Abstract: A rotary pump includes a balance drum connected to a pump shaft between a hydraulic unit and the pump shaft, an axial relief passage between a balance drum and a stationary part stationary relative to a pump housing, and a balancing device arranged between the balance drum and the hydraulic unit, the balancing device including a ring-shaped rotary part connected to the pump shaft, and a ring-shaped non-rotary part movable only in the axial direction, the rotary part having an axial face facing the hydraulic unit, the rotary part and the non-rotary part overlap in a radial direction, which is perpendicular to the axial direction, and the non-rotary part movable in the axial direction such that a radial relief passage is open during operation of the pump, with the radial relief passage extending in the radial direction between the rotary part and the non-rotary part.

Abstract: A motor-driven compressor equipped with multiple compression sections, the motor-driven compressor including, at least one housing, at least two drive shafts, the at least two drive shafts being rotatably supported in the housing by at least two bearings, a flexible coupling device connecting the drive shafts, an electric motor mounted on a first compression shaft of the at least two drive shafts, and at least two compression sections. A first compression section of the at least two compression sections is cantilevered at a free end of a first compression shaft of the at least two drive shafts, and a second compression section is mounted between two bearings on a second compression shaft of the at least two drive shafts.

Abstract: A gas turbine engine includes a fan, a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the fan and compressor.

Abstract: A steam turbine facility includes a rotor shaft, a high-pressure turbine blade row and an intermediate-pressure turbine blade row disposed on the rotor shaft, a first low-pressure turbine blade row and a second low-pressure turbine blade row disposed on the rotor shaft on both sides of the intermediate-pressure turbine blade row, respectively, and a third low-pressure turbine blade row and a fourth low-pressure turbine blade row disposed on the rotor shaft on both sides of the high-pressure turbine blade row, respectively. The steam turbine facility is configured such that steam having passed through the intermediate-pressure turbine blade row is divided to flow into the first low-pressure turbine blade row, the second low-pressure turbine blade row, the third low-pressure turbine blade row, and the fourth low-pressure turbine blade row.

Abstract: A mixed-flow impeller for an electric submersible pump can include a lower end and an upper end; a hub that includes a through bore that defines an axis; blades that extend at least in part radially outward from the hub where each of the blades includes a leading edge and a trailing edge; an upper balance ring that includes a radially inward facing balance chamber surface and a radially outward facing diffuser clearance surface; and an upper guard ring disposed radially outwardly from the upper balance ring where the upper guard ring includes an axially facing diffuser clearance surface that is disposed axially between the trailing edges of the blades and the upper end.

Abstract: A flywheel apparatus that magnetically unloads a top rotor bearing is described. The apparatus includes a flywheel housing, a rotor with a vertical axis of rotation that includes a magnetic material, a magnet configured to apply a desired upward off-loading force along the vertical axis of rotation, an upper bearing connected to an upper shaft of the rotor, and a bearing housing disposed between the upper bearing and the flywheel housing that substantially prevents downward axial motion of the upper bearing. The magnet includes an electromagnet. A force sensor is used to measure a force on the upper bearing which is provided as input to a controller that updates the current to the electromagnet. The rotor is maintained in a fixed axial position and a spring disposed below a lower bearing absorbs axial dimension growth of the rotor.

Abstract: Centrifugal electric pump, comprising a pump body, with an aspiration inlet and a delivery outlet, a hydraulic volute, within which an impeller is accommodated, and comprising an electric motor for moving the impeller. The hydraulic volute is constituted by two half-shells made of plastic material and mutually joined with joining means and with sealing means.

Abstract: A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool is also disclosed.

