Abstract: The invention relates to the bearing for an adjustable rotor blade on the rotor hub of a wind energy plant, with a roller bearing as the pivot bearing for the positioning drive, which can transfer high axial forces and large twisting moments with low relative movements between the bearing halves. One bearing half comprises a bearing ring with two positive-fit rows of roller bodies, radially offset from each other and the other bearing half comprises a bearing ring engaging with the above with a U-shaped section. The bearing ring for the rotor blade, forming the other bearing half, comprises two rings (10, 12) of varying diameter, which are independently fixed to the rotor blade (3). The circular root of the hollow rotor blade is split into two sub-shells (3a, 3b) and each sub-shell is fixed to one of the both rings (10, 12), of the one bearing ring.

Abstract: A fan having stable pre-loading device includes a stator, at least one bearing, a rotor having a blade structure, a shaft and a rigid spacer. Among these, the bearing is formed in the space of the stator. One terminal of the shaft is coupled to the stator. The elastic device is formed on the bearing. The rigid spacer is formed on and thus compresses the elastic device. Another terminal of the shaft passing the rigid spacer as well as the elastic device is coupled to the inner ring of the bearing.

Abstract: To provide a water pump capable of preventing coolant leaked from a shaft sealing member from invading a bearing by a simple construction, a water pump has an outer ring of a bearing attached to an inner peripheral face of a pulley, an inner ring of the bearing attached to an outer peripheral face of a cylindrical portion of a housing and a shaft sealing member attached to an inner peripheral face of the cylindrical portion.

Abstract: A fan having stable pre-loading device includes a stator, at least one bearing, a rotor having a blade structure, a shift and a rigid spacer. Among these, the bearing is formed in the space of the stator. One terminal of the shaft is coupled to the stator. The elastic device is formed on the bearing. The rigid spacer is formed on and thus compresses the elastic device. Another terminal of the shaft passing the rigid spacer as well as the elastic device is coupled to the inner ring of the bearing.

Abstract: A turbine installation comprising a turbine in combination with an electrical closed-loop control system. The turbine is disposed in a flow of water for producing electrical energy. The turbine includes a hollow hub and a plurality of runner blades pivotally connected to a hollow hub. Each blade comprises a hydrofoil being bounded by an inner surface and a distal outer surface, a leading edge and a trailing edge separated by a water directing surface. The blades are adjustable in pitch from a maximum pitch position in which an inner portion of the water directing surface extends substantially in a direction of the water flow, to a minimum pitch position in which an outer portion of the water directing surface is substantially perpendicular to the water flow. The hollow hub has spaced apart inner and outer surfaces and a hub longitudinal axis. Each blade is pivotally connected to the hub about a rotational axis.

Abstract: A bearing assembly for a gas turbine engine rotor includes a damper bearing configured to support the rotor, a bearing centering sub-assembly configured to position the damper bearing relative to the rotor, and a retainer. The damper bearing includes a frame that defines a bearing bore, an inner race, and an outer race, said inner and outer races within said bearing bore. The bearing centering apparatus sub-assembly includes a plurality of first springs and a plurality of second springs. The retainer is coupled to the bearing housing and is configured to maintain an axial position of the bearing outer race with respect to the support structure.

Abstract: A buffer pad is provided for use in an electric fan that has a blade assembly and a spindle extending from the blade assembly and rotatably supported in a bearing. The spindle further has a distal end extending beyond the bearing. The inventive buffer pad includes a wear-resistant piece for abutting the distal end of the spindle, and a resilient body adapted to be held in place within the electric fan for resiliently supporting the wear-resistant piece. The buffer pad can absorb vibrations generated by the rotary blade assembly.

Abstract: A rotor assembly for a gas turbine engine includes a bearing assembly that reduces dynamic loads to a support frame and static bending to the rotor assembly during periods of rotor unbalance. The rotor assembly includes a rotor shaft coupled to a fan and supported longitudinally with a plurality of bearing assemblies on a support frame. A number two bearing assembly includes a paired race, a rolling element, and a mounting race. The mounting race includes a spherical face and is secured to the bearing assembly with a retainer that plastically fails at a pre-determined moment load.

