a self-aligning manner.

Abstract: An arrangement having an annular seal extending about a machine axis, and a vessel for sealing an L-shaped gap extending along a circumferential direction between a main vessel body and a cover is provided. A radial section of the gap extends in the radial direction and circumferential direction, and an axial segment extends in the axial direction and the circumferential direction. A sealing chamber is provided in the region where the radial segment and the axial segment intersect, the chamber expanded radially and axially relative to the adjacent gap segments. A seal is disposed in the sealing chamber, and a greater pressure is present in the radial segment than in the axial segment, the pressure differential sealed by means of the seal. The seal includes a support ring disposed radially inward made of a first material, and a jacket element made of a second material.

Abstract: A direct driven wind turbine and a main bearing used in such a wind turbine is provided. A rotor of the wind turbine is directly connected with a rotating drive train of the wind turbine, the rotating drive train is directly connected with a rotor of an electrical generator of the wind turbine. The rotating drive train is connected with a stationary part of the wind turbine via at least one bearing, which allows the rotation of the drive train in relation to the stationary part. The at least one bearing is a plain bearing and the bearing is a tapered bearing, which comprises at least one conical shaped sliding surface.

Abstract: A compressor motor housing includes an aft region having a radially inner surface defining an inner diameter and a radially outer surface defining an outer diameter. Also included is an O-ring groove extending around at least a portion of the aft region within the radially outer surface, the O-ring groove. The O-ring groove includes a groove width, a groove depth and a groove diameter, wherein a width ratio defined by the groove width in relation to the groove diameter ranges from about 0.0257 to about 0.0272. The O-ring groove also includes an axially forward face, an axially aft face and a circumferential face disposed radially outwardly from the radially inner surface. The compressor motor housing further includes an O-ring seal simultaneously disposed in contact with the axially forward face, the axially aft face and the circumferential face.

Abstract: A rotating assembly of turbomachinery is provided. The rotating assembly includes a plurality of components mounted on a rotatable shaft within a housing of the turbomachinery and at least one foil journal bearing assembly for mounting the rotatable shaft to the housing. The foil journal bearing assembly includes an annular bearing carrier mounted to the housing. An annular bearing sleeve is disposed within the annular bearing carrier and attached thereto. The annular bearing sleeve is lined with a plurality of foils. A journal is mounted to the rotatable shaft. The journal has an outer surface engaging the foils. The journal is configured to at least one of the following: resist operational deflection thereof and reduce the effects of misalignment. A method for producing the journal of the foil journal bearing assembly is also provided.

Abstract: A turbomachine seal assembly includes a rotor disposed about an axial centerline, the rotor having an outer surface. Also included is a stationary component extending circumferentially about the rotor. Further included is at least one primary annular seal ring operably coupled to the stationary component and extending radially inwardly to close proximity with the outer surface of the rotor. Yet further included is a secondary annular seal ring operably coupled to the stationary component and integrally formed with the at least one primary annular seal ring, the secondary annular seal ring extending radially inwardly to close proximity with the outer surface of the rotor.

Abstract: An embodiment of the present invention is a turbine nozzle baffle including an annular box structure. The turbine nozzle baffle includes a first diaphragm, a second diaphragm, and a static portion of a rotating seal that form a one-piece annular box structure. The first diaphragm extends from an inner diameter of the box structure to an outer diameter of the box structure to form a first axial side. The second diaphragm includes a first portion and a second portion. The first portion extends from the inner diameter to the outer diameter to form a second axial side. The second portion extends toward the first axial side to form the outer diameter. The second diaphragm connects to the first diaphragm at the outer diameter. The static portion of the rotating seal faces radially inward at the inner diameter between the first axial side and the second axial side.

Abstract: A method of deploying offshore wind turbine assemblies includes mounting a wind turbine assembly horizontally on a vessel and transporting the wind turbine assembly to an offshore site. The wind turbine assembly is raised to a vertical condition at the site and attached to anchor weights. Blades are attached to the turbine head after the wind turbine assembly is in the vertical condition. In one embodiment, the wind turbine assembly can include a tower including tapered lower and upper sections joined together at their respective wide ends, a turbine head connected to the upper section, and a platform connected to the lower section. The platform includes a buoy tank partially filled with ballast to provide mass and buoyancy. A wave piercing cowling is rotatively attached to the lower section. The turbine head can include an adjustable journal bearing, scabbard blade mounts, and a gearless induction generator with flux adjusting capabilities.

Abstract: A compressor housing is provided with a shroud member, which surrounds a compressor impeller, and a sealing member. The shroud member has a facing surface that is located at a position on a radially outside of the compressor impeller on an inner circumferential surface of the shroud member. The sealing member is provided on the facing surface. The sealing member is formed from a cylindrical material that has free-cutting property to the compressor impeller. The sealing member is press-fitted into the facing surface of the shroud member.

Abstract: A turbomachine component includes a first housing portion having a first end that extends to a second end. At least one of the first and second ends includes a first sealing surface having a seal receiving passage. A second housing portion includes a first end that extends to a second end. At least one of the first and second ends includes a second sealing surface configured and disposed to register with the first sealing surface. A seal member is provided in the seal receiving passage. The seal member includes a plurality of bristles that extend toward the second sealing surface.

Abstract: Enhanced abrasion resistance in well fluid wetted assemblies is described. The bearing set of the invention provides an enhanced abrasion resistance that is better capable of withstanding friction from solids in electric submersible pump (ESP) well production applications. The flutes, grooves, sectors and intersections of the invention provide improved fluid and solid flow through assembly components, which improves cooling while the assembly is in operation and reduces body wear, thereby increasing the lifespan of the ESP system.

