Abstract: A flow discouraging system includes a stator assembly, a rotor assembly, and a plurality of fingers. The stator assembly includes one or more stationary components forming a side wall, the side wall including an annular groove defined by an outer axially-extending surface, an inner axially-extending surface, and a radial surface extending between the outer and inner axially-extending surfaces. The rotor assembly is disposed adjacent to and spaced apart from the stator assembly to form a portion of a cavity and includes an annular rim extending at least partially into the annular groove. The plurality of fingers is disposed in the annular groove and extends from the one or more stationary components the annular rim.

Abstract: A parallel redundant fan system includes at least first and second fans located adjacent each other. Each fan includes: (i) a fan housing defining a fan chamber in which an impeller is supported for rotation about an axis of rotation; (ii) a first chamber outlet in communication with the fan chamber and defined by an opening in a first wall of the fan housing; (iii) a second chamber outlet in communication with the fan chamber and defined by an opening in a second wall of the fan housing; and, (iii) first and second backflow prevention dampers respectively associated with the first and second chamber outlets. The first and second dampers respectively include first and second damper plates that selectively pivot from their closed positions toward their opened positions against the closing force of respective first and second counterweights in response to exhaust air flow pressure exerted thereon.

Abstract: A sanitary air jet device [1000] is operated by a user blowing air into its first stage inlet [1111] of a mouthpiece [1110]. The air stream causes a first stage turbine [1130] to rotate and spin a shaft [1205]. The shaft passes through a separator wall [1140]. A second stage turbine [1230] is connected to the shaft [1205] on the other side of the separator wall [1140] in a second stage chamber [1201]. The shaft [1205] causes second stage turbine [1230] to spin and draw air in through a number of second stage inlets [1211] in the second stage chamber [1201]. The second stage turbine [1230] blows the clean air out of a second stage exhaust [1221]. The second stage chamber [1201] is separated from the first stage chamber [1101] such that it does not receive the air blown in by the user. Therefore, one may blow out candles on a cake with clean air and no longer spray saliva droplets and microbes on the cake.

Abstract: Provided is a centrifugal compressor. In the centrifugal compressor, a plurality of sub-compressors each of which includes an impeller are connected in parallel to increase a compression capacity, the plurality of sub-compressors are each assembled to a single common shaft that is rotated by a driving unit, and the impellers of the plurality of sub-compressors are disposed in opposing directions. The centrifugal compressor reduces a production cost, and cancels thrusts during driving so as to reduce a loss of a bearing, thereby increasing efficiency of the compressor.

Abstract: A centrifugal reverse flow disk turbine for power generation, comprising; a) a turbine shaft; b) a disk rotor disposed on said turbine shaft; c) a housing, having said turbine shaft and said disk rotor, bearings, seal devices, and at least one jet nozzle means; d) a plurality of radially engraved channel for transporting working fluid from entering ports, placed axially near said turbine shaft; e) a plurality of said channels having two curvatures; first curvature has a small radius, and concaved pertinent to rotational direction of said rotor, starting from the entering port to middle of its flow path, and the second curvature has a large radius, convexed pertinent to rotational direction of said rotor, positioned near the peripheral of said rotor; a plurality of a buket attached at every flow channel, directing against nozzle disposed on said housing, thereby deriving impinging counter supersonic flow.

Abstract: In a disc turbine for operation from steam, including superheated steam, a stack of horizontally oriented discs is fitted centrally with a hub having a closed upper end from which a driveshaft extends upwardly, supported by a bearing system. The hub is configured with identical vanes arrayed uniformly about the central axis and specially shaped to accomplish a set of desired flow path objectives. The vanes are generally tapered such that their cross-sectional shape evolves from predominantly solid material in area at the top of the hub to predominantly open area at the bottom of the hub, where the flow paths proceed downwardly into a tubular exhaust passageway. The entry to the exhaust passageway may take the form of effectively a hollow portion of the shaft in the exhaust region, which may be supported from the enclosure by a bearing set. The central opening in each disk, and thus in the stack, and in the periphery of the hub are both configured with a complementary mating interface pattern: e.g.