Abstract: The turbomachine comprises a stationary casing with a rotating member configured to rotate about a rotation axis in the stationary casing. The turbomachine further includes a rotating balance drum, arranged for co-rotation with the rotating member. A stationary sleeve is arranged in a fixed relationship with the stationary casing and surrounds the balance drum. The stationary sleeve comprises a plurality of consecutively arranged sleeve sections. A fluid channel is defined by an outer surface of the balance drum and an inner surface of the stationary sleeve. Between at least one pair of sequentially arranged upstream sleeve section and downstream sleeve section an annular chamber is provided, fluidly coupled to the fluid channel. Shunt holes are arranged on the upstream sleeve section, each shunt hole having a shunt hole inlet on an inner surface of the upstream sleeve section, and a shunt hole outlet in the annular chamber.

Abstract: A gas turbine engine for an aircraft such as a UAV includes a compressor connected to a turbine with a combustor to produce a hot gas stream. The rotor is supported by two radial foil bearings. An axial thrust bearing assembly is positioned between the compressor disk and the turbine disk and includes an axial thrust bearing radial disk extending from a hollow axial tube. Compressed air is bled off from the compressor and passed into an axial thrust balance chamber to provide the axial thrust balance for the rotor. The compressed air from the thrust bearing chamber then flows through both of the radial foil bearings for cooling, is collected in and around the hollow tube, and then discharged into the inlet of the turbine. An orifice can be adjusted to meter and control a pressure occurring in the thrust balance chamber.

Abstract: A reverse osmosis system and a method of operating the same includes a membrane housing comprising a reverse osmosis membrane therein. The membrane housing has a feed fluid inlet, a brine outlet and a permeate outlet. A first turbocharger has a first pump portion and a first turbine portion. The brine outlet is coupled to a first pipe directing a first portion of brine to the first pump portion. The first pump portion is in fluid communication with the feed fluid inlet. A feed pump communicates feed fluid to the feed fluid inlet. The brine outlet is coupled to a second pipe directing a second portion of brine away from the first pump portion.

Abstract: A multi-stage horizontal centrifugal pump for conveying a fluid has a rotor including a rotatably arranged shaft and a plurality of impellers for conveying the fluid and a stator. All the impellers are arranged in a rotatably fixed manner on the shaft. The stator includes a plurality of stage casings, which are arranged consecutively one after another with respect to an axial direction determined by a central axis. The stator encompasses the rotor, and each stage casing is designed and arranged centrically with respect to the central axis. A plurality of wear rings is disposed between the rotor and the stator, each of which is fixed with respect to the stator, and surrounds the rotor with a clearance. At least one of the wear rings is designed eccentrically.

Abstract: A disk assembly includes a first disk, a second disk and a third disk. The first disk is engaged with a compressor section of a gas turbine. The second disk is engaged with a turbine section of the gas turbine. The third disk is disposed between the first and second disks and transfers a rotational torque applied to the second disk to the first disk. A through-hole is defined through the third disk along an axial direction of the gas turbine. A distance between the third disk and a tie rod is less than each of distances between the first and second disks and the tie rod, such that spaces are defined by surfaces of the third disk respectively in communication with the compressor section and the turbine section.

Abstract: An example method of balancing a shaft includes inserting a balancing insert into one of a plurality of cavities. The plurality of cavities are radially inside an outermost surface of the shaft.

Abstract: A centrifugal compressor includes a rotor including: a shaft that extends along an axis and an impeller that is fixed to an outer surface of the shaft and feeds a fluid that flows into a first side in an axial direction to an outer side in a radial direction of the axis under pressure; a diaphragm that surrounds the impeller from an outer circumference side; a first casing head disposed at a second side of the diaphragm in the axial direction at an interval; a seal device disposed between the first casing head and the shaft; and a bearing device disposed at the second side in the axial direction with respect to the seal device and disposed between the first casing head and the shaft.

Abstract: A propulsion device that defines a central axis and a circumferential direction is provided. The propulsion device may include a core engine and a core casing. The core engine may include an engine shaft extending along the central axis. The core casing may have an inner surface and an outer surface. The core casing may extend along the circumferential direction about the propulsion device, as well as along the central axis from a forward end to an aft end. The core casing may define a primary air flowpath having an annular inlet at the forward end and an exhaust at the aft end. The core casing may further define a reverse flow passage extending from an outer surface entrance to an inner surface exit.

