Abstract: A rolling bearing device includes a bearing housing supported on a casing of a turbocharger, and a pair of rolling bearings mounted within the bearing housing and rotatably supporting a turbine shaft. A middle position between the pair of rolling bearings in an axial direction and a central portion of the bearing housing in the axial direction are offset from each other in the axial direction. Each of the rolling bearings includes an inner ring, an outer ring, an intermediate ring interposed between the inner and outer rings, a row of rolling elements rollably interposed between the inner ring and the intermediate ring, and a row of rolling elements rollably interposed between the intermediate ring and the outer ring. The intermediate ring has a damper function to be very slightly displaced or very slightly deformed elastically so as to damp vibration produced during rotation of the turbine shaft.

Abstract: In a rotatable duct type shrouded rotating wing, permanent magnets are arranged in the outer periphery of a rotatable duct, rotor blades are connected to the inner periphery of the rotatable duct, the rotor blades having a rotatable support portion at about every 2.5 m to prevent deflection or distortion. The shroud and the rotatable duct are constantly in vertical contact with each other, and an appropriate horizontal spacing is provided between the inner periphery of the shroud and the outer periphery of the rotatable duct to permit expansion and contraction of the rotatable duct and the rotor blades. Accordingly, even if the shrouded rotating wing is of a large radius, is used in a horizontal orientation and undergoes a rapid change of direction mounted to a turntable, it always rotates stably to generate lift and thrust.

Abstract: Roller bearings, and struts and gas turbine engines using such bearings are provided. In this regard, a representative roller bearing for a gas turbine engine includes: a roller having a rolling surface and an end; a race having a flange and defining a raceway, the raceway terminating at the flange, the raceway being operative to receive the roller such that the rolling surface of the roller engages in rolling contact with the raceway; and a hard coating applied to the flange such that the end of the roller engages in sliding contact with the coating.

Abstract: The invention relates to a turbocharger (1) having a cartridge (K), which is arranged in a turbine housing (2), for the variable turbine geometry, having a bearing housing (3) which is arranged between the turbine housing (2) and a compressor housing of a compressor wheel and in which is arranged a bearing arrangement for a shaft (W) which supports the turbine wheel and the compressor wheel, and having a plate spring (4) which is arranged between the cartridge (K) and the bearing housing (3), wherein the plate spring (4) is constructed from at least two material layers (5, 6) and an isolator (17).

Abstract: A ball bearing for use in cryogenic applications has an inner ring and an outer ring that define a raceway between them, and there is a set of rolling balls in the raceway with slug ball separators between adjacent rolling balls. The bearing may be used in a pump for cryogenic fluids such as LNG, LOX, LH2, etc.

Abstract: In a high-speed rotating shaft (10) of a supercharger which is rotatably supported by two radial bearings (12a, 12b) spaced at a fixed distance (L), directly couples a turbine impeller fixed to one end and a compressor impeller fixed to the other end, and transmits a rotational driving force of the turbine impeller to the compressor impeller, a small shaft portion (14) having a smaller diameter than a bearing portion is provided between bearings. The small shaft portion (14) is offset to a compressor side.

Abstract: An exemplary method includes positioning a plurality of seal rings on a shaft operably coupled to a turbine wheel and inserting the shaft into a bore via axial inward movement wherein during insertion, an outer seal ring contracts and then expands along a chamfer to reach an outer seal seat. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: A frame (10) for an electrical fan includes a bracket (20) and a bearing support (30) located at the center of the bracket. The bearing support includes a metal tube (50) and a plastic body (40) connecting with the metal tube. The metal tube defines at least one connecting hole (52) in a wall thereof. The plastic body includes an inner portion (42) located inside the metal tube, an outer portion (44) located outside the metal tube, and a connecting portion (46) located in the connecting hole and integrally connecting the inner and the outer portions of the plastic body. The inner portion is used for engaging with two bearings (60) for rotatably connecting with a rotor shaft of the electrical fan.