Abstract: A high-strength heat resisting cast steel which has high creep rupture strength at temperatures of 620° C. or above, high toughness, and good weldability. A method of producing the steel, a steam turbine casing, a main steam valve casing, and a steam control valve casing, each casing being made of that steel, as well as a steam turbine power plant using those components are also provided. The high-strength heat resisting cast steel contains 0.06-0.16% by mass of C, 0.1-1% of Si, 0.1-1% of Mn, 8-12% of Cr, 0.1-1.0% of Ni, 0.7% or less of Mo, 1.9-3.0% of W, 0.05-0.3% of V, 0.01-0.15% of one or more of Nb, Ta and Zr in total, 0.1-2% of Co, 0.01-0.08% of N, and 0.0005-0.01% of B, the balance being Fe and unavoidable impurities.

Abstract: A caseless rotor assembly is provided. The caseless rotor assembly includes a rotor shaft, a high pressure portion with a high pressure rotor blade, a low pressure portion with a low pressure rotor blade, and a common wall between the high pressure portion and the low pressure portion. The common wall extends radially from the rotor shaft. The common wall itself includes a shaft end oriented towards the rotor shaft and an outer end on the other side of the common wall, oriented radially outwards. Additionally, the common wall surrounds circularly the rotor shaft.

Abstract: A modular multistage pump assembly includes a volute having a suction side and a pressure side, a pump stack having at least one stage, and a modular flange coupled to each of the volute and the pump stack.

Abstract: An apparatus and method for treating sewage The apparatus receives sewage at a receiving compartment and separates solids from liquids at the receiving compartment. The solids can be extracted from the receiving compartment by an auger. The liquid sewage flows through a series of treatment compartment containing rotating biological contactor discs for treatment by these rotating biological contactor discs. The rotating biological contactor discs are secured to a rotating shaft. The rotating shaft and the auger are powered by a quasi-submerged turbine displaced by a flow of air.

Abstract: A flow enhancement improvement for an underwater turbine generator (10) is disclosed wherein a longitudinal hole (240) is disposed in the central area (26), typically a hub (20) of the generator (10), and a second, augmentor duct (41), preferably rigid, is disposed about the outer duct (40) or housing of the unit to create a slot (200) area. The slot (200) and hollow hub (20) create areas of smooth, laminar fluid flow. The leading edges of the hub (20) or central ring and the augmentor (41) and outer ducts (40) are elliptical to enhance the fluid dynamics of the structure.

Abstract: A blower unit for a portable blower, having a drive shaft that is rotatably driven by a drive motor. Disposed in the blower unit is an axial fan that is provided with at least one fan wheel driven by the drive shaft and at least guide wheel fixedly disposed in the housing. To achieve a simple construction and a simple manufacture, the housing has at least two housing sections and is divided approximately parallel to the axis of rotation of the drive shaft.

Abstract: A centrifugal pump has impellers that are not connected by a central shaft. More specifically, each of the impellers has a separate hub segment that interlocks with an adjacent hub segment from another impeller. The hub segments are rotated in unison with each other to rotate the impellers.

Abstract: A heat dissipation module includes a housing, and a fan including an outer frame, a first rotor, a base, a second rotor and a driving device. The first rotor includes a shaft, a first hub and a plurality of first rotor blades disposed around the first hub. The base is disposed in the outer frame. The second rotor includes a plurality of second rotor blades, and is coupled to the shaft of the first rotor and disposed next to the first rotor. The driving device is supported by the base for driving the first rotor and the second rotor simultaneously.

Abstract: An airfoil for use in a rotor assembly is disclosed, the airfoil having a tip-cutter located on a sidewall near a tip portion, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-grinder located on the tip portion, wherein the tip-grinder capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-rake that facilitates reducing loading induced to said airfoil during tip rubs.

