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 vacuum pump (10) comprises at least one rotor shaft (12) having a rotor section (14) with a rotor (16), a bearing section (18) with a bearing (20), and a shaft sealing system (22) that is axially situated between the rotor section (14) and the bearing section (18). The shaft sealing system (22) axially comprises, on the side of the rotor, a gas seal (32) and, on the side of the bearing, an oil seal (34). The shaft sealing system (22) additionally comprises, between the gas seal (32) and the oil seal (34), a separating chamber, which surrounds the rotor shaft (12) and is ventilated by at least one separating chamber ventilation duct (60, 62). This enables the pressure difference that decreases via the gas seal and the pressure difference that decreases via the oil seal to be adjusted. An appropriate adjustment can prevent oil on the bearing side from passing through the oil seal toward the separating chamber.

Abstract: A front cover 5 of a converter cover 4 is formed with a punched hole 12, a thrust bearing 13 having the same outer shape as that of the punched hole 12 is fitted to the punched hole 12, a bearing housing 14 is fitted to the outside, thereby tightly closing the converter cover 4 to support the thrust bearing 13. A thrust applied from a turbine hub 9 to the thrust bearing 13 is received by a flange 14b of the bearing housing 14.

Abstract: A housing unit for a turbocharger (1) comprises a rotor shaft (18) to mount a rotor on both its ends. Furthermore, there is a bearing housing part (4) for supporting the rotor shaft (18), and a turbine housing (2), an opening or recess of which facing an end portion (5) of the bearing housing (4). In this way, the end portion of the bearing housing (4) may be inserted into the opening or recess and may be fastened to the wall of the turbine housing (2) which delimit and surround the opening or recess. Within the region between the end portion of the bearing housing (4) and the turbine housing (2), at least one heat resistant sealing (17, 31) is provided which may be formed of a mineral material or of metal.

Abstract: A drainage pump has a pump part in which blades mounted on a rotary shaft are arranged in a pump casing and an underwater bearing unit which uses pumped water mixed with hard particles as a lubricant and has a sliding bearing for journaling the rotary shaft. A portion of the rotary shaft journaled by the sliding bearing is formed of a cemented carbide material and a shaft journaling surface of the sliding bearing is formed of a thermoplastic resin material to be embedded with hard particles.

Abstract: A device (D) is dedicated to securing a machine shaft (AIP) on a bearing support (SP).

Abstract: An exemplary shield includes an attachment mechanism disposed on an outer surface to attach the shield to a joint of a boreless compressor wheel and a passage extending from a proximate end of the shield to a distal end of the shield. An exemplary method includes inserting a shield at least partially in a joint of a boreless compressor wheel and treating, at least partially, an end surface of the joint to thereby reduce fatigue of the boreless compressor wheel. Other exemplary joints, compressor wheels, shields, etc., are also disclosed.

Abstract: A guide device for guiding a variable-pitch blade, in particular in a turbomachine compressor, the blade having a pivot formed by a cylindrical axial shank mounted in a cylindrical housing of a casing and pivotally guided about an axis in said housing by bearings, where the bearings are abutment bearings with conical rollers, the axes of the rollers being substantially perpendicular to the pivot axis of the blade.

Abstract: A rotor and bearing system for a turbomachine. The turbomachine includes a drive shaft, an impeller positioned on the drive shaft, and a turbine positioned on the drive shaft proximate to the impeller. The bearing system comprises one gas journal bearing supporting the drive shaft between the impeller and the turbine. The area between the impeller and the turbine is an area of increased heat along the drive shaft in comparison to other locations along the drive shaft. The section of the drive shaft positioned between impeller and the turbine is also a section of the drive shaft that experiences increased stressed and load in the turbomachine. The inventive bearing machine system positions only one radial bearing in this area of increased stress and load.

Abstract: A vane arrangement for a compressor of a gas turbine engine comprises a plurality of circumferentially arranged vanes, a plurality of levers and a control ring. Each vane comprises a fixed upstream portion secured to a casing and a movable downstream portion pivotally mounted to the casing. The movable portion of each vane is pivotally mounted at the upstream end of the movable portion adjacent the fixed portion of the respective vane. The movable portion of each vane has a spindle extending through an aperture in the casing. Each aperture in the casing has an elongate shape in cross-section and each aperture has a bush arranged within the aperture and around the spindle to fill the elongate shaped aperture. The downstream end of the fixed portion of each vane has substantially the same shape as the upstream end of the movable portion of the respective vane.

