Abstract: A mass spectrometer includes a vacuum chamber, a turbomolecular pump, and a roughing pump. The vacuum chamber is divided into a low vacuum chamber and a high vacuum chamber respectively provided with, on their wall surfaces, a first opening and a second opening. The turbomolecular pump has an operation chamber including in its inside a blade rotor and being provided with a first intake port, and an exhaust chamber communicating with the operation chamber and being provided with a second intake port and an exhaust port. The turbomolecular pump is placed so that the high vacuum chamber and the operation chamber communicate with each other through the second opening and the first intake port, and the low vacuum chamber and the exhaust chamber communicate with each other through the first opening and the second intake port. The roughing pump is connected to the