Abstract: A fan assembly includes a first fan and a second fan mounted on the first fan. The first fan includes a plurality of locking units and a plurality of positioning dots extending upwardly therefrom. Each of the locking units includes a perpendicular portion and a horizontal portion. The second fan defines a plurality of through holes therein corresponding to the locking units of the first fan, and a plurality blind holes therein corresponding to the positioning dots of the first fan. Each of the locking units of the first fan extends into a corresponding through hole of the second fan with the horizontal portion thereof engaging with the second fan near an edge of the through hole. Each of the positioning dots of the first fan is received in a corresponding blind hole of the second fan.

Abstract: In a steam turbine having a cross-over duct for delivering steam discharged from an intermediate pressure turbine to low pressure turbines, the intermediate pressure turbine provides two outlets for discharging exhaust steam, the low pressure turbine provides two inlets, and the outlets and the inlets are arranged on the same straight line as viewed from a planar direction. One of the outlets and one of the inlets which are close to each other are connected through a cross-over duct, the other of the outlets and the other of the inlets which are far from each other are connected through another cross-over duct, and the cross-over ducts are arranged to be at two stages in the up-down direction.

Abstract: An axial face seal (13), which seals a pump housing in the region of the pump shaft (12), is constructed in an axially compact manner. Spring holders (24, 25), which transmit the required pressing force of a compression spring (23), are connected to one another with a positive fit in a rotation direction, and hold a rotating axial face seal ring (19) in a rotationally fixed manner to the pump shaft (12). The spring holders (24, 25) are compact and enclose an abutment ring (33) for pump impellers as well as the compression spring (23). A motor-side spring (24) engages over the rotating axial face seal ring (19), by which an axially extremely short constructional length is achieved.

Abstract: A multi-stage centrifugal pump assembly which is manufactured in the same construction type with cast components on the one hand, and with a stainless steel lining formed of sheet metal on the other hand, includes a bearing carrier (13) which is designed and suitable for the connection of a cast housing component (12) as well as for receiving a sheet metal lining made of stainless steel.

Abstract: With the multi-stage centrifugal pump assembly, the connection between the motor shaft (7) and the pump shaft (9) is effected by way of a thread (26, 27), which joins the fits (31, 34) lying therebehind, between a pocket hole bore (24) in the pump-side end of the motor shaft (7) and the motor-side end of the pump shaft (9). Thereby, a transition fit (32) is provided in the region of the bearing (11), and a press fit 34 in the free region therebehind.

Abstract: A pump apparatus comprising a series of stacked impellers rotating about a common axis, for pumping a viscous fluid mixture upwardly from an underground location. The pump apparatus comprises a generally cylindrical housing having an intake at or near its suction end. A plurality of impellers are mounted in the housing to rotate about a shaft, which each induce flow of the mixture toward the discharge end of the pump. Each impeller has a series of radially outwardly extending vanes, one or more of such vanes having a radially-extending horizontal slot and arranged to generate an upwardly moving column of fluid. Without being limited to the theory of operation, the horizontal slot in the vanes assists in creating laminar flow and reducing turbulent flow.

Abstract: A turbine energy generating system includes a combustion chamber for converting fuel into energy by igniting an air and fuel mixture, a turbine for converting energy produced by the combustion chamber into mechanical energy, and a generator for converting mechanical energy produced by the turbine into electrical energy in the range of 1 to 15 kilowatts.

Abstract: An apparatus for adjusting a thrust load on a rotor assembly of a gas turbine engine includes an impeller rear cavity defined between a rear face of an impeller of the rotor assembly and a stationary wall spaced axially apart from the rear surface of the impeller. A pressurized air flow with a tangential velocity is introduced into the impeller rear cavity at a tip of the impeller to pressurize the cavity. Means are provided in the cavity for directly interfering with the tangential velocity of the pressurized air flow to affect an average static pressure of the pressurized air flow within the cavity in order to adjust the thrust load on the rotor assembly caused by the average static pressure in the cavity.