Abstract: A bearing structure includes a through-hole penetrating through in the axial direction of shaft, a bearing holder accommodated in the through-hole, a semi-floating metal bearing accommodated in the bearing holder and supporting the shaft inserted into the inside, and a positioning member being inserted into a radial direction of the shaft for both the bearing holder and the semi-floating metal bearing and regulating movement of the semi-floating metal bearing in the axial direction and in a rotating direction of the shaft relative to the bearing holder. For the bearing holder, a press-fit portion to be press-fitted into the through-hole is formed. A gap is formed between at least one of outer circumferential surfaces of both end parts of the bearing holder in the axial direction and the inner circumferential surface of the through-hole.

Abstract: A steam turbine having a cooling option, in which steam is taken from the flow channel, the steam cooling the thrust-compensating intermediate floor, being mixed with a small amount of live steam and being returned to the flow channel. A method cools the steam turbine, wherein steam is extracted from the high-pressure region and is fed to a space between the thrust-compensating partition wall and inner casing, wherein steam from the space between the thrust-compensating partition wall and the inner casing is fed via a first cross feedback passage to the high-pressure region.

Abstract: Various aspects of the disclosed technology relate to axial thrust analysis of turbomachinery designs. A cavity of a turbomachinery design is divided into sub-cavities. Magnitudes of horizontal components of forces exerted on rotational faces in each of the sub-cavities are computed based on computational fluid dynamics, areas of the rotational faces and angles of the rotational faces. The horizontal components are components along a rotational axis of the turbomachinery design. Directions of the horizontal components of the forces are determined based on how many faces a line parallel to the rotational axis intersects between a rotational face of interest and a side of the cavity. A thrust force on a turbine of the turbomachinery design attributed to secondary fluid systems is computed using the magnitudes and the directions of the horizontal components of the forces.

Abstract: A blood pump includes a hub having an axis of rotation and a generally cylindrical shape. The hub has an upstream end region, a central region, and a downstream end region, and the hub includes a magnetic material. Blades that are disposed on the downstream end region of the hub extend downstream of the hub.

Abstract: A gas turbine engine, system, and method with clearance control are provided. For example, the gas turbine engine includes a static component, and a rotating component that shifts axially in one of an aft direction and a forward direction in relation to the static component during a first operating condition of the gas turbine engine, and shifts axially in the other of the aft direction and the forward direction in relation to the static component during a second operating condition of the gas turbine engine. The first operating condition is when a rotating component growth and a static component growth change at different rates. The second operating condition is when the rotating component growth and static component growth normalize.

Abstract: A pre-diffuser and exit guide vane (EGV) system for a gas turbine engine includes an annular EGV assembly containing a number of guide vanes and having an annular opening bounded by a radially inner annular sealing surface at a first radius and a radially outer annular sealing surface at a second radius. First and second seals substantially matching the first and second radii respectively join the EGV assembly to an annular pre-diffuser having an annular opening bounded by radially inner and outer annular sealing surfaces at substantially the first and second radii. The seals seal the inner sealing surface of the EGV assembly to the inner sealing surface of the pre-diffuser and the second seal seals the outer sealing surface of the EGV assembly to the outer sealing surface of the pre-diffuser, such that the EGV assembly annular opening is in fluid communication with the annular opening of the pre-diffuser.

Abstract: A torque transfer system for centrifugal pumps. A torque transfer system for a centrifugal pump includes a bearing sleeve above an impeller, the bearing sleeve and a hub of the impeller surrounding a rotatable shaft and coupled to the rotatable shaft by a key, the bearing sleeve having a stepped bottom edge, a top edge of the hub stepped inversely to the bottom edge of the bearing sleeve such that the top edge and the bottom edge interlock with a clearance between longitudinally extending portions of the interlocked edges, wherein upon reduction of torque transference between the key and the sleeve, the clearance closes such that the longitudinally extending portion of the stepped top edge contacts the longitudinally extending portion of the stepped bottom edge thereby maintaining rotation of the sleeve with the rotatable shaft. A centrifugal pump includes modules with a series of stepped, interlocked impellers.