Abstract: A rotor assembly for a gas turbine engine including a bearing centering sub-assembly that facilitates reduces an effect of radial forces transmitted to a bearing assembly is described. The bearing assembly supports a rotor shaft with a rolling element positioned radially inward from an outer race. The bearing centering sub-assembly is coupled to the outer race and includes a plurality of first springs and a plurality of second springs extending circumferentially in rows. Each first springs is coupled between a second spring and the outer race such that each first spring is radially aligned with respect to each second spring.

Abstract: A rotor assembly for a gas turbine engine including a bearing assembly and a damper sub-assembly that facilitate reducing dynamic motion to the rotor assembly is described. The bearing assembly includes rolling elements positioned between a paired race. The rotor assembly includes a rotor shaft supported by the bearing assembly. The damper sub-assembly is radially outward from the bearing assembly adjacent a sump housing, and includes a damper insert. A predetermined preload force is applied to the rolling elements. An outer race of the bearing assembly distorts to substantially match a distortion pattern of the damper insert.

Abstract: A gas turbine engine includes a lubrication system that supplies oil through a plurality of circumferential grooves and radial grooves to a bearing assembly. The grooves extend within an inner surface of a first rotor shaft sized to fit in an interference fit around a main rotor shaft. The circumferential grooves are spaced circumferentially around the inner surface of the first rotor shaft and are substantially perpendicular to the radial grooves. The radial grooves are in flow communication with a plurality of scoops extending between an outer and inner surface of the first rotor shaft, and with the bearing assembly.

Abstract: A turbine, adaptable to improve the survivability of fish present in water flowing therethrough, includes a hub and associated runner blades. Each blade comprises an inner edge and a distal outer edge, a leading edge and a trailing edge separated by a water directing surface. Each blade is rotatable relative to the hub about a blade rotational axis. The turbine is provided with a gap shielding device designed to shield a gap formed between the hub and the blade inner edge as the blade is rotated about its axis. The gap shielding device may comprise a plurality of independently biased pins, a plurality of fluid jets, a plurality of flexible members, a fluid-filled boot, and combinations thereof.

Abstract: A sealing arrangement between two radially adjoining components of an assembly that rotates during operation, in particular between the rotor and the rotating blade of a gas turbine component includes a sealing element in a depression of an inner one of the two components at the boundary surface to the outer one of the two components. The sealing element is designed in such a way that it does not or does only slightly project beyond the depression during assembly and that, during rotation of the assembly, the centrifugal force acting on it produces a sealing joint between the components. The present sealing arrangement permits an easy installation of rotating blades to the rotor of a gas turbine.

Abstract: An adjustable steady bearing support assembly and method provides support for a bearing in rotational contact with a shaft in a vessel such as a mixing vessel. The assembly and method allows axial movement of the bearing along the shaft in response to changes in the radial dimensions of the vessel while providing radial support of the bearing. The assembly employs strut assemblies having pivotally mounted strut pairs with an included angle between the struts in each pair to resist torsional forces on the a bearing.

Abstract: An electric motor having a housing, having an armature, having an armature shaft supported in two slide bearings, where one of the slide bearings axially displaceably receives the armature shaft and the other slide bearing limits an axial displaceability of the armature shaft by the disposition of a stop disk between a slide bearing bush of the slide bearing and the armature, by the disposition of an axial stop, in the form of a stop ring pressed over one end of the armature shaft. The armature shaft end protrudes out of the housing and is intended for carrying and driving a fan wheel that has a hub which is located adjacent the particular a slide bearing that receives only radial forces.