Abstract: This apparatus (1) includes an air intake duct, a volute (5) of which the inlet opening (22) communicates with the air intake duct, a first vane rotor (4) located immediately downstream of the inlet opening (22) of the volute (5), a motor (3) for driving the rotor (4), and a motor (3) for rotating the rotor (4) in order to generate a centrifugal air flow in the volute (5). The apparatus further includes: a casing (2) having a tubular portion (10a) located at a substantially constant distance from the motor (3), the casing (2) and the motor (3) thereby together bounding a gas flow passage (15) including at least one gas inlet orifice (20) and at least one gas outlet orifice (16); and a second vane rotor (6) located downstream of the gas inlet orifice (20) rotated in order to generate a forced gas stream in the gas flow passage (15).

Abstract: An impeller system with split impeller configuration between adjacent turbine wheels for synchronizing their thermal response is provided. Exemplary embodiments include a turbomachine having a turbine, a compressor and a rotor disposed between the turbine and the compressor, and an impeller system. An impeller system includes a turbomachine wheel, and another turbomachine wheel disposed adjacent to the first turbomachine wheel, a rabbet joint defined between the first and second turbomachine wheels and a split impeller disposed on the first and second turbomachine wheels.

Abstract: A gas turbine engine (10) having a pressure-rise combustor (30) and the pressure-rise combustor (30) is positioned upstream of a stage of turbine nozzle guide vanes (32). The vanes (33) of the stage of turbine nozzle guide vanes (32) forms an ejector and each of the vanes (33) has an upstream portion (34) and a downstream portion (36). The upstream portions (34) of the vanes (33) have leading edges (38) and the upstream portions (34) are arranged substantially straight and parallel to define constant area mixing passages (40) for a flow of gases there-through. The downstream portions (36) of the vanes (33) are arranged at an angle to the upstream portions (34) of the vanes (33) to turn the flow of gases there-through.

Abstract: A locking and fixing device for a heat shield element, which heat shield element can be arranged along a heat shield row axially directly next to at least one blade provided in a blade row and has, axially facing the blade, at least two projections of rib-like design which are spaced apart in the circular circumferential direction, are raised above a side wall section facing the blade and define a clear intermediate space which extends in the circular circumferential direction and into which a locking lug provided on the blade can be fitted. Further disclosed is at least one rib-like projection, on its side facing away from the clear intermediate space, providing an extension which extends in the circular circumferential direction, is connected to the projection and the side wall section and rises above the side wall section at most up to the rib height of the projection.

Abstract: A multistage radial turbocompressor has at least first, second, and third intake parts each forming a respective intake spaced along an axis and first, second, and third output parts each forming a respective output axially juxtaposed with the respective intakes. Respective first, second, and third fans having axially directed vanes are rotatable in the housing formed by the parts between the intakes and outputs. A shaft centered on the axis carries the first, second, and third fans. One of the fans is back-to-back with another of the fans with the vanes of the one fan facing axially oppositely away from the vanes of the other of the fans. Radial bearings support the shaft in the housing, and an axial bearing between the one fan and the other fan supports the shaft in the housing.

Abstract: A high-efficiency, multi-stage centrifugal pump and method of assembly. The pump can include three pump stages with each one of the three pump stages including a front casing, a back casing, an impeller, and a bladed diffuser. The front casing and the back casing are removeably coupled around the impeller and the bladed diffuser. In the three-stage pump, the fluid can be pumped at a flow rate between about 300 liters per second and about 500 liters per second with an efficiency between about 86% and about 91%. The method includes separately casting, machining, and polishing each one of the front casing, the back casing, the impeller, and the bladed diffuser.

Abstract: A vacuum pump comprises a drive shaft and a Siegbahn pumping mechanism. The Siegbahn pumping mechanism comprises a rotor element located on the drive shaft and an annular stator element located about the drive shaft and proximate the rotor element, the stator element comprising a plurality of walls extending towards the rotor element and defining a plurality of spiral channels. The stator element comprises a plurality of sections, with means such as a resilient member being located about the sections to urge the sections together, and thereby inhibit gas leakage between the sections of the stator element. The resilient member can also form a seal between the stator sections and a casing located about the pumping mechanism.