Abstract: An apparatus and system for a thrust-absorbing horizontal surface pump assembly. A thrust-absorbing horizontal surface pump system includes an intake chamber including a stationary thrust bearing paired with a rotatable thrust runner to form a thrust bearing set, wherein a first face of the stationary thrust bearing positioned towards the rotatable thrust runner is at least partially diamond-coated, and wherein a second face of the rotatable thrust runner positioned towards the stationary thrust bearing is at least partially diamond-coated, a fluid entrance that receives fluid into the intake chamber, and a pump inlet that receives the fluid into the multi-stage centrifugal pump, wherein the thrust bearing set is arranged around the intake shaft such that during operation of the electric motor the thrust bearing is in a pathway of the fluid as the fluid flows between the fluid entrance and the pump inlet.

Abstract: A multi-stage compressor is described, comprising a rotor having a plurality of axially stacked impellers and a tie rod extending through the stacked impellers and holding the impellers together. A gas compression path extends from a compressor inlet to a compressor outlet and through the impellers. A flow channel is provided between the tie rod and the stacked impellers. The flow channel develops along at least a portion of the tie rod. Hot gas is diverted from the compression path and flows through the flow channel to heat the tie rod during startup of the compressor.

Abstract: A bearing assembly includes a shaft and a thrust runner attached to the shaft. The shaft runner protrudes radially outward from the shaft. A thrust bearing is positioned axially adjacent to the thrust runner. A first flow passage is between the thrust runner and a first face of the thrust bearing. A second flow passage is between a second face of the thrust bearing and a housing. A restriction feature restricts a flow of fluid through the second flow passage.

Abstract: A centrifugal pump impellor includes balancing holes that reduce axial thrust while minimizing the loss of pump efficiency. In one general aspect, the balancing holes penetrate the rear shroud between the blades, and are angled in both axial and rotational directions so as to direct the leakage fluid approximately parallel to the primary process fluid, so that it causes minimal interference with the primary fluid flow. In a second general aspect, the balancing holes extend from the rear cavity within the impellor blades and through the leading edges of the blades, thereby entering the primary flow in locations where the process fluid is almost static relative to the blades. This minimizes the impact on the flow of the process fluid past the blades, and thereby minimizes the loss of pump efficiency caused by the balance holes. In embodiments, each blade leading edge includes a plurality of balancing hole outlets.

Abstract: Components resistant to traveling wave vibration and methods for manufacturing the same are provided. The component comprises a component body and a plurality of features disposed thereabout according to an asymmetry pattern that separates a pair of repeated eigenvalues associated with a targeted mode that deflects in excess of a threshold deflection limit in response to traveling wave excitation. The method comprises identifying, in a model of a rotationally periodic component, one or more modes thereof that deflect in excess of a threshold deflection limit in response to a traveling wave excitation. Each of the modes has a pair of repeated eigenvalues associated therewith. An asymmetry pattern is determined that separates each pair of repeated eigenvalues by a desired frequency split. A plurality of features are formed and disposed according to the asymmetry pattern about the component body defining an asymmetrical component comprising the component resistant to traveling wave vibration.

Abstract: An electrical submersible pump assembly includes a centrifugal pump having stages. Each of the stages has an impeller in cooperative engagement with a downstream diffuser. The impeller is axially movable relative to the downstream diffuser between a downthrust and an upthrust position. The downstream diffuser has an annular downstream wall surface, relative to the impeller, defining a downstream cavity. The impeller has a downstream balance ring that locates alongside the downstream wall surface. An annular clearance between the downstream balance ring and the downstream wall surface increases in response to the impeller moving from the downthrust to the upthrust position.