Abstract: A footstep bearing for an impeller shaft of a container stirring mechanism is described. The footstep bearing has at least one shaft butt end (1) that is mounted, in particular, on the wall (2) of the container (16), and an impeller shaft (9) with a gap (13) in the region of the engagement between shaft butt end (1) and impeller shaft (9). In the region of the gap (13), the shaft butt end (1) and/or the impeller shaft (9) are/is provided on their surface with sliding elements on which the opposite surface of the impeller shaft (9) and/or the shaft butt end (1) slide and the shaft butt end (1) has means (11) for the passage of a flushing fluid (3) through the gap (13) between impeller shaft (9) and shaft butt end (1).

Abstract: A turbine disposed in a water passageway includes a hub and associated runner blades. Each blade comprises an inner edge and a distal outer edge, a leading edge and a trailing edge separated by a water directing surface. Each blade is rotatable relative to the hub about a blade rotational axis. The water passageway includes a spherically-shaped discharge ring that conforms to the outer edges of the blades to improve certain turbine parameters such as cavitation, efficiency, flow disturbance, and fish survivability. The turbine hub may also include a spherically-shaped outer surface in a region swept by the inner edges of the blades when the blades are rotated from maximum to minimum pitch, as well as seals attached to the inner edges of the blades. The hub may also be associated with blades in which the chord is reduced in the root region of the blade.

Abstract: An improved structure of a radiating fan comprises a blade seat, an axle center and a bearing. The central portion of the blade seat is installed with the axle center made of precision ceramic material, the outer peripheral surface of the axle center is covered by a hollow bearing made of precision ceramic material. Since the axle center and the bearing made of precision ceramic material have the advantages of long lifetime, low noise, and without using lubricating oil. Thus it is better than the axle center made of stainless steel and the oil bearing made of copper.

Abstract: A molten metal impeller having a base portion including a circumferential notch. The notch having a generally radial wall and a generally axial wall, at least one of the radial or axial walls including a plurality of grooves. A ceramic bearing ring is cemented into the notch.

Abstract: A turbine brush seal protection device includes an annular substrate having an outer periphery and defining a slot open at the outer periphery. The slot is for receiving a portion of an annular brush seal of a gas turbine subassembly during installation of a gas turbine and such that the annular substrate at least partially covers the annular brush seal of the gas turbine subassembly. The annular substrate at the outer periphery and within the slot thereof is removably mounted to a stationary portion of the gas turbine subassembly.

Abstract: A fan suitable for use in a refrigerator includes a motor frame having a bracket insertion hole, a bracket including a cylindrical portion fitted into the bracket insertion hole so as to project from the motor frame and a bearing, a stator including a stator core, a stator coil wound on the stator core, and a molded layer molded from a synthetic resin so as to cover the stator core and the stator coil, the stator being disposed on an outer periphery of the cylindrical portion projecting from the bracket insertion hole so as to be supported by the cylindrical portion and the motor frame, a rotor including a rotational shaft inserted into the cylindrical portion so as to be rotatably mounted via the bearing on the bracket and having both ends, a rotor yoke disposed on one end of the shaft opposite to the motor frame so as to cover the stator, and a rotor magnet disposed on an inner circumferential face of the rotor yoke so as to be opposed to an outer circumferential face of the stator core with a gap between t

Abstract: A turbine installation having reduced inner and outer gaps comprises a water passageway and a turbine runner disposed in the passageway downstream of a discharge ring. The turbine runner includes a hollow hub having spaced apart inner and outer surfaces and a longitudinal axis and a plurality of runner blades. Each blade comprises a hydrofoil having an inner edge and a distal outer edge, a leading edge and a trailing edge separated by a water directing surface. Each blade is pivotally connected to the hub about a rotational axis extending in a direction generally perpendicular to the longitudinal axis so that its inner edge is proximate the hub. Each blade is rotatable between a maximum pitch position and a minimum pitch position. The discharge ring has a spherical configuration cooperable with the outer edge of each of the blades to reduce an outer gap formed between the outer edge of each of the blades and the passageway.