Abstract: A fluid pump assembly includes a rotatable component that can be rotated about an axis and a static vane assembly located adjacent to the rotatable component. The static vane assembly includes a circumferential surface axially spaced from the rotatable component, and one or more vanes extending from the circumferential surface toward the rotatable component. The one or more vanes are configured to produce a radial load on the rotatable component when the rotatable component is rotating about the axis and a fluid is present between the static vane assembly and the rotatable component.

Abstract: A steam turbine 10 is comprised of a double-structured casing configured of an outer casing 21 and an inner casing 20, a turbine rotor 23 disposed through the inner casing and having a plurality of stages of moving blades 22 implanted, and a plurality of stages of stationary blades 25 disposed alternately with the moving blades 22 in the axial direction of the turbine rotor 23 in the inner casing 20. The steam turbine 10 is further provided with a discharge passage 30 which externally guides steam, which has flown in the inner casing and passed the final stage moving blades while performing expansion work, directly from the inner casing interior.

Abstract: In a multistage centrifugal compressor, a plurality of impellers is attached to the same rotary shaft. Vaned Diffusers and vaneless diffusers are used, as diffusers, for respective compressor stages configuring the compressor. The vaned diffusers are continuously used from the first compressor stage to the middle compressor stage, and the vaneless diffusers are used for the last compressor stage and the previous stage. While high efficiency is maintained at the compressor stages having the vaned diffusers, an operating flow range is secured at the compressor stages having the vaneless diffusers.

Abstract: A vertical tower fan includes a frame structure defining multiple vertically spaced fan spaces, a fan module controllable to rotate vertically spaced fan blades, and multiple housing members mounted on the frame structure at different elevations and respectively surrounding the fan blades and respectively rotatable to adjust the direction of one respective air outlet.

Abstract: An air diffuser system for an impeller for a centrifugal pump has least one channel (36) with first opening (40) through the backside (14) and a second opening (42) through the front side (38) of the impeller (12). Tubes (44) are associated with each channel (36) and extend from the backside (14) of the impeller (12). Tube ends (48) are oriented in the direction of rotation (46) of the impeller (12).

Abstract: A rotor assembly for a miniature gas turbine propulsion system comprises a centrifugal compressor wheel, a turbine wheel, a shaft and a tie bolt. The centrifugal compressor wheel includes a first curved tooth coupling, and the turbine wheel includes a second curved tooth coupling interconnected with the first curved tooth coupling. The shaft extends from the centrifugal compressor wheel, and the tie bolt extends between the shaft and the turbine wheel to bring the first curved tooth coupling into compression with the second curved tooth coupling. As such, the compressor wheel and the turbine wheel are assembled and remain, over the operational envelope of the propulsion system, in a reliably robust aligned configuration.

Abstract: A rotating assembly for a turbomachine includes a plurality of rotating members that extend radially outward from a central hub. Each of the plurality of rotating members includes a base portion detachably mounted to the central hub, a tip portion, a mid-span portion that extends between the base portion and the tip portion, and a shroud portion positioned at one of the tip portion and the mid-span portion. The shroud portion includes a pressure side and a suction side. At least one hard face interface member is secured to at least one of the suction side and the pressure side of the shroud portion. The at least one hard face interface member is both mechanically interlocked with, and metallurgically bonded to, the shroud portion.

Abstract: A turbo vacuum pump comprising a suction part 23A that sucks gas in an axial direction; a discharge part 50 that discharges the gas sucked by the suction part 23A, the discharge part 50 having a plurality of rotating impellers 70, 80 and a stationary impeller 71 arranged so as to be opposed to each of the plurality of rotating impellers 70, 80; and a rotating shaft 21 that rotates the plurality of rotating impellers 70, 80, wherein the plurality of rotating impellers 70, 80 include at least one stage of a first turbine impeller 70 for discharging the sucked gas in the axial direction, the first turbine impeller 70 being fixed to a suction-part-side end face 15 of the rotating shaft 21, and at least one stage of a second turbine impeller 80 fixed to the rotating shaft 21 that extends through the second turbine impeller 80, the second turbine impeller 80 being arranged downstream of the first turbine impeller 70.