Abstract: A fluid machine in communication with a thrust bearing fluid source includes a housing having a bearing portion receiving fluid from the fluid source. A bearing chamber is formed in the bearing portion. An extension of a rotor is positioned within the bearing chamber so that a first pocket is disposed adjacent to a first side of the extension and a second pocket is disposed adjacent to a second side of the extension. An extension lateral side is adjacent to the bearing chamber lateral side. The extension comprises a first channel extending from a first half of the extension lateral side to the first pocket. The extension comprises a second channel extending from a second half of the extension lateral side opposite the first channel to the second pocket. The bearing chamber receives fluid from the bearing channel which is communicated to the first and second channels and the pockets.

Abstract: The present invention relates to a cooling device for a jet engine having an axial compressor with several compressor stages including a rotor with rotor blades, a stator with stator vanes and an annulus. In order to reduce the temperature of the components at the outlet of the high-pressure compressor by simple measures and hence to increase the efficiency of a jet engine, a slot-like branch opening surrounding the rotor for a cooling airflow diverted from the main airflow into a first cavity upstream of the rotor is provided upstream of the last compressor stage of the axial compressor, with passage openings being arranged in the rotor for passing on the diverted cooling airflow from the first cavity into a second cavity downstream of the rotor.

Abstract: The present disclosure relates to a rotary blood pump with a double pivot contact bearing system with an operating range between about 50 mL/min and about 1500 mL/min, wherein the force on the upper bearing is less than 3N during operating speeds up to 6000 rpm. The disclosure also relates to a method of using a blood pump system for persistently increasing the overall diameter and lumen diameter of peripheral veins and arteries by persistently increasing the speed of blood and the wall shear stress in a peripheral vein or artery for period of time sufficient to result in a persistent increase in the overall diameter and lumen diameter of the vessel.

Abstract: A centrifugal fluid machine includes an impeller (4) that has a front shroud (41) arranged on one side in an axial direction, a rear shroud (42) arranged on the other side in the axial direction, and a plurality of blades (43) provided side by side in a circumferential direction between the front shroud and the rear shroud and is rotatably supported within a casing (2); a suction passage (2A) that allows a fluid to be sucked therethrough in the axial direction toward the impeller with the rotation of the impeller; a discharge passage (2B) that allows a fluid delivered under pressure by the impeller with the rotation of the impeller to be discharged in a direction intersecting the axial direction of the impeller; and a first flow path (5A) that communicates with the discharge passage, leads to the suction passage through a gap between the casing and the rear shroud, and an opening (5Aa) that opens toward the downstream side of the suction passage in a suction direction of a fluid.

Abstract: The blower comprises: a stator being provided in a case; a radial bearing being provided in the case; a rotor shaft being provided in the case and supported by the stator and the radial bearing; a rotor being integrated with the rotor shaft; and an impeller being integrated with the rotor shaft, the impeller sucking a fluid into the case from an axial direction and sending the same in the circumferential direction of the impeller. The impeller is attached to the rotor shaft to make a blade forming surface of the impeller face the rotor in the axial direction. A shaft end of the rotor shaft, which is located on the opposite side of the impeller, is supported by a thrust receiving member.

Abstract: A hydraulic device includes a cover plate with a cylinder hole opposite an end surface of a rotating shaft of a gear which receives two thrust forces in the same direction. A piston extends through the cylinder hole. A working liquid in a high pressure side acts on a back surface of the piston to press the piston onto the end surface of the rotating shaft, thereby causing a drag that cancels the two thrust forces acting on the gear.

Abstract: A turbine includes a stator (10) and a rotor (20); a plurality of turbine stages (30) through which a flow path of an operating fluid extends; an axial thrust balancing piston (40) arranged at the rotor and a first piston chamber (41) connected to one of the turbine stages (30.1) so that the operating fluid can be conveyed into the first piston chamber with a first fluid pressure, and a second piston chamber (42) has a counterpressure so that an axial thrust opposed to a flow direction of the operating fluid can be exerted on the rotor; and a pressure control device (60) connected to the second piston chamber. The pressure control device constructed to vary the counterpressure by controlled removal of fluid from the second piston chamber so that the axial thrust of the axial thrust balancing piston can be varied.