Abstract: The sealing ring seals between relatively rotating and vibrating machine parts such as parts of an aircraft propeller, and has several sealing lands. The shape and configuration of the lands are selected so that natural vibration frequencies of the ring or lands are not vibration frequencies to which the ring is subject in use.

Abstract: An agitator includes a drive motor having a shaft projecting through an axial end of a housing and having connected thereto a propeller boss. The propeller boss and housing define a circumferential gap spanned by a circumferentially extending radially outermost gap covering and sealing portion of a deflector ring. The deflector ring includes a radially innermost ring mounting portion located in the circumferential gap. The deflector ring is preferably made of elastomeric material and an outermost circumferential surface of the deflector ring is exteriorly convexly curved in the form of an aerofoil converging axially toward ends of sealing lips of the deflector ring gap covering and sealing portion.

Abstract: A fan assembly (10) includes first and second housing sections (70, 72) which, when mated by a first set of fasteners, define a plurality of circumferentially spaced openings (162) that lead to an internal housing chamber (82). The fan assembly (10) also includes a plurality of blade units (140), each of which includes an integral support stem (142) having a journal portion (148) rotatably mounted within a respective one of the openings (162), an enlarged flange portion (144) and a radial post portion (138) rotatably supported by a hub member (106) within the internal chamber (82). Each blade unit (140) preferably has a thrust bearing (156), bushing sleeve (158) and fan blade (152) integrated with the support stem (142), with the fan blade (152) being preferably molded to the support stem (142) following positioning of the thrust bearing (156) and bushing sleeve (158) to form an integral component.

Abstract: An actuation system which includes apparatus for transferring control signals for varying the blade pitch from a non-rotating member to a rotating member of a gas turbine engine is described. In one embodiment, the engine includes a main disk containing a row of blades, and the disk is coupled to a main shaft which rotates about the engine axis. An actuating disk, or cone, rotates with the main disk, and the torque required to rotate the actuating cone is transmitted through ball splines attached to the main shaft. The ball splines allow transmission of torque between the disk and the cone and at the same time enable the disk and the cone to move axially relative to each other without binding. The actuating cone is supported at one end by the ball splines and at its other end by ball thrust bearings. The ball thrust bearings are pre-loaded to enable the bearings to withstand axial loads in opposite directions.

Abstract: A hollow portion is provided on the core of an inner shaft (2) to form an oil feed port (3), a plurality of oil feed holes (4) which are connected with both of the outer peripheral face of the inner shaft (2) within a range (L) of the bearing surface of the inner shaft (2) and the oil feed port (3) are radially provided in a line , and axial oil grooves (5) each of which includes an inner shaft surface side opening portion (4a) of the oil feed hole (4) are provided on the outer peripheral face of the inner shaft to form a contra-rotating bearing device for a contra-rotating propeller which causes the inner shaft (2) and an outer shaft (2) to contra-rotate mutually. In place of the oil grooves, a plurality of concave-convex portions may be formed in the axial direction of a contra-rotating bearing on the inner peripheral face of the bearing and circular portions may be provided on both axial ends of the concavo-convex portions to form the contra-rotating bearing device for a contra-rotating propeller.

Abstract: A Kaplan turbine or similar hydraulic machine has a hub body (1) fixed to the turbine shaft with radial blades attached to the hub body. The blades are fitted with oil lubricated bearings in the hub body. A sealing arrangement for the oil system has first (60) and second (61) circumferential sealing members with a circumferential space (65) between the first and second sealing members (60, 61). High pressure water from a water source is directed into the circumferential space (65) via a connecting channel (64) to block the lubricating oil from leaking into the working fluid.

Abstract: An impeller has a plurality of rotating passageways which can be defined between adjacent blades, the blades having a curved root portion and able to pivot across a part spherical hub to maintain a fine line contact. The passageways have a convergence to improve the efficiency of the impeller. The hub can be split into two relatively rotating portions, with the blades attached to each portion to provide an efficient means to vary the pitch of the blades.