Abstract: The invention relates to an intermediate casing (21) for an aircraft jet engine, comprising an outer shell (23) and also front and rear flanges (25, 27) which are arranged radially inside with respect to the outer shell, the casing (21) also comprising structural arms (17) which extend radially between the flanges as far as the shell (23), the rear flange being equipped with receiving means (34) for receiving a fixing bracket for fixing a rod for absorbing the thrust forces, and the first receiving means comprising bosses (36) coming from the rear flange, through which bosses through-orifices (38) are formed which are passed through by fixing screws of the bracket. According to the invention, at least one of the bosses (36) extends as far as making contact with one of the structural arms (17).

Abstract: Multistage centrifugal compressor having a horizontally openable tank, comprising a lower semi-tank and an upper semi-tank, a shaft having a series of rotors and a series of stages each of which comprising, in turn, a series of lower semi-diaphragms and a series of upper semi-diaphragms, a lower half-ring and an upper half-ring which can be coupled to form a bearing ring, the lower half-ring being fastened internally to the lower semi-tank , and the corresponding upper half-ring being fastened to the upper semi-tank , in each stage of the multistage centrifugal compressor, the lower semi-diaphragms are rigidly constrained to one another to form a first pile of lower semi-diaphragms and, the corresponding upper semi-diaphragms are rigidly constrained to one another to form a second pile of lower semi-diaphragms, the first pile can be constrained to the lower half-ring and the second pile can be constrained to the upper half-ring.

Abstract: A system for stabilizing a water brake including at least two rotor disks, a chamber of the water brake for containing water positioned between the at least two rotor disks, a pressure measuring device for measuring a partial pressure in the chamber, and an air injection device for injecting air into the chamber to increase the partial pressure in the chamber.

Abstract: A sanitary air jet device [1000] is operated by a user blowing air into its first stage inlet [1111] of a mouthpiece [1110]. The air stream causes a first stage turbine [1130] to rotate and spin a shaft [1205]. The shaft passes through a separator wall [1140]. A second stage turbine [1230] is connected to the shaft [1205] on the other side of the separator wall [1140] in a second stage chamber [1201]. The shaft [1205] causes second stage turbine [1230] to spin and draw air in through a number of second stage inlets [1211] in the second stage chamber [1201]. The second stage turbine [1230] blows the clean air out of a second stage exhaust [1221]. The second stage chamber [1201] is separated from the first stage chamber [1101] such that it does not receive the air blown in by the user. Therefore, one may blow out candles on a cake with clean air and no longer spray saliva droplets and microbes on the cake.

Abstract: A direction-switchable pneumatic cylinder includes: a cylinder body with two intakes, several exhaustion ports and a rotary shaft; and a predetermined number of movable wheels and fixed wheels arranged in the cylinder body and interlaced with each other. Each of the movable wheels and fixed wheels is formed with several vents concentrically arranged into an inner circle and an outer circle. The rotary shaft is fitted through the movable wheels and fixed wheels. The fixed wheels are not rotatable, while the movable wheels are synchronously rotatably with the rotary shaft. The outer circles of vents of the fixed wheels and the movable wheels are aligned with one intake, while the inner circles of vents of the fixed wheels and the movable wheels are aligned with the other intake. When high-pressure gas is guided into the pneumatic cylinder from one intake, the airflow will flow through the outer circles of vents to drive the movable wheels and the rotary shaft in one direction.

Abstract: The Combined Hydrodynamic-Inertial Rotoset-Selfbooster is a non-fuel power unit which includes: the hydrodynamic vane-fairing inertial rotor placed inside a closed loop tubular tunnel; a hydraulic module with a rotary pump propelling operative liquid in selfboosting manner to drive said rotor, cavitation preventor, and the electromechanical structure with the starter, electric output generator, storage battery, charger, drives, cooler, meters, control. The total combined rotor's torque is a sum of selfboosting hydrodynamic portion, and selfboosting inertial portion of the common integrated power produced simultaneously by the united rotor. The technology of rotoset-selfbooster can comprise various designes including mono- and poly-tunnel-rotor sets with a wide varieties of operative liquids, rotary pumps, and output power structures. The total power ratio is about 7.5 depending on design and KW required.

