Abstract: A bearing arrangement for a turbine rotor of a turbine is adapted to be mounted in a drill string and to be driven by the flow of drilling fluid. The bearing arrangement includes a turbine chamber surrounding the turbine rotor and having an inflow and an outflow, a stator on which the turbine rotor is rotatably mounted, and a cavity formed between the turbine rotor and the stator and accommodating at least one radial plain bearing and being separated from the turbine chamber by an axial plain bearing constructed as a bearing ring seal and by a conveyor screw which is disposed on the turbine rotor and operates to convey from the cavity to the turbine chamber.

Abstract: Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a stator assembly and a rotor assembly configured to operatively engage each other to form a first seal and a second seal; the first seal being provided by a hydrostatic seal having a seal face and a seal runner; and the second seal being provided by a back-up seal such that responsive to a failure of the first seal, the back-up seal maintains at least a portion of a pressure differential established by the first seal prior to the failure.

Abstract: A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.

Abstract: A turbine seal member for use in a gas turbine engine includes a turbine seal substrate having a gas-path side and a ceramic layer disposed on the gas-path side that includes a plurality of mechanical indentations.

Abstract: A leaf seal 10 in a rotary machine is located between a higher pressure region 14 and a lower pressure region 16 of the machine. Blow-down forces are greater on the lower pressure side 16 of the leaf seal 10 than on its higher pressure side 14, resulting in greater inward deflection of the leaves 20 on the lower pressure side of the seal than on its higher pressure side, leading in turn to greater wear of the leaves and the contacting rotor surface 44 on the lower pressure side 16 of the seal. To counteract this, the free ends 36 of the leaves 20 can be given a tapered profile 42 to gradually reduce the length of each leaf 20 over its width ‘w’ from its higher pressure side 14 to its lower pressure side 16, so that the leaves 20 are free to deflect under the blow-down forces by the amount of their reduction in length (a maximum of ‘x’), before they contact the rotor surface.

Abstract: A dynamic sealing system between two coaxial rotary shafts respectively comprising an inner shaft and an outer shaft. Connected to the inner shaft, the system comprises a sectorized annular assembly of wipers that are movable under the effect of centrifugal force, and an annular receptacle for liquid arranged in the inside surface of the outer shaft.

Abstract: An apparatus is provided and includes a first member with a flow diverting member extending from a surface thereof and a second member disposed proximate to the first member with a clearance gap area defined between a surface of the second member and a distal end of the flow diverting member such that a fluid path, along which fluid flows from an upstream section and through the clearance gap area, is formed between the surfaces of the first and second members. The second member is formed to define dual vortex chambers at the upstream section in which the fluid is directed to flow in vortex patterns prior to being permitted to flow through the clearance gap area.

Abstract: The static seal (30) includes a rotary seal body (32) comprising an annular base portion (34) which is drivingly mountable on a rotary component such as a shaft and an annular cantilever portion (40) connected at one end to the base portion (34). The seal (30) 5 further includes a rotary seal face (48) and circumferential weights (44) connected to the cantilever portion (40). The seal is configured to dilate under centrifugal force to provide a running clearance between the rotary seal face and a complementary static seal face with which the rotary seal face is in contact when the rotary seal body (28) is stationary. The rotary seal body is further configured so as to facilitate the breaking up of slurry which may set around the seal when the pump (10) of which the seal forms part is inoperative.

Abstract: A compressor of a gas turbine engine comprises blades 2, 4 provided on blade platforms 8, 12 of a rotor. Stator vanes 20 lie between the blades 2, 4 and are connected to a vane support structure 22. Sealing rings 38 are secured to the vane support structure 22 to restrict air flow into stator wells 36 on each side of the vane support structure 22. The sealing rings 38 are made from a flexible material so that they deflect on installation of the vane support structure 22 in a direction radially inwards between the adjacent blade platforms 8, 12.

Abstract: In one embodiment, a method for controlling seal clearance in a turbine engine includes positioning a seal ring within a turbine engine, the seal ring having an inner annular surface and an outer annular surface, the inner annular surface and the outer annular surface both being circular but non-concentric, rotating the seal ring within the engine until the seal ring is placed in an aligned orientation at which a center of a circle that defines the inner annular surface coincides with a centerline of the engine, and securing the seal ring while in the aligned orientation.