Abstract: A propeller blade retention assembly for use with a propeller having a hub rotatable about a propeller axis, is disclosed. The assembly includes a blade receiver for mounting the blade to the hub and an internal surface of a hub arm for interfacing the receiver with the hub. The receiver is positioned in the hub arm and is non-integral with the blade and the hub arm internal surface. A retention mechanism is used for retaining the blade receiver to the hub arm while allowing relative rotatable motion therebetween. A preload device is provided for preloading the retention mechanism prior to centrifugal loading during propeller blade operation. The blade is separable from the blade receiver without disturbing the operability of the retention mechanism.

Abstract: A turbine, disposed in water flowing therethrough, includes a hub and associated runner blades. Each blade comprises an inner surface and a distal outer surface, a leading edge and a trailing edge separated by a water directing surface. Each blade is rotatable relative to the hub about a blade rotational axis. The hub includes a spherically-shaped outer surface in a region of the hub swept by the inner surface of the blades when the blades are rotated from maximum to minimum pitch. The hub may also be associated with blades in which the chord is reduced in the root region of the blade. The turbine may also include seals attached to the blade inner surface and an essentially spherically-shaped discharge ring to improve certain turbine parameters such as cavitation, efficiency, flow disturbance, and fish survivability.

Abstract: A system and device for pumping molten metal that reduces bearing member fractures comprises a pump having a pump chamber including a first bearing surface, a rotor having a second bearing surface that aligns with the first bearing surface. The second bearing surface is formed by a plurality of spaced bearing pins attached to the rotor. Each bearing pin has an outer surface preferably substantially flush with the outer perimeter of the rotor. The pins are comprised of a heat resistent material that is harder than the material comprising the rotor.

Abstract: A turbine, adaptable to improve the survivability of fish present in water flowing therethrough, includes a hub and associated runner blades. Each blade comprises an inner edge and a distal outer edge, a leading edge and a trailing edge separated by a water directing surface. Each blade is rotatable relative to the hub about a blade rotational axis. The turbine is provided with features designed to shield a gap formed between the hub and the blade inner edge as the blade is rotated about its axis.

Abstract: A centrifugal blood pump assembly according to one aspect of the invention includes a housing, an impeller adapted to rotate within the housing for feeding blood, an impeller position control device, and an impeller rotation torque generating device. The impeller rotates without contacting the inner surface of the housing when the position control device and torque generating device are operative. Even when the position control device is inoperative, operation of the torque generating device enables rotation of the impeller while a blood flowpath is defined between the surface of the impeller facing the torque generating device and the inner surface of the housing. A centrifugal blood pump assembly according to another aspect of the invention involves a pump including a housing having blood inlet and outlet ports and an impeller adapted to rotate within the housing for feeding blood.

Abstract: A liquid pump in which a perfect seal is achieved between a liquid and the atmosphere without the use of magnets includes a driving unit coupled to external power for being rotated thereby, a shaft installed obliquely with respect to the axial direction of the driving unit and having one end thereof rotatably supported on the driving unit, an impeller, rotatably supported on a housing so as to rotate in coaxial relation to the driving unit, for rotatably supporting the other end of the shaft and impelling a liquid by being rotated, and a bellows provided between the shaft and the housing for effecting sealing liquid-tightly between the shaft and the housing on the side of the impeller.

Abstract: In a vertical-axis waterpower machine, the shaft is mounted in a bearing-supporting star. It has a track ring for a supporting bearing. Supporting-bearing segments are supported via adjusting elements on a supporting ring firmly connected to the bearing-supporting star. To simplify the construction and improve the accessibility of the adjusting elements, the latter are designed as rocking levers. The rocking levers act as single-armed or double-armed levers and are elastic in the lever longitudinal direction.