Abstract: A turbo blower, include an air hood provided with an air inlet and a turbine disposed within the air hood driven and rotated by a motor. The turbine consists of a plurality of guide vanes fitted between a circular base plate and a top plate. The turbo blower is characterized by the height of each of the guide vanes, commencing at a vane front end close to a center of the base plate, gradually decreases to a relatively lower point at a middle section of the guide vane, and the height of each of the guide vanes, commencing at the relatively lower point, gradually increases to a vane rear end, thereby forming a curved shape. The turbo blower is able to automatically decrease power consumption when the air inlet end or the air outlet end is obstructed, thereby reducing motor load.

Abstract: A multistage centrifugal compressor includes a rotary shaft, and multistage impellers attached to the rotary shaft. Each of the impellers includes a hub, a shroud and blades therebetween in a radial cascade arrangement. An annular suction passage for guiding the fluid flow from the inward radial direction to a blade inlet is disposed upstream of the centrifugal impeller. A diffuser is disposed downstream of the centrifugal impeller. A bend portion is disposed downstream of the diffuser, and a return channel with a guide blade portion is disposed downstream of the bend portion. The annular suction passage at a hub side includes an axial parallel portion.

Abstract: Method and apparatus for pumping drilling fluid (mud) containing drill cuttings, comprising a centrifugal pump with screw pump accelerator. The screw pump creating positive pressure for centrifugal pump inlet to increase performance. The screw pump mud level fluctuations are compensated by the vertical screw pumping unit. Adjusting the elevation of pump will adjust the quantity of mud pumping, which is not possible with ether one pump alone. Air is allowed to mix with the mud in the centrifugal pump to create air bubbles to decrease density of the mixture and decrease the head pressure.

Abstract: A method for fabricating an outlet guide vane includes the steps of fabricating a structural spar from a first material, fabricating a fairing from a second material, and installing the fairing onto the spar so as to at least partially surround the spar and form an airfoil. An outlet guide vane includes an airfoil including a leading edge and a trailing edge, a structural spar formed from a first material located within the airfoil, and a fairing formed from a second material at least partially surrounding the spar. A gas turbine engine assembly includes a core gas turbine engine, a fan assembly including a plurality of fan blades coupled to the core gas turbine engine, and a plurality of outlet guide vanes coupled downstream from the fan blades, at least one of the outlet guide vanes including an airfoil having a leading edge and a trailing edge, a structural spar formed from a first material located within the airfoil, and a fairing formed from a second material at least partially surrounding the spar.

Abstract: A fan including a plurality of spaced fan bodies that rotate in a substantially cylindrical cavity having inlet and outlet openings for tangential intake and discharge of the fluid, the fan bodies comprising substantially disc-shaped bodies that extend in a substantially radial direction from the shaft and are positioned on the shaft such that the shaft runs through the centre of the fan bodies and in such a manner that a void is formed between two neighbouring fan bodies, and wherein each fan body is connected to the shaft or to a spacer only, and wherein the fan bodies are provided with flow elements on both of their radially extending faces, the flow elements consisting of curved projections, the curved projections being curved forwardly as compared to the direction of rotation of the fan bodies and the curved projections extending between two imaginary circles on the fan bodies' radially extending faces having radii r1 and r2 respectively, wherein r1<r2, the radius r1 is larger than the outer radius of

Abstract: A method of fabricating a turbine rotor is provided. The method includes fabricating a plurality of substantially cylindrical disks. Fabricating each disk includes fabricating a substantially cylindrical body and extending a bore substantially concentrically through the body. The method also includes coupling at least two of the plurality of disks together to form a rotor having a bore extending axially therethrough.