Abstract: A product and method for use with a turbocharger system may include a housing with a shaft rotatably supported by the housing. The shaft may extend in an axial direction. A bearing assembly may support the shaft in the housing. A wheel may be connected to the shaft and may rotate relative to the housing. A clearance opening may be defined in the axial direction between the wheel and the housing. A thrust washer may be engaged with the bearing assembly. The thrust washer may have an outer circumference and may be movable relative to the housing. An efficiency washer may be disposed around the outer circumference of the thrust washer and may determine the clearance opening by defining a space within which the thrust washer moves relative to the housing in the axial direction.

Abstract: The invention provides a tilting-pad thrust bearing that requires less oil supply and a rotary machine having the same. A tilting-pad thrust bearing 100 comprises: multiple oil inlets 10 disposed in spaces between pads 6; multiple outflow guide grooves 12 each formed near the inner circumferential edge of the sliding surface of the pad 6 such that the outflow guide grooves 12 extend in a circumferential direction; and multiple inflow guide grooves 13 provided separately from the outflow guide grooves 12 and formed at the leading ends of the sliding surfaces of the pads 6 so as to be located more radially inward than the oil inlets 10. Each outflow guide groove 12 is open to the sliding surface and the trailing end surface of the pad 6. Each inflow guide grooves 13 is open to the leading end surface and the sliding surface of the pad 6.

Abstract: A compressor oil seal comprising a thrust bearing (59) adapted for insertion into a turbocharger housing cavity (33), concentric with the turbocharger's compressor wheel shaft (11). An insert (360) is adapted for insertion into the cavity (33) adjacent the thrust bearing (59), wherein the thrust bearing (59) and insert (360) are configured to provide an oil drain cavity (35) therebetween. The oil seal also includes an oil flinger (340) that includes a flinger flange (382) and a sleeve portion (383) extending therefrom. The flinger flange (382) extends between the thrust bearing (59) and the insert (360). A plurality of spiral vane segments (74) are circumferentially spaced about the flinger flange (382). Each spiral vane segment (74) extends arcuately from a first end (372) to a second end (373). The spiral vane segments (74) are disposed between the flinger flange (382) and the insert (360).

Abstract: A turbocharger includes: a bearing provided in a turbocharger body, and configured to rotatably support a turbine shaft in an insertion hole formed in the bearing; and an opposing portion which faces an end surface of the bearing in an axial direction of the turbine shaft. An end-surface guide portion is provided to any one of an opposing surface of the bearing which faces the opposing portion, and an opposing surface of the opposing portion which faces the bearing. The end-surface guide portion configured to make the insertion hole and an outer peripheral edge of the end surface of the bearing in radial directions of the turbine shaft communicate with each other extends forward in a rotational direction of the turbine shaft from a part of the end surface of the bearing which communicates with the insertion hole.

Abstract: A system and method for sealing a shaft disposed for rotation within a casing, where two axially-spaced seal rings of an oil film seal extend around the shaft and define a clearance therebetween. Oil is pumped into the clearance from an oil reservoir and a portion of the oil is received in an annular port defined in the casing between an outer labyrinth seal and one of the axially-spaced seal rings. The oil mixes with a process gas to for an oil and gas mixture. A blower is in fluid communication with the annular port and circulates the oil and gas mixture to a trap where the oil is separated from the process gas and a separated process gas is returned back to the annular port.