Abstract: A safety device on an aft seal system equipped with at least two gaskets for a ship's propeller shaft, which propeller shaft is sealed with respect to the outside water and with respect to a lubricant chamber, and on which a ring-shaped chamber is reserved between each two gaskets, to which chamber are connected a feed line for compressed air and a discharge channel which can be emptied by means of a solenoid valve which opens and closes periodically. The pressure in the ring-shaped chamber is kept always slightly lower than the respective outside water pressure and the lubricant pressure by means of a pressure regulation mechanism.

Abstract: A seal arrangement for controlling any large bearing clearance in the vicinity of a propeller shaft, such as for a propeller drive system for ships with two concentric propeller shafts rotating in opposite directions, has a housing ring for supporting the sealing lips and a supporting ring for supporting the housing ring and defining a clearance therebetween. This clearance can be sealed, and maintained by means of elastic ring walls disposed between and interconnecting the housing to the supporting ring, so that compensation can be achieved for changes in the clearance during rotation of the propeller shaft.

Abstract: The invention relates to a rotating machine part having, in particular, a flat housing or base with an essentially cylindrical outer wall or with symmetrically distributed projections which are arranged in particular in the form of a star, in particular a rotor (1) of a cycloid propeller, the cylinder axis or rotor axis being the same as the rotation axis and the machine part or housing rotating in an atmosphere or a medium which is able to transmit heat to a sufficient extent to produce a required cooling effect on the machine part or housing or in its interior.

Abstract: A ram air turbine power system is provided with a deployable ram air turbine mounted in-line with a power supply unit such as an electrical generator and/or an hydraulic pump. The ram air turbine includes a turbine shaft supported for rotation by bearings within a generator housing, wherein a rear end of the turbine shaft and a generator shaft are supported by a common bearing, and further wherein the forwards ends of the turbine and generator shafts are supported by a pair of bearings separated by a resilient bearing mount. In addition, the in-line ram air turbine and related power supply unit are supported from a hollow strut with hydraulic and electrical lines and related mechanical linkages extending therethrough.

Abstract: A seal arrangement for controlling any large bearing clearance in the vicinity of a propeller shaft, such as for a propeller drive system for ships with two concentric propeller shafts rotating in opposite directions. The seal arrangement has a housing ring for supporting the sealing lips and a supporting ring for supporting the housing ring and defining a clearance therebetween. This clearance can be sealed and maintained by using elastic ring walls disposed between and interconnecting the housing to the supporting ring, so that compensation can be achieved for changes in the clearance during rotation of the propeller shaft.

Abstract: A ship, in particular a deep-draft vessel configured for travel on the oceans or great lakes, can have a hull with two concentrically rotating propeller shafts passing through the hull, and rotate in opposite directions to one another. The ship will generally have seals between the propeller shafts, and between the propeller shafts and the hull. In general, it is necessary to lubricate and cool the sealing surfaces of the individual seals, so that the useful life of the individual seals is prolonged, and the risk of failure of the seals is reduced. For the effective lubrication of highly-stressed seals of propeller drive systems for ships with two concentric propellers rotating in opposite directions, a forced feed lubrication system with circulating lubricating oil has been found to be advantageous.

Abstract: A seal arrangement for controlling any large bearing clearance in the vicinity of a propeller shaft, such as for a propeller drive system for ships with two concentric propeller shafts rotating in opposite directions, has a housing ring for supporting the sealing lips and a supporting ring for supporting the housing ring and defining a clearance therebetween. This clearance can be sealed, and maintained by using elastic ring walls disposed between and interconnecting the housing to the supporting ring, so that compensation can be achieved for changes in the clearance during rotation of the propeller shaft.