Abstract: A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body.

Abstract: A compressor for a gas turbine, in particular an aircraft gas turbine, has a rotor hub carrying rotor blades, a stator equipped with stator vanes, a shroud associated to the stator vanes, and an arrangement providing sealing between the shroud and rotor hub to prevent leakage. To achieve almost complete suppression of leakage air and, concurrently, simplification of design and manufacture, the sealing arrangement (20) between the shroud (8) and rotor hub (3) is formed by a discharge arrangement (23) for leakage air.

Abstract: Various systems and apparati as well as devices and structures are provided which may be used or incorporated into air handling systems (e.g. (air) ventilation systems and apparati) for the manipulation or control of air in an enclosure such as a building, a room of a structure such as a residence, and the like. Such air handling systems may for example include a blower wheel assembly, an airflow baffle element having a fresh air path side and an opposed exhaust air path side, for the transfer of heat from warm exhaust air (taken from inside an enclosure e.g. a building) to cooler exterior fresh air (drawn into the enclosure e.g. building). The air handling systems may not only exhaust stale interior air to the outside of an enclosure but as desired or necessary also intermingle a portion of such stale air with fresh air for delivery of the intermingled air back into the enclosure (during cold or warm weather).

Abstract: A pump has a one piece combined floating wear ring and liquid director that includes an upper ring portion received over an impeller hub and a curved lower portion that separates the pump impeller and suction chambers and directs liquid from the suction chamber inlet port to the impeller inlet.

Abstract: A vacuum pump includes a gas inlet, a quick-rotatable rotor connectable with a flange of a multi-chamber vacuum installation which flange has a plurality of suction openings separated by separation walls, and a gas path separating structure which is located in the gas inlet of the pump, dividing the gas inlet in suction regions, and which seals, together with the separation walls, chambers of the multi-chamber vacuum installation.

Abstract: There is provided a non-contact, passively suspended blood pump that includes (a) a housing; (b) a pump rotor within the housing, wherein the pump rotor has a first end and a second end, and an axis of rotation; (c) a first axial thrust bearing across a first axial gap, between the first end and the housing, that axially suspends the first end; (d) a second axial thrust bearing across a second axial gap, between the second end and the housing, that axially suspends the second end; (e) a first radial hydrodynamic bearing that radially suspends the first end; and (f) a second radial hydrodynamic bearing that radially suspends the second end. Determining pump differential pressure by monitoring rotor axial position allows automatic physiologic control.

Abstract: A cooled turbine shroud includes an arcuate flow path surface adapted to surround a row of rotating turbine blades, and an opposed interior surface; a forward overhang defining an axially-facing leading edge, an outwardly-extending forward wall and an outwardly-extending aft wall; opposed first and second sidewalls, wherein the forward and aft walls and the sidewalls define an open shroud plenum; at least one leading edge cooling hole extending from the shroud plenum to the leading edge; and at least one sidewall cooling hole extending from the plenum to one of the sidewalls. The flow path surface is free of cooling holes and may include a protective coating applied thereto.

Abstract: A turbo-type fluid machine comprises a mouth ring part provided between a shroud of an impeller and a pump casing and having a seal function. The mouth ring part comprises an impeller ring on a side of the shroud of the impeller and a casing ring provided on a side of a non-rotating body wall surface of the casing. The impeller ring is structured to have a stepped portion that is in the form of a staircase with at least two steps to be small in diameter toward a suction side of the impeller and large in diameter toward an outlet of the impeller. The casing ring is labyrinth-shaped to comprise a projection and a recess. A narrow clearance part having a narrow radial clearance is formed between the projection and the impeller ring. A flow passage spatial portion defining an enlarged portion of the narrow radial clearance is formed by the recess and the stepped portion of the impeller ring.