Abstract: A thrust shaft for a fan has a shaft body with an enlarged disk adjacent one axial end to provide a rotating surface in a pair of thrust bearings. A first cylindrical portion extends from the disk in a first direction, and a second cylindrical portion extending from the disk in a second opposed direction. The second cylindrical portion has a hollow bore, and there are a plurality of holes extending through the second cylindrical portion to communicate an outer periphery with the bore. A ratio of the diameter of the bore to a diameter of the plurality of air holes is between 6.60 and 7.00. A ratio of an overall length of the second cylindrical portion, and a distance from a face of the enlarged disk to a center of the holes is between 14.4 and 15.2. A thrust bearing assembly, a fan, a cabin air supply system, and a method are also disclosed.

Abstract: An impeller includes a plurality of vanes formed around a hub, each of the plurality of vanes defines an offset between a leading edge and a trailing edge.

Abstract: The present invention provides a method and apparatus of inhibiting a thrust bearing capacity of a compression system from being exceeded during a surge event in which a thrust bearing is biased with a biasing force to increase the thrust bearing overload margin between the capacity of thrust bearing to absorb axial forces and the greatest force produced during the surge event. This biasing force can be produced by appropriately sizing the high pressure seal on the side of the impeller opposite to the inlet of a compressor of the compression system so that the back disk force produced in the high pressure region of the high pressure seal and the low pressure region located inwardly of the high pressure region creates the desired bias force value and direction.

Abstract: An air cycle machine has a housing which holds a compressor section, and a turbine section having an expansion area, and a fan section disposed outside of the housing. A shaft, which attaches to and is coaxial with the compressor section, the turbine section and the fan section, is supported by an air journal bearing and an air thrust bearing. The shaft has a hollow core for porting cooling air from the air journal bearing and the air thrust bearing, and a tube that extends into said expansion area and communicates cooling air from the turbine expansion area to the thrust bearing.

Abstract: An expander-generator is disclosed having an expansion device and a generator disposed within a hermetically-sealed housing. The expansion device may be overhung and supported on or otherwise rotate a hollow expansion rotor having a thrust balance seal being arranged at least partially within a chamber defined in the expansion rotor. Partially-expanded working fluid is extracted from an intermediate expansion stage and a first portion of the extracted working fluid is used cool the generator and accompanying radial bearings. A second portion of the extracted working fluid may be introduced into the chamber defined within the expander rotor via a conduit defined in the thrust balance seal chamber. The second portion of extracted working fluid minimizes unequal axial thrust loads on the expander rotor due to the overhung arrangement.

Abstract: An axial flow pump for a blood circulating pump for the circulation of blood, the rotor the rotor being constructed and arranged to impel blood in a downstream direction upon rotation of the rotor about its axis in a forward circumferential direction. The rotor is provided with hydrodynamic thrust bearing surfaces, each such thrust bearing surface being constructed and arranged to apply a hydrodynamic force to the rotor with a component of the force in the downstream direction upon rotation of the rotor in the forward circumferential direction.

Abstract: A centrifugal pump for delivering hot fluids, having a contacting shaft seal, a seal housing (13) for the shaft seal (14), and a return line (8) for a partial flow of the delivered fluid, in which no delivered fluid is discharged out of the seal housing (13); a separate housing cover (9) is disposed between the seal housing (13) and the pump housing (1); there is a contact surface which minimizes heat transfer between the seal housing (13) and the housing cover (9); and the return line (8) is connected to the housing cover (9) and/or to the pump housing (1).

Abstract: A compressor rotor compresses and delivers compressed air across a turbine rotor. The turbine rotor is connected to the compressor rotor such that rotation of the turbine rotor drives the compressor rotor. A shaft is connected to rotate with the turbine rotor and the compressor rotor. A thrust bearing is provided by a member extending perpendicular and radially outwardly of the shaft. The member rotates with the shaft and faces a first housing wall. A hollow chamber is formed on an opposed side of the first housing wall. A cooling air path supplies air across a thrust bearing surface, and between the member and the first housing wall. The first housing wall has a communication hole for communicating cooling air from the cooling air path into the hollow cavity to drive air within the hollow chamber. Also, a housing incorporating the communication hole is disclosed.

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.