Abstract: The invention employs the principle of the prior art for cooling a heated body by means of so-called heat pipes, with seal devices for rotating shafts, in particular for a ship's propeller shaft. According to this principle, an externally closed chamber extending in the longitudinal direction and filled with a liquid working fluid extends on one end into the body to be cooled, and on the other end into a cold medium, whereby a constant circulation takes place, so that the work fluid is evaporated in the hot portion of the chamber, the vapor flows into the cold portion of the chamber, condenses there, and the condensate is returned to the hot portion by way of a capillary structure (FIG. 1 ).

Abstract: A household appliance (D) has a housing (H). A fan (A) located inside the housing circulates air through the appliance. The fan is attached to a motor (M) located outside the housing. The motor has a shaft (S) extending through an opening (O) in a sidewall (W) of the housing and the fan is connected to the inner end of the shaft. A hub ring (9) is used for mounting the motor to the housing and includes a flange (13) having tabs (17) which engage a hub U of the motor to interlock the motor/fan assembly with the hub ring. The housing has a projection (3) on the outside of the housing through which the shaft extends and the hub ring has a sleeve 11 received in the projection to align and support the motor/fan assembly.

Abstract: A contrarotating propeller type propulsion system having first and second output rotary cylinders which are carried individually on an outside support cylinder fixedly secured to a first support structure, the first output rotary cylinder being borne on the outer peripheral surface of the first support cylinder through bearings and the second output rotary cylinder borne on the inner peripheral surface of the first support cylinder through bearings. The first and second output rotary cylinders serve to support the first and second contrarotating propellers, respectively. The first and second output rotary cylinders are supported on the first support cylinder at two axially spaced points. The driving shaft is borne on a second support cylinder fixedly secured to the support structure and surrounded by the first support cylinder.

Abstract: Drag produced by cold, viscous oil, interacting with the gear meshes of a gear drive (8) connected to a ram air turbine (2) of an aircraft (1), is controlled to allow proper start-up of the ram air turbine. The lubricating oil is isolated from the gear meshes in remote sumps (11, 12) when the turbine is located in the stowed, inoperative position. An oil metering orifice controls the oil flow from the remote sumps to gearbox sumps with movement of the turbine from the stowed position (A) to the deployed position (B), so as to delay the application of cold, viscous coil to the gear meshes until after start-up of the turbine. This avoids excessive start times and failure to start from the high drag caused by cold, viscous oil on the gear meshes.

Abstract: A fan assembly has variable pitch blades adjustable from outside the assembly while the fan is operating so as to alter the volume and direction of the induced airflow. The fan blades have an airfoil configuration such that air is moved by the fan in either direction with equal inefficiency. The airfoil configuration of the blades is neutral and the blades are straight. The fan assembly is lubricated by a pick-up non-rotatably mounted in a reservoir formed by the pulley hub and blade hub. The pick-up feeds lubrication directly to the bearing assemblies on which the spider and pulley hub are mounted.The neutral airfoil shape of the blade extends along the blade, and the blade has a blunt leading edge and a tapered trailing edge.

Abstract: A centrifugal classifier comprising a housing, which is provided with inlets for material to be classified and classifying air or with an inlet for material to be classified and classifying air and with outlets for fines and for coarses, and at least one rotor, which essentially consists of an annular series of blades and is movably mounted in the housing. The rotor is movably mounted in the housing by at least one bearing, which is adapted to be purged by a fluid and which serves also as a seal between the rotor or rotor shaft and the housing.

Abstract: A fan assembly has variable pitch blades adjustable from outside the assembly while the fan is operating so as to alter the volume and direction of the induced airflow. The fan blades have an airfoil configuration such that air is moved by a fan in either direction with equal efficiency. The fan assembly includes a non-rotating secondary shaft axially moveable in a main shaft. The secondary shaft has a spider interconnected with the crank arms of the blade arms by a snugly fitted universal joint assembly. The airfoil configuration of the blades is neutral and the blades are straight. The fan assembly is lubricated by a pick-up non-rotatably mounted in a reservoir formed by the pulley hub and blade hub. The pick-up feeds lubrication directly to the bearing assemblies on which the spider and pulley hub are mounted.