Abstract: A hybrid radial gas turbine engine component comprises an inner hub portion joined to an outer ring portion. The inner hub portion is a first alloy and operates at temperatures less than 1200° F. The outer ring portion is a second alloy and is designed to withstand extended periods at temperatures greater than 1200° F.

Abstract: A gas turbine engine with a geared architecture includes a multiple of bearing compartments and at least one carbon seal that seals at least one side of each of the multiple of bearing compartments.

Abstract: A bearing support apparatus for a gas turbine engine, including: a first annular member; a second annular member disposed within the first annular member; first and second axially spaced-apart rolling-element bearings disposed between the first and second annular members so as to enable relative rotation of the first and second members; a first spring element mounting the first bearing to the first member; and a second spring element mounting the second bearing to the first member through the first spring element, such that the first and second bearings are physically supported in series relative to the first member.

Abstract: A method of measuring a flow rate of a first fluid through a rotary seal of a gas turbine engine comprising controlling a probe flow of a second fluid at an intra-seal cavity and measuring a pressure change in the first fluid caused by the probe flow.

Abstract: A turbine engine including at least one shaft and at least one bearing for rotatably guiding the shaft about an axis of the turbine engine, the bearing including a first radially inner ring and a second radially outer ring enclosing rolling members, wherein the first ring is floatingly mounted on the shaft via a fluid damping film.

Abstract: A method for manufacturing a metallic component especially configured and designed for a turbomachine includes a) for a precision-casting process, a wax model with a wax structure is produced, subsequently b) the tip of the wax structure is thermally and/or mechanically treated such that a region with an undercut is formed on the wax structure, subsequently c) the metallic component is manufactured from the wax model in the precision-casting process, with a component structural element with an undercut forming on a surface of the component, and d) the component structural element is provided at least partially with a ceramic coating, a plastic-containing coating, in particular a fibre composite layer and/or a plastic component.

Abstract: It is intended, with respect to a first floating bush bearing disposed on a compressor housing side and a second floating bush bearing disposed on a turbine housing side, to improve oscillation stability when a turbine rotor revolves at a high speed, reduce the number of parts, and facilitate processing and assemblability. Provided are a bearing housing (13) for a turbocharger (1), a rotor shaft (16) passing through the bearing housing (13), a first floating bush bearing (17) interposed between the bearing housing (13) and the rotor shaft (16) and disposed on a compressor housing (12) side and comprising a first floating bush, and a second floating bush bearing (18) that has the same shape as the first floating bush bearing (17) and is disposed on a turbine housing (11) side and comprises a second floating bush (20). The inner bearing width (Li) of the first and second floating bushes is formed to be smaller than the outer bearing width (Lo) by the same proportion in both bushes.

Abstract: A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material.

Abstract: An improved personal propulsion device that imparts thrust directly to the user when operating a human powered vehicle to improve mobility thereof. The device allows hands free control of thrust magnitude and direction so both hands can grasp and control bicycle handlebars and brakes, watercraft paddles, ski poles or other apparatuses. In another embodiment, the device can be attached directly to the vehicle. The device can be provided with a collapsible shrouded propeller assembly comprising a shroud made up of interlocking panels that are each removably attached to the end of an elongated strut, with each the struts being pivotally and/or telescopically disposed relative to the propulsion mechanism. The panels can be slidably engaged with the struts. A gradiently flexible garment can be worn by a user and utilized with a gradiently flexible fairing attached to the user and a bicycle to improve aerodynamics when riding the bicycle.

Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a flexible metallic seal contacting the interface member to provide a seal between the interface member and the turbine section.

Abstract: A liner is provided for an air flow passage of a gas turbine engine. The liner comprises an acoustic attenuation layer which forms an air-washed surface of the flow passage, and a heat exchanger layer which extends as a backing to the acoustic attenuation layer. The heat exchanger layer is configured to carry a heated fluid flow and to transport heat from the fluid flow to the acoustic attenuation layer from where the heat is transferred to air flowing through the air flow passage.

Abstract: A method of fabricating a machine component is provided. The method includes preparing at least a portion of a surface of a machine component for receiving a sintered preform. The method also includes forming a pre-sintered preform hybrid hardface mixture that includes combining a predetermined portion of at least one hardfacing material with a predetermined portion of at least one brazing material. The method further includes forming a pre-sintered preform. The pre-sintered preform has predetermined dimensions. The method also includes forming the sintered preform and positioning the sintered preform on the machine component. The method further includes fixedly coupling the sintered preform to at least a portion of the machine component via brazing.

Abstract: A composite component such as a fan rear seal comprises a hub and a body of composite material which is molded over the outer periphery of the hub. The body is formed from a preform of fiber reinforcement impregnated with a resin, in a compression molding process. The body has an annular projection provided with a sealing surface. The sealing surface may comprise circumferential fins, or may be a surface of, for example, an abradable seal insert molded into the composite material of the body.

Abstract: A wind turbine is provided comprising a rotatable main shaft having a centre axis and being at least indirectly connected to a wind turbine rotor of the turbine and a main bearing supporting the rotatable main shaft at least indirectly against a first stationary part of the turbine, wherein fastening unit are provided for fastening the rotor to the first or a second stationary part of the turbine during replacement of the main bearing and tappet unit are provided which are able to act on the main bearing and permit a movement of the main bearing relatively to the first stationary part in the direction of the centre axis. A method for replacement of a main bearing is also provided.