Abstract: A wind power plant comprises an outside ring, an inside ring and roll bodies arranged between an inside jacket of the outside ring and an outside jacket of the inside ring for permitting twisting or rotation of the bearing rings against one another. One of the rings on the jacket comprises an auxiliary sensor at least along a portion of the periphery. The auxiliary sensor together with the primary sensor provided in the other bearing ring are configured in such a way that a twisting or rotational position of the two bearing rings relative to one another can be detected.

Abstract: A cooling fan includes a fan housing (50) having a central tube (52), a bearing structure received in the central tube, a stator (60) mounted around the central tube, and a fan blade set (70). The bearing structure includes a shaft (30) being rotatably received in the central tube and connecting to the fan blade set. An inner bearing (20) is fixedly mounted around the shaft to rotate with the shaft. Upper and lower outer bearings (10) are fixedly mounted into the central tube and are mounted around two opposite ends of the inner bearing, respectively. The inner and outer bearings are made of magnetic materials. The inner bearing floats between the outer bearings whereby rotation of the shaft does not cause the inner and outer bearings to wear.

Abstract: Method and arrangement for providing a turbine or compressor device having a rotor (1), that includes a first rotor section (2) having at least one disc-shaped or annular element (3) which has a multiplicity of blades (4) arranged in series on a circumferential path for guiding a gas flow, and a second, elongate rotor section (5) which projects at right-angles from the rotor disc (3) and which has a rotor shaft (6) connected to the rotor disc. A first and second bearing (8, 9) are fitted at a distance from one another along the rotor shaft (6), and the first bearing (8) is arranged closer to the rotor disc (3) than the second bearing (9). The bearing holder (25) of the first bearing (8) has a greater outside width than other than other components (9, 14, 15, 31) arranged on the rotor shaft (6) between the first bearing (8) and the free end of the rotor shaft (7).

Abstract: The present invention relates to a gas turbine engine comprising a shaft, a bearing, a coupling supported by the bearing, the shaft being engaged by an end trunnion inside the coupling and fixed to the coupling by means of a cylindrical nut. The engine is characterized in that the nut is in axial abutment in a first direction against the coupling and the trunnion is screwed onto the nut, a slotted stop ring housed in an annular groove of the nut forms an axial abutment in the direction opposing the first direction, so as to allow the removal of the trunnion from the coupling by unscrewing the nut.

Abstract: A blower includes a stationary portion including an inlet and an outlet, a rotating portion provided to the stationary portion, and a motor adapted to drive the rotating portion. The inlet and outlet are co-axially aligned. The stationary portion includes a housing, a stator component provided to the housing, and a tube providing an interior surface. The rotating portion includes one or more bearings that are provided along the interior surface of the tube to support a rotor within the tube. In an embodiment, the blower is structured to supply air at positive pressure.

Abstract: A cooling fan includes a fan housing (10) having an upper tube (111) extending downwardly from a top side thereof and a lower tube (121) extending upwardly from a bottom side thereof, a ball bearing (20) being mounted in the upper tube, a sleeve bearing (30) being mounted in the lower tube, a stator (45) mounted around the lower tube, and a rotor (40). The rotor includes a hub (401) located between the ball bearing and the sleeve bearing and a shaft (50) extending through the hub. Two ends of the shaft are rotatably received in the ball bearing and the sleeve bearing, respectively.

Abstract: A miniature blower fan includes an axial seat and a shaft extending from a central portion of the axial seat. A plurality of vanes and a magnet are mounted to an outer circumferential wall of the axial seat. The vanes extend radially outward from the outer circumferential wall of the axial seat and are spaced at regular intervals. The miniature blower fan further includes a casing having an air inlet. The vanes have a thickness larger than 30% of an overall height of the vanes and the magnet. In another embodiment, a web extends radially outward from the outer circumferential wall of the axial seat, the vanes are mounted to a side of the web, and the magnet is mounted to the other side of the web. The vanes have a thickness larger than 30% of an overall height of the web, the vanes, and the magnet.

Abstract: A rotor support includes a first ring disposed around a first axis, a second ring disposed around the first axis downstream from the first ring, and a plurality of beams extending between the first and the second rings. Each beam is configured to provide an axial stiffness, when an axial force is exerted on the first ring, and a radial stiffness, when a radial force is exerted on the first ring. Each beam has a height extending parallel to a second axis and a width extending parallel to a third axis. The beams are distributed around the first ring to provide a substantially uniform circumferential axial stiffness around the rotor support, and the height of each beam is greater than the width of each beam. Damping can be provided by the placement of a damper between the rotor support and the support housing.

Abstract: A heat dissipation fan includes a fan frame, a stator mounted to the frame, and a rotor rotatably disposed around the stator. The fan frame includes a bracket, a central tube for positioning the stator, and a supporting member. The supporting member is made of a material having a higher bending strength than a plastic material used to form the bracket and the central tube. The supporting member includes a main body connected to the central tube, a plurality of ribs extending radially outwardly from the main body, and a plurality of engaging units formed at free ends of the ribs, respectively. The engaging units are embedded in the bracket for integrally connecting the central tube to the bracket.

Abstract: A cooling fan includes a base (31), an impeller (33), a magnetic ring (38) and a stator (30). The base has a central tube (311) extending upwardly therefrom. An annular protrusion (313) is formed around the tube near a bottom end thereof. The protrusion is homocentric with the tube. The impeller includes a hub (332) and a shaft (333) extending downwardly from a central portion of the hub. The stator is mounted around the protrusion. An annular space (320) is defined between the stator and the tube. The magnetic ring is received in the annular space, and is fixedly mounted around the shaft to rotate with the shaft during operation of the cooling fan.

Abstract: A shaft oil purge system comprises an entrance seal, an exit seal and a buffer air flow. The entrance seal comprises a circumferential carbon seal running on an inner shaft and another carbon seal running on an outer shaft. The exit seal comprises a labyrinth seal positioned on the inner shaft and towards the exit end of the annulus between the shafts. An abradable material filled groove positioned radially outward from the exit seal allows the inner shaft to rub without compromising the integrity of the outer shaft. The buffer air flow enters the annulus from a cavity at the entrance seal, purges oil from the annulus and improves the efficiency of the seals.

Abstract: This invention provides a small, high efficiency, oil-free turbine-driven alternator (i.e. turboalternator) suitable for conversion of stored energy in a process gas to electrical power, facilitating recapture of energy during operation that would otherwise be wasted. The turboalternator includes a turbine and a generating device operatively connected together by a rotating shaft capable of rotating at high speeds. The rotating shaft is supported by foil gas bearings.

Abstract: A centrifugal environmentally safe pump including a motor driven pump shaft having a fluid pumping impeller affixed thereto. A plurality of annular shaft supporting bearing assemblies are disposed along the shaft adjacent a lubrication chamber, the lubrication chamber housing lubrication fluid (e.g. oil) maintained at a level below rotating portions of the bearing assemblies so as to maintain a low operating temperature within the chamber and adjacent the bearings. A lubricating fluid dispenser having a thin-profile, disc-shaped portion is affixed to the pump shaft within the lubrication chamber for rotation along with the shaft. A plurality of wire-like fluid contacting members are loosely connected along the outer periphery of the disc-shaped portion through respective bearing sleeves, the wire members for dipping into the lubricating fluid when the pump shaft is rotating thereby dispersing or misting the fluid throughout the chamber.

Abstract: Component parts for a mixing assembly adapted to be used with clean in place techniques. The component parts may include an impeller assembly, an adjustable hub assembly, and a steady bearing assembly. The bearing assembly may include a supporting structure having a fitting and a plurality of legs extending from the fitting and securely engaging the vessel, and a guide bearing bore adapted to receive a shaft, wherein the guide bearing is adapted to be removably engaged from the supporting structure and wherein the guide bearing is removable from the supporting structure shaft without necessitating removal or lifting of the shaft.

Abstract: A light steel frame fan structure comprises a rotating disk, a fixing ring. A receiving groove is disposed on the rotating disk, an axial column is disposed in the receiving groove and a locking hole is disposed on the axial column; a hollow engaging column is projected from on surface of the fixing ring and an indentation portion indented inward is disposed on another surface of the fixing ring; the indentation portion is communicated with the through hole. When the fixing ring is to be folded with the rotating disk, the axial column of the rotating disk is passed through the through hole on the engaging column of the fixing ring, at least one bearing is placed in the indentation portion, and a locking element is then locked in the locking hole on the axial column to allow the rotating disk to be pivotally connected to the fixing ring. Whereby, the use life of the fan can be extended, the noise can be avoided and the components installment can be stabilized.

Abstract: When it is assumed that a thickness of a stator core is TSt as measured in parallel with an axial direction of a rotary shaft and a thickness of the fan housing is TFr as measured in parallel with the axial direction, a ratio of TSt/TFr is defined as 8% to 25%. With this arrangement, among frequency components included in vibration to be carried to the fan housing when a rotor is rotated, an over-all value of frequency components caused by cogging torque becomes smaller than an over-all value of frequency components caused by unbalance of the rotor. As a result, the vibration to be carried to the fan housing when a rotor is rotated may be restrained, in particular, when the rotor is rotated at a low speed.

Abstract: An arrangement for supporting a shaft of a vacuum pump includes a first bearing for supporting the shaft at one of its end, a second bearing for supporting the shaft at another of its ends and formed as a rolling bearing, a holder for receiving the second bearing and including an oscillating base, a fixation member secured in the vacuum pump housing, metallic connection members for connecting the oscillating base with the fixation member and axial springs arranged between the oscillating base and the fixation member and providing for the axial stiffness of the holder which is greater than its radial stiffness thereof and greater than the axial stiffness of the first bearing.

Abstract: A bearing assembly for a gas turbine engine rotor includes, in an exemplary, an inner race, an outer race assembly, and a rolling element. The outer race assembly includes a body, a plurality of first springs attached to the body, and a plurality of second springs. Each first spring is radially aligned with a corresponding second spring forming a spring pair. The outer race assembly also includes a plurality of connecting members. Each connecting member extends between and connects a first end of the first spring and a first end of the second spring of said spring pair. The outer race assembly further includes a flange with each second spring attached to the flange.

Abstract: A ball bearing assembly for a gas turbine engine comprises an inner race that couples to a rotor shaft; an outer race that couples to a primary static structural support; a plurality of ball elements between the inner race and the outer race; and a ball cage that comprises a carbon-carbon composite material to maintain the relative radial spacing of the ball elements between each other within the inner race and the outer race after subjection to high loads, heat generation and long-term storage.

Abstract: A multistage centrifugal pump in which each stage includes a one-piece or multi-piece housing and an impeller disposed therein. The pump stages are arranged between an inlet end member and an outlet end member and retained therebetween by connectors so as to be connected to a flow-guiding system. All impellers are positioned on a single pump shaft that is supported by at least two pump bearings. One end of the pump shaft is provided with a device for receiving a connector of a drive unit, and outer support members are disposed at mounting points adjacent the end members in order to mount the centrifugal pump in its installation location. The pump shaft (3) is supported by two two pump bearings (11, 12), with the maximum distance (LL) between confronting sides of the two pump bearings (11, 12) being less than or equal to a minimum structural stage height (LM) multiplied by the number of pump stages (2.1-2.5) minus 1.

Abstract: An exemplary thrust collar for a turbocharger includes a substantially annular body that includes an axis of rotation, a bore, opposing end surfaces where one of the end surfaces is substantially normal to the axis of rotation and capable of seating a back end of compressor wheel, and a surface disposed in the bore where the surface is substantially normal to the axis of rotation and capable of seating a surface of a turbocharger shaft. The axial distance between the end surface for seating a back end of a compressor wheel and the surface disposed in the bore for seating a surface of a turbocharger shaft is selected to improve balancing of a rotating assembly. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: A cooling fan includes a frame (30), a stator (20) and a rotor (10). The frame includes a base (32) having a central tube (34). A bearing (22) is received in the central tube. The rotor includes a hub (11) having a shaft (15) extending from the hub into the bearing. An oil retaining ring (40) is mounted on the hub around the shaft and near a top of the central hub.

Abstract: A lubricating system for a fan (10) includes a lubricant storage space (17) formed at an end portion of the fan for receiving lubricant therein. A lubricant temporary retaining space (145) is defined at the other end portion of the fan for temporarily retaining the lubricant therein. A lubricant returning space (125) communicates the lubricant storage space with the lubricant temporary retaining space for enabling the lubricant to flow from the retaining space to the storage space. The returning space is defined in a tube (12) made of plastic, wherein a bearing (13) is mounted in the tube and a stator (15) is mounted around the tube.

Abstract: A method for assembling a gas turbine engine assembly includes coupling a fan assembly to a core gas turbine engine such that the fan assembly is upstream from the core gas turbine engine, coupling a fan assembly to a core gas turbine engine such that the fan assembly is upstream from the core gas turbine engine, wherein the core gas turbine engine includes a high-pressure turbine, coupling a low-pressure turbine downstream from the core gas turbine engine such, wherein the low-pressure turbine includes a disk and a plurality of splines formed in the disk, providing a shaft that includes a first end and a second end that includes a plurality of splines, coupling the shaft between the low-pressure turbine and the fan assembly, and coupling a differential bearing between the shaft and the high-pressure turbine such that the shaft provides rotational support for the high-pressure turbine.

Abstract: In an assembly with two concentric shafts, the internal shaft projecting beyond the external shaft, a seal support sleeve placed between the shafts has a conical shape and bears on a spacer mounted on the external shaft between an assembly nut of the forward end of the external shaft and a bearing, so that the nut is accessible to be unscrewed through the space between the two shafts, thus enabling the external shaft to be disassembled. The invention may be applicable to front bearings of gas turbine high pressure shafts and makes it possible to disassemble the high pressure body from the rear, without needing to disassemble equipment, such as a fan on the front of the machine, or hindering the installation of a gear.

Abstract: A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor that includes a first plurality of rows of turbine blades configured to rotate in a first rotational direction, providing a low-pressure turbine outer rotor that includes a second plurality of rows of turbine blades configured to rotate in a rotational direction that is opposite the first rotational direction, and coupling a support structure between the outer rotor and a turbine mid-frame such that the support structure supports a forward end of the outer rotor, and wherein the support structure includes a first portion that has a first coefficient of thermal expansion and a second portion that has a second coefficient of thermal expansion that is different than the first coefficient of thermal expansion.

Abstract: A fan assembly includes an end bracket which is coupled to a motor assembly. The end bracket includes a circumferential channel which is interrupted by an opening. A fan is provided which includes a plurality of blades. A shroud at least partially encloses the fan and defines a chamber. An insert, which may or may not be an integral part of the end bracket, is received in the chamber and includes a circumferential ramp. The circumferential ramp is configured to provide the chamber with an internal cross-sectional area which varies circumferentially so as to improve airflow efficiency.

Abstract: A turbine section of an engine that includes a shaft, a plurality of blades extending radially relative to the shaft, a bearing assembly, a flowpath housing, and a shroud is provided. The bearing assembly is mounted to the shaft adjacent to the plurality of blades. The flowpath housing is coupled to the bearing assembly and includes an inner cylinder, an outer cylinder, and a strut. The inner and outer cylinders each include a strut attachment point between which the strut is coupled, and the outer cylinder includes an outer surface. The shroud is disposed concentric to the outer cylinder and has an inner surface including a groove formed therein that is substantially aligned with the outer cylinder strut attachment point. The groove has a depth that provides and maintains a gap between the outer cylinder outer surface and the shroud inner surface when the flowpath housing is exposed to heat and the strut radially expands.

Abstract: The turbine engine of the invention includes a rotor with at least one bearing, mounted on a bearing supporting part, said part being connected to the fixed structure by an uncoupling device, including at least one fusible screw passing through at least one bore, said screw comprising a head and a threaded portion, a fusible portion forming a preferential failure area, located between the head of the screw and its threaded portion. The screw comprises, between its threaded portion and its fusible portion, a portion for blocking the screw in rotation, cooperating with a complementary blocking portion provided in the bore. By means of the invention, the torsional torque related to the tightening of the screw is not transmitted to its fusible portion.

Abstract: The bearing system includes a first component having a first substrate and a first coating. The first coating includes a DLC layer and a DLN layer between the DLC layer and the substrate. A second component is in sliding engagement with the first component.

Abstract: A direct replacement impeller hub for the torque converter of an automatic transmission and a method of repairing an impeller assembly utilizing the replacement impeller hub to provide increased service longevity. In the present impeller hub the geometric roundness characteristic of the impeller hub is controlled to an exacting tolerance during the manufacturing process in accordance with American National Standards Institute (ANSI) definitions to provide a close tolerance fit within a mating bearing sleeve. The present impeller hub is also finish ground in accordance with ANSI definitions to reduce surface friction and to provide an optimal sealing surface for engagement with a radial seal, which is disposed about the impeller hub sealing it to prevent contaminants from entering the hydraulic pump of the transmission. The present impeller hub also includes additional structural features such as fillet radii machined on selected features to facilitate assembly of the torque converter.

Abstract: A turbine shaft may be used to remove a heat load from pliant bearings without requiring the use of a process fluid for cooling the turbine shaft. The turbine shaft comprises a heat conductive sleeve disposed between an outer surface of a tie rod shaft and an inner surface of a bearing journal; the heat conductive sleeve having a sleeve inner surface separated from a sleeve outer surface by a sleeve thickness; the heat conductive sleeve having a first end separated from a second end longitudinally about a center axis; the sleeve outer surface being in physical contact with the inner surface of the bearing journal; and the heat conductive sleeve having a thermal conductivity that is greater than a thermal conductivity of the bearing journal.

Abstract: A bearing structure for the blade of cooling fan, comprises a hollow cylindrical body and an outward extended seat whose diameter is larger than the body. The seat has a recess at the bottom. The body forms a long cavity and upward flange. This bearing is placed in the hub of the cooling fan; the blade rotor shaft is inserted into the cavity of the bearing, and the flange of the body works as a C-clamp buckling the round groove on the blade rotor shaft to confine the motion of the rotor shaft. The bearing design renders easy fabrication and assembly, good dust shield to keep the dust off the rotor and reduce the rotary friction and resistance to the minimum. In addition, the magnetic force is limited for the self-adjustment, which further alleviates the frictional resistance sop the service life the cooling fan is extended longer.

Abstract: The system enables an increase in the guidance length of the outer pivot of the vane, so that the bushing can be extracted without needing to open the stator casing. It mainly includes a bushing placed inside a bossing of the stator, the length of which is greater than the length of the bossing projecting outwards from the bossing. Thus, the contact length of the outer pivot is prolonged. The bushing is terminated at its end by a gripping hook to enable extraction of the bushing by means of a claw. It is advantageously also provided with a positioning edge.