Abstract: A sealing arrangement for a compressor that compresses a gaseous mixture of air and fuel includes a pressurized air supply duct for supplying pressurized air into a leakage pathway defined between a compressor wheel and a housing of the compressor, which leakage pathway leads from the main gas flow path into a bearing area of the compressor, the pressurized air being supplied at a pressure sufficient to ensure that air and gaseous fuel cannot flow from the main gas flow path through the leakage pathway into the bearing area. A portion of the pressurized air flows into the bearing area, while the remainder of the air flows outwardly and is either fed back into the main gas flow path or is combined with air and gaseous fuel that leaks past an outer seal and is recirculated back to the compressor inlet.

Abstract: The present invention relates to a seal arrangement in which a substantially labyrinth type seal is utilised between a rotating component and a stationary component such as a housing. An edged fin of the seal arrangement incorporates a slot nozzle or a slot nozzle is associated with a fin in order that fluid flow through those slot nozzles either impinges upon opposed surfaces or at least narrows the available leakage gap width for greater sealing efficiency. Typically, several seal arrangements in accordance with the present invention and possibly in association with simple barrier fins are combined in an assembly to provide an appropriate acceptable combined operational sealing efficiency in a turbine engine.

Abstract: A centrifugal pump, the impeller (2) of the pump having one or more holes through the impeller adjacent to its hub. The hole or holes (7) are positioned between the vanes (3) of the impeller and closer to the hub than the periphery of the impeller. The total area of the holes is more than 0.4% of the area of the impeller, preferably 0.5-0.6% of the area of the impeller or more than 2% of the inlet area of the pump, preferably 2.5-5% of the inlet area. Preferably there is a cavity or a pit (8) at the back of the impeller.

Abstract: A diffuser is provided having a spaced apart shroud and backing plate. A diffuser vane is provided between the backing plate and shroud. The vane includes first and second sealing surfaces opposite from one another and adjacent to the backing plate and shroud. Leading and trailing surfaces are arranged opposite from one another and adjoin the first and second sealing surfaces. The first sealing surface includes a first protrusion extending therefrom approximate to the leading surface with a gap extending from the trailing surface to the first protrusion. The second surface includes a second protrusion extending therefrom proximate to the trailing surface with a second gap extending from the leading surface to the second protrusion. The surfaces provide four corners such that the protrusions are arranged on opposite corners from one another to create a pressure differential between the first and second sealing surfaces.

Abstract: In known delivery systems, a pump chamber and a revolving impeller in the pump chamber rotating about a pump axis, in which protuberances are provided inside the pump chamber on predetermined end walls, it is disadvantageous that the protuberances very and are complicated to make. In the delivery system of the invention, the friction in the pump chamber is reduced and the efficiency is improved by providing spacers, which space the impeller apart from the end walls of the pump chamber. That the protuberances are disposed in at least one ring around the pump axis.

Abstract: A rotating shaft seal assembly for a shaft supported for rotation within a housing includes a traction drive rotating a seal ring about the shaft at a speed different from the shaft. The seal ring supports a plurality of seal elements rotated at the speed different from the shaft. The reduced speed of the sealing elements and reduced pressure at each seal reduces the PV level allowing the use of known sealing materials in applications otherwise not within applicable PV levels.

Abstract: The present invention relates to a seal system for use in rotary machines. The seal system includes a first member and a second member forming an annulus, a high pressure region and a low pressure region in the annulus, and a liquid seal intermediate the first and second members and intermediate the high pressure region and the low pressure region for reducing gas leakage from the high pressure region to the low pressure region.

Abstract: A hydrodynamic sealing system for centrifugal systems comprising a double, asymmetric impeller attached to a rotary shaft, a fixed housing that surrounds the double impeller, a fluid inlet (5) in an axial direction and a fluid outlet in a radial direction with respect to the double impeller, with the double impeller defining a front side which receives the entry of fluid and a rear side close to the sealing zone of the shaft with the fixed housing. The double impeller is provided with means for taking the fluid from its front side to its rear side, so that when the double impeller rotates there arises a control of the pressure in the sealing zone, thus permitting balancing of the stresses on the double impeller and optimization of the sealing system.

Abstract: A method enables a structural cover for a gas turbine engine to be manufactured. The method includes forming a torroidial body including an integrally-formed windage cover portion and a seal flange portion, and forming a plurality offastener openings extending from a forward side of the torroidial body to an aft side of the torroidial body, such that when installed in the gas turbine engine, the windage cover portion facilitates shielding the fastener openings from a gas flow path.