Abstract: A bearing support for a rotor of an aircraft turbine engine which includes a front bearing and a front bearing support and bearing strut for securely attaching the front bearing, to the aircraft turbine engine support structure, wherein the front bearing support and bearing strut are integral with the aircraft turbine engine support structure.

Abstract: To further isolate imbalances in a rotating structure such as a gas turbine engine, an effective length between two bearings may exceed an actual length. This may be achieved via one or more tapering bearing supports associated with at least one of the bearings.

Abstract: A low-pressure turbine of a turbomachine, the turbomachine comprising a high-pressure turbine disposed upstream from the low-pressure turbine, and an exhaust casing disposed downstream from the low-pressure turbine, the low-pressure turbine comprising a rotor secured on a low-pressure trunnion, a low-pressure shaft, a first rolling bearing disposed on said low-pressure shaft and supporting a high-pressure trunnion having fastened thereon a rotor of the high-pressure turbine, a second rolling bearing disposed on said low-pressure trunnion downstream from said first rolling bearing and enabling said low-pressure trunnion to be centered relative to said exhaust casing, and a system of fluting for enabling said low-pressure trunnion to drive said low-pressure shaft, said system of fluting being disposed between said first and second rolling bearings.

Abstract: The invention is a fan drive attachment assembly for a motor vehicle that uses a tapered coupling to assemble the drive hub and fan drive together.

Abstract: An axial flow fan motor having an impeller molded integrally with a shaft from a synthetic resin. The shaft is easily assembled with a bearing arrangement by being brought into tight contact with the inner ring of the bearing arrangement and is reliably fixed thereto in the elastic region of the shaft. A through hole is formed in the shaft along its central axis. After the shaft is fit into the inner ring of the bearing arrangement, a metal pin is pressed into the axial through hole. Because the pin is pressed in, the shaft is elastically expanded and brought into tight contact with the inner ring and fixed thereto in the elastic region of the shaft. Furthermore, the distal end portion of the shaft elastically outwardly expands and is pressed against the end surface of the inner ring, thereby preventing the bearing arrangement from coming off the shaft.

Abstract: A fan seat (30, 30?) includes a basis (31) with a vertical extending tubal portion (32) having a pair of flanges (33) integrally formed on opposite ends of an inner circumferential surface thereof, and a bearing set (34, 34?) located in the tubal portion and sandwiched between the flanges. The bearing set includes a tube (36) and a pair of bearings (38) firmly secured in opposite ends of the tube. A method for producing the fan seat includes the following steps: providing a mold (50) with a cavity (53), locating the bearing set in the cavity with a space (60) formed between the bearing set and the mold corresponding to the tubal portion, injecting molten material into the space, and cooling the molten material whereby the molten material congeals into the tubal portion and integrates with the tube.

Abstract: A turbomachine has a turborotor made up of a shaft and a rotor disk, and an electric machine having an electric rotor. The rotor disk is arranged at one end of the shaft, in overhung manner, and the electric rotor is connected with the shaft of the turborotor. The electric rotor is arranged on the other end of the shaft, also in overhung manner, and the shaft is mounted on shaft bearings in a bearing housing that thermally separates the shaft bearings from the electric machine.

Abstract: An exemplary bore for a shaft of a turbomachine includes a longitudinal axis extending generally from an inner end to an outer end of the bore, an outer seat disposed proximate to the outer end of the bore at an outer seat radius for an outer seal ring wherein the outer seat comprises an inner end, an outer end, a step at the inner end extending radially inward to a step radius, and a chamfer at the outer end extending radially inward over an outward axial distance to a chamfer plateau radius and an inner seat disposed inward the outer seat at an inner seat radius for an inner seal ring wherein the outer seat radius exceeds the inner seat radius. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: An inline centrifugal mixed flow fan (20) includes an axially extending intake conduit (22). An inlet cone (28) is disposed at an intake end (24). An impeller (30) is disposed downstream of the inlet cone and includes a centrally disposed wheel-back (32) rotated by an electric motor (44), plural fan blades (34) extending radially outwardly from the wheel-back and a wheel cone fixedly (36) attached to and circumscribing the wheel blades. A driver chamber (48) downstream of the impeller includes plural radially extending straight vanes (50) to direct air to an outlet end (26). The fan is configured to achieve reduced sound level and increased efficiency.

Abstract: A shaft (12) for a pump (10) or other rotating machine, made substantially out of only engineering plastic—such as the polymer PEEK or some other selected polymer—and including portions having respective surfaces (12a–d) serving as bearing surfaces, the shaft (12) thus integrating the functions of both a shaft structure and a bearing structure. In some applications, the shaft (12) includes both portions having respective surfaces serving as radial bearing surfaces (12a–b) and also portions having respective surfaces serving as thrust bearing surfaces (12c–d), all made from the same engineering plastic as the rest of the shaft (12) and formed as part of the shaft (12). The engineering plastic may include one or more additives such as PTFE or carbon fiber, especially in case of dry-run applications.

Abstract: An ultra-high speed vacuum pump evacuation system includes a first stage ultra-high speed turbofan and a second stage conventional turbomolecular pump. The turbofan is either connected in series to a chamber to be evacuated, or is optionally disposed entirely within the chamber. The turbofan employs large diameter rotor blades operating at high linear blade velocity to impart an ultra-high pumping speed to a fluid. The second stage turbomolecular pump is fluidly connected downstream from the first stage turbofan. In operation, the first stage turbofan operates in a pre-existing vacuum, with the fluid asserting only small axial forces upon the rotor blades. The turbofan imparts a velocity to fluid particles towards an outlet at a high volume rate, but moderate compression ratio. The second stage conventional turbomolecular pump then compresses the fluid to pressures for evacuation by a roughing pump.

Abstract: Turbocharger comprising a rotor shaft (5), a turbine housing (2), a compressor housing (3) connected to the turbine housing (2), and including at least one air supply channel (13?) for supplying air to be compressed and at least one discharge channel (11) for delivering compressed air. One end of the rotor shaft projects into the compressor housing and supports a compressor rotor (21). A bearing (12) in the region of the compressor rotor supports the rotor shaft, and forms a bearing gap. The bearing includes two seals (29,30) axially spaced from one another to seal the bearing gap and to leave an intermediate space (31) between them. A suction channel (33,34) is connected to a vacuum source and sucks gas out of this intermediate space.

Abstract: A gas friction pump includes stationary (6) and rotatable (5) pump-active elements secured on a rotor shaft (4) and forming with the rotor shaft components of the rotor, with the rotor shaft (4) being supported by two, spaced from each other, radial bearings (8, 9), of which one is located closer to the gravity center of the rotor than the other, and an axial bearing (16), and with the radial bearing (9), which is located closer to the gravity center of the rotor, being formed as a gas bearing, and another radial bearing (8) being formed as a non-gas bearing.

Abstract: The invention relates to a turbine installation, especially a steam turbine installation. The inventive turbine installation comprises at least two partial turbines, each of the partial turbines having a rotor disk that extends along the main axis. Said rotor disks are rigidly interlinked to a shafting. At least one of the partial turbines has an inner housing that concentrically encloses the rotor disk and that is mounted so as to be axially displaceable in a bearing area. To allow for an axial displacement a push element transmits the axial force and is linked with the inner housing. In order to allow the inner housing to be axially displaced as easily as possible, the bearing area has a bearing device with a static friction and/or sliding friction that is so low that the axial misplacement that spontaneously occurs when the static friction is overcome during displacement of the inner housing is smaller 2 mm.

Abstract: An air turbine starter for use in aircraft or other gas turbine engine applications. In a particular embodiment, the air turbine starter has a thrust bearing having an outer ring, an inner ring, a cage and balls. The outer ring has a first shoulder, a second shoulder and a race surface therebetween to receive the balls. The second shoulder is smaller than the first shoulder. The orientation of the cage is such that the pilot of the cage is aligned to the first shoulder of the outer ring. The raceway curvature of the inner ring, the internal clearance, and clearance between the pilot and outer ring are all increased. An improved thrust bearing is also provided.

Abstract: A tubeaxial fan (10) broadly including a cylinder (12), a propeller (14) rotatably supported in the cylinder (12), and a drive assembly (16) operable to rotate the propeller (14) is disclosed. The propeller (14) includes blades (28,30,32,34,36,38) each having an inventive blade design. The inventive blade design presents a chord length (C), a stagger angle (?e), and a camber height (?c) that vary along each of the blades as shown in TABLE 1. The inventive blade design presents an external surface of each of the blades having a shape defined by the relative positioning of a plurality of coordinates contained in at least nine cross-sections (e.g., the blade (28) includes cross-sections (44,46,48,50,52,54,56,58,60)). The cross-sections (44,46,48,50,52,54,56,58,60) of the illustrated blade (28) have the corresponding plurality of coordinates listed in TABLE 2.

Abstract: A dampening system for a miniature high-speed turbojet engine provides single or multiple resilient mountings for forward and aft bearings which mount a rotor shaft. The self-induced first engine order of the rotating rotor shaft is transmitted through the forward and aft bearing and is then absorbed in the resilient mountings.

Abstract: An improved diesel engine water pump includes three main features that aid in extending the maintenance-free life of the pump. The impeller shaft is carried by tapered roller shaft support bearings of which the impeller bearing has a floating outer race that is urged axially by a preload spring to provide a prescribed axial preload that maintains concentricity of the shaft with the axis and prolongs bearing life. An improved oil seal combines an oil slinger, a stationary deflector and a lip oil seal with a return passage to the engine to more effectively limit oil leakage from the pump. An improved water seal includes pressurized water jets fed from the pump volute that flush wear particles from the water seal surface and increase water seal life. Further details of these features are also disclosed.

Abstract: A fan housing assembly includes a mounting base formed with a through hole thereon and a bushing. The bushing has a sleeve and is coupled to the mounting base by connecting the sleeve to the through hole. The mounting base and the bushing can be separately formed with predetermined materials in view of the different quality requirements before being assembled, thus resulting in lower manufacturing cost and enhanced flexibility in the fan design.

Abstract: The system comprises a nacelle mounted to turn about a vertical axis on the top of a mast and carrying a rotary portion which rotates about a substantially horizontal axis in a large diameter bearing. The rotary portion comprises a hub to which blades are fixed. The system has an electric generator comprising a stator and a rotor in the shape of a disk. The rotor is fixed by a connecting member to the hub adjacent the bearing so that the forces exerted by the wind on the rotary portion are transmitted directly to the bearing without passing through the electric generator.

Abstract: An improved diesel engine water pump includes three main features that aid in extending the maintenance free life of the pump. The impeller shaft is carried by tapered roller shaft support bearings of which the impeller bearing has a floating outer race that is urged axially by a preload spring to provide a prescribed axial preload that maintains concentricity of the shaft with the axis and prolongs bearing life. An improved oil seal combines an oil slinger, a stationary deflector and a lip oil seal with a return passage to the engine to more effectively limit oil leakage from the pump. An improved water seal includes pressurized water jets fed from the pump volute that flush wear particles from the water seal surface and increase water seal life. Further details of these features are also disclosed.

Abstract: A circulating lubrication system for a centrifugal pump, or other rotating equipment utilizing an oil sump, is disclosed. The lubrication system includes an external reservoir located distant from the main lubrication chamber, so that lubricating fluid from the main misting chamber is forced out of the main chamber, cooled and cleaned (i.e. filtered) in the external reservoir, and thereafter fed back into the main lubricating chamber. In such a manner, the lubrication system maintains substantially clean, cool, and moisture free lubricating fluid in the main misting chamber and reduces the required downtime of the device. Thus, the life span of the device is lengthened while at the same time production is increased.

Abstract: A turbine includes, in an exemplary embodiment, an outer housing, a turbine shaft rotatably supported in the outer housing, and a plurality of turbine stages located along the turbine shaft. Each turbine stage includes a diaphragm attached to the casing, a rotor having a plurality of buckets and a bucket cover fixedly attached to the turbine shaft, and a packing ring mounted in a first circumferentially extending groove in said diaphragm. The packing ring includes a seal shroud and a sealing means and is positioned adjacent the turbine shaft. The seal shroud is fabricated from a first material having a first coefficient of expansion, and the is diaphragm fabricated from a second material having a second coefficient of expansion. The first and second materials are selected so that at a first temperature a gap between the turbine shaft and the diaphragm is larger than at a second higher temperature.

Abstract: A dampening system for a miniature high-speed turbojet engine provides single or multiple resilient mounting which includes a seal with an at least partially encapsulated spring for forward and aft bearings which mount a rotor shaft. The self-induced first engine order of the rotating rotor shaft is transmitted through the forward and aft bearing and is then absorbed in the resilient mountings. Dependable seal and vibration reduction is thereby provided irrespective of long term storage.

Abstract: A turbocharger rotor has a turbine wheel and shaft, a compressor wheel and adapter and a separate thrust runner clamped together by a fastener rod. The adapter is piloted on the shaft and the thrust runner is piloted on the adapter, which has annular ends engaging the shaft and adapter for torque transmission between the turbine and compressor wheels. An anti-rotation coupling relates the phase angles of the shaft with the adapter and the thrust runner during assembly. Opposed radial thrust faces on the thrust runner and adapter are disposed at opposite ends of a compressor bearing journal on the adapter to allow placement of mating bearings on a single element of a turbocharger housing. Advantages include simplification of manufacture and assembly of the rotor in a turbocharger housing.

Abstract: A relative movement of a fan 1 toward a motor 2, which is one of the relative movements of the fan 1 with respect to a rotating shaft 23, is restricted by an inner ring 221 of a radial bearing 22. Due to this, the relative movement of the fan 1 toward the motor 2 is restricted by the inner ring 221 when the joining force between the fan 1 and the rotary shaft 23 is decreased, so that the contact between the fan 1 and the housing 21 can be prevented. Moreover, as the inner ring 221 rotates together with the rotating shaft 23, a rotational force is transferred from the inner ring 221 to the fan 1 in a state in which the relative movement of the fan 1 toward the motor 2 is restricted by the inner ring 221.

Abstract: A bushing and washer forming a bearing assembly at the outer radial end of a stator vane, the outer bearing assembly, and the bearing assembly at the inner radial end of the stator vane, the inner bearing assembly, that facilitate durability, effectiveness and reduced cost. Both the inner and outer bearing assemblies are designed to rotate relative to the vane shaft and the respective mating shroud or case to even out the wear around the circumference of the bushing. When a rotating bushing is used, a flange on the bushing is designed to be positioned on the inside of the case, so that a pressure differential across the case applies a force to the vane to move it outwardly against the flange and the flange against the case, thereby minimizing air leakage.

Abstract: An arrangement for the releasable fastening of struts serving as bearing carriers for the rotor of an aeronautical gas turbine to the casing structure of the aeronautical gas turbine, with stop faces, arranged in the circumferential direction and in the axial direction of the rotor of the gas turbine, at that end of the strut which faces away and acts as a connection head, the stop faces being assigned matching stop faces on the casing structure of the aeronautical gas turbine, and with a screw connection, inclined at an angle, between the casing structure and the connection head of the strut, for the purpose of the positive and non-positive retention of the strut on the casing structure.

Abstract: An improved diesel engine water pump includes three main features that aid in extending the maintenance-free life of the pump. The impeller shaft is carried by tapered roller shaft support bearings of which the impeller bearing has a floating outer race that is urged axially by a preload spring to provide a prescribed axial preload that maintains concentricity of the shaft with the axis and prolongs bearing life. An improved oil seal combines an oil slinger, a stationary deflector and a lip oil seal with a return passage to the engine to more effectively limit oil leakage from the pump. An improved water seal includes pressurized water jets fed from the pump volute that flush wear particles from the water seal surface and increase water seal life. Further details of these features are also disclosed.

Abstract: The complex mechanical gear trains and lubrication systems of conventional engine configurations are eliminated by using combinations of hydrodynamic air foil bearings, hydrodynamic solid geometry carbon seals/bearings, magnetic bearings, and electrical starter/generators that can also act as bearings to support the high speed shafts of gas turbine engines. The various bearing types and the starter/generators are arranged in such a way as to share peak loads experienced by the engine shaft during maximum aircraft maneuvers. This results in a minimal bearing and engine size.

Abstract: A method of minimizing oil consumption in a gas turbine engine, by avoiding reliance on air intake into the engine oil circuit for bearing chamber oil sealing purposes. The engine oil circuit has bearing chambers with hydropad seals between the shaft and bearing chamber. During engine operation the ring rotates to cast oil radially outwardly from the shaft axis toward the outer periphery of the bearing chamber under centrifugal force, independent of any gas pressure differential across the sealing surfaces of the hydropad seal.

Abstract: A wind turbine with a rotor, a nacelle and a tower. The nacelle comprises a planetary gear (4) with a planetary holder (5), on which the hub (6) of the rotor is rigidly secured, and which can be connected to the shaft of an electric generator. The planetary gear (4) comprises a ring gear (7) fixedly mounted on an engine frame (9) in the nacelle or on the member (8) rigidly connected to said frame. The planetary wheels (17a, 17b) of the planetary gear can run around a centrally arranged sun wheel (14) while engaging the latter. The sun wheel is optionally connected to a parallel gear (30). The planetary holder (5) is rotatably mounted in the ring gear (7) by means of at least two sets (17) of planetary twin wheels (17a, 17b). Each set of planetary twin wheels is mounted on a bogie shaft (19) on the planetary holder.

Abstract: An antifriction bearing unit comprises a rotating shaft, an outer ring, and rolling members. The rotating shaft comprises a large-diameter shaft portion serving as an inner ring and a small-diameter shaft portion, which is hollow and has a fitting portion of increased diameter at one end thereof. The large-diameter shaft portion has an end portion fitted and fixed in the fitting portion of the small-diameter shaft portion. The fitting portion has an outward flange integral with an end thereof. The outer ring is fixedly provided with a seal member having lips slidable in contact with the flange and the outer peripheral surface of the large-diameter shaft portion, respectively.

Abstract: A system is provided for changing the critical speed of a shaft that includes: a first shaft supported for relative rotational movement with respect to a stationary structure, a forward bearing disposed at the forward end of the shaft, an aft bearing disposed at the aft end of the shaft, at least one active bearing disposed between the forward bearing and the aft bearing, and means for changing the support stiffness of the active bearing.

Abstract: A draining and cooling system for gas turbine cushions where the above-mentioned gas turbine has its own drain unit (11), which consists of two essentially concentric rings connected to each other by means of a number of spokes (12, 13). In the draining system described, the lubricating and cooling oil is fed into the gas turbine's drain unit (11) by means of at least a first pipe (14), located inside one of the spokes (12) and is drained by means of at least a second pipe (20), located inside one of the spokes (13).

Abstract: A turbomachine has a turborotor made up of a shaft and a rotor disk, and an electric machine having an electric rotor. The rotor disk is arranged at one end of the shaft, in overhung manner, and the electric rotor is connected with the shaft of the turborotor. The electric rotor is arranged on the other end of the shaft, also in overhung manner, and the shaft is mounted on shaft bearings in a bearing housing that thermally separates the shaft bearings from the electric machine.

Abstract: A casing (12) for a steam turbine section has a housing (14) installed therein for a bearing supporting a rotor for buckets. A housing support structure (10) includes a pair of horizontally extending struts (T1-T2) extending from a side (18) of the casing to the housing and a second pair of struts (T3, not shown) extending from the opposite side of the casing to the housing. The struts are in fluid communication with the interior of the housing and the atmosphere and both support the housing within the casing and vent the interior of the housing. Vertical struts (T4-T6) also extend between the casing and the housing. A foundation plate (20) is installed beneath the casing, and a pair of gibs (28) are installed on opposite sides of the casing along the longitudinal centerline thereof to strengthen the casing and prevent tilting of components within the casing when a vacuum within the casing is present.

Abstract: The invention recites a power turbine assembly including a turbine rotor and a plurality of turbine blades mounted to said rotor and adapted to rotate said rotor in response to a flow of hot gas over said blades. A support structure having a journal bearing and at least one other bearing supports said rotor for rotation, said journal bearing having a proximal end and a distal end with respect to said turbine blades. A supply of lubricant communicates with said journal bearing to provide lubricant between said rotor and an inner surface of said journal bearing, said lubricant damping rotational frequencies of said rotor and creating a temperature gradient from greater than about 1000° F. at said blades to less than about 350° F. at said distal end.

Abstract: A lubrication system for equipment (e.g. centrifugal pump) employing a rotating shaft and corresponding support bearings is disclosed. The lubrication system includes a lubricant dispenser having a plurality of blades or dispensing members pivotally attached thereto, the dispenser affixed to the shaft for rotation therewith. Centrifugal force created by rotation of the shaft to which the dispensing blades are attached causes the blades to extend radially outward from the shaft center during operation so as to dispense the lubricant throughout a lubricating or misting chamber in order to lubricate the adjacent bearings. The system is also advantageous in that the blades are permitted to pivot or flap downward toward the shaft in either direction so that the dispenser may be more easily inserted into the misting chamber during manufacturing of the device or replacement of the lubricating system.

Abstract: A vertical turbine pump which operates with its inlet sub-merged in a body of liquid to be pumped employs an impeller provided with two or three equiangularly spaced vanes and a diffuser section provided with three equiangularly spaced stationary vanes. A vertical turbine pump incorporating such a combination of impeller and diffuser vanes exhibits favorable hydraulic efficiency and smooth operation and can effectively handle liquids with entrained solids. The pump bowl bearings are part of a cartridge which is readily removed and installed through the upstream end of the pump to facilitate servicing in the field.