Abstract: A single-shaft multistage pump is provided to make small-sized and space-saved possible. The single-shaft multistage pump includes a rotary shaft on which impellers are disposed at multiple stages, bearings and for supporting the rotary shaft, and a balance device adapted to apply, to the rotary shaft, a balance thrust force opposing an impeller thrust force. A water-lubricated bearing is used as each of the radial bearings, and the rotary shaft is supported by the water-lubricated bearings with a balance member of the balance device interposed therebetween.

Abstract: A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor configured to rotate in a first direction, providing a low-pressure turbine outer rotor configured to rotate in a second direction that is opposite the first rotational direction, and coupling at least one foil bearing to at least one of the inner and outer rotors to facilitate improving clearance control between a first rotating component and at least one of a second rotating component and a non-rotating component.

Abstract: An air turbine starter (ATS) configured to couple to a gearbox, the ATS including an output shaft having an outer peripheral surface, a gearbox section, and an ATS section, the gearbox section configured to be disposed within, and coupled to, the gearbox and the ATS section configured to be disposed within the ATS, and a shield plate extending radially from the outer peripheral surface and coupled to the ATS section of the output shaft.

Abstract: A method for assembling a gas turbine engine includes providing a low-pressure turbine inner rotor that includes at least a first pair of adjacent rows of turbine blades that are configured to rotate in a first direction providing a low-pressure turbine outer rotor that includes a forward end, an aft end, and at least one row of turbine blades that is rotatably coupled between the first pair of inner rotor turbine blades, wherein the at least one row of outer rotor turbine blades is configured to rotate in a second direction that is opposite the first direction, and coupling a support assembly between the first pair of inner rotor turbine blades such that the support assembly supports the outer rotor forward end.

Abstract: The rotor (5) of a gas turbine containing a compressor part (1) and a turbine part (3) is mounted in an axial thrust bearing (19) and in two radial journal bearings (16, 17). One of the bearings is a journal bearing (16) arranged in the intake area of the compressor part (1) and the other journal bearing (17) together with the thrust bearing (19) is arranged in the area of the turbine part (3).

Abstract: A cooling fan comprises a rotor configured to generate airflow. The cooling fan further comprises an outlet guide vane adapted to receive the airflow generated by the rotor and to orient the airflow in a substantially axial direction relative to the rotor. The cooling fan further comprises a diffuser configured to receive the airflow from the outlet guide vane and produce airflow with higher static pressure relative to an inlet of the diffuser. The cooling fan produces a work coefficient greater than 1.6 and a flow coefficient greater than or equal to 0.4.

Abstract: An electrical submersible pump runner having a core layer and a wear layer affixed to the core layer. One embodiment of the invention provides an electrical submersible pump that includes a motor section and a centrifugal pump section. A seal section and rotary gas separator may also be included. The pump is powered by an electric cable that connects the pump, located in a bore hole, to a power source on the surface. A thrust runner coated with a wear layer (e.g., polymer) is provided in the motor and/or seal section to reduce bearing temperature, provide longer bearing life, reduce costs, and facilitate overhaul. The runner may also function as a rotating up-thrust bearing when the runner is coated with a wear layer on one side that is formed with a bearing geometry. In this case, the up-thrust bearing may be eliminated.

Abstract: A vacuum pump of the invention comprises, in a common pump body (100): molecular drag pump stages (5) in series with regenerative pump stages (9). The molecular drag pump stages (5) comprise a molecular drag rotor (5a) including a blind axial cavity (5c) open towards the downstream end, and the motor (7) is housed at least in part in said blind axial cavity (5c). The drive shaft (8) is coupled via its upstream end (8a) to the molecular drag rotor (5a), and it is coupled via its downstream portion (8b) to the regenerative rotor (9a). The motor (7) is secured to the central segment of the drive shaft (8). This provides a universal pump of small size, enabling pumping to be performed from 1000 mbar down to 10?8 mbar, and suitable for being placed in the vicinity of a vacuum chamber.