Abstract: An improved oil seal is provided for sealing passage of a rotatable shaft through an end wall of a bearing housing in a turbomachine or the like, wherein the shaft is rotatably supported within the bearing housing by oil-lubricated bearings. The improved oil seal comprises a dynamic oil-air separator and a slinger rotor mounted on the shaft for rotation therewith, the slinger rotor having an outwardly extending slinger ring with an outboard seal face with radially oriented slots and a circumferential groove or grooves.

Abstract: A method and apparatus carrying the method for sealing a radial gap between coaxial inner and outer rotating shafts of a gas turbine engine includes using a radial seal as a main seal to seal the gap for a normal engine operation condition, and using an axial seal as a back-up seal for a double seal of the gap. The radial seal provides a seal which meets relatively restrictive leakage requirements for the normal engine operation condition and the axial seal provides a back-up seal which meets less restrictive leakage requirements but is much more tolerant of radial displacement and vibration between the coaxial inner and outer rotating shafts. Thus, an engine operable condition is ensured under abnormal conditions, such as bird strikes, in which the coaxial relationship between the inner and outer rotating shafts are affected by unbalancing forces caused by the bird strike, thereby causing a failure of the radial seal.

Abstract: A rotary blood pump comprising at least one rotor, a housing and at least one conduit in the rotor for conducting a by-passed portion of the blood into a clearance between the rotor and the housing, the portion of blood consisting mostly of plasma without red cells, thus preserving the solid particles and red cells from damage.

Abstract: Two stages of relatively rotatable guide vanes (22,24) are arranged in tandem. Shroud portions (42,46) on the vanes overlap in loose engagement, until an associated gas turbine engine starts operating. Gas loads then act on the downstream vane stage (24) and move it in a downstream direction until the opposing flanks of radially opposing lands (44,48) on respective shrouds (42,46) engage, whereupon, gas leakage via the overlap onto the turbine casing (40) is at least substantially reduced.

Abstract: A pump has a housing defining a pump chamber and having a shaft opening. An impeller shaft extends through the shaft opening and is sized to define a gap between the impeller shaft and the shaft opening. An impeller is attached to the shaft inside the pump chamber. The impeller includes a first set of impeller blades for transporting fluid through the pump chamber and a second set of impeller blades for creating a pressure force which pushes fluid away from the shaft opening. The pump with sealless shaft prevents fluid from leaking through the gap, and therefore is particularly suited for use in a tank-type vacuum cleaner capable of collecting both dry material and fluid. The gap is used in such an application to prime the pump, thereby discharging fluid collected in the tank.

Abstract: In a centrifugal pump, a barrier ring in the form of a dynamic seal member is interposed between relatively rotating, generally circular wall portions which undergo relative axial movement to vary the width of a gap between the wall portions, the seal member having an outer jacket of flexible material and an annular spring member of frustoconical configuration inserted into offset grooves in the jacket, and when the seal member is mounted under compression between the confronting surfaces will follow the relative axial movement between the wall portions to maintain liquid-tight sealing engagement with the wall portions. In a modified form of invention, the seal member includes a pair of helical spring members inserted into grooves in an outer flexible jacket and, when the seal is mounted under compression between confronting surfaces of the wall portions as described will maintain liquid-tight sealing engagement notwithstanding variations in the width of the gap between members.

Abstract: A heat dissipation fan as disclosed includes a heat dissipation fan blade, a self-lubricating bearing, a stator having an electrical circuit plate and a casing. The heat dissipation fan blade includes a shaft extending therefrom. The shaft has a rounded free end that and contains a neck to seat a locking plate therein. The casing has a collar extending therefrom to hold the stator in place. The collar contains a recess to securely receive the self-lubricating bearing and forms an internal shoulder to restrain and support the locking plate and the self-lubricating bearing. The locking plate is round and contains a through hole therein. The through hole has a diameter corresponding to that of the neck in the shaft. The locking plate has multiple slits formed on the periphery of the through hole. A washer is placed in the bottom of the recess and contains a hole with a diameter smaller than the shaft to abut the free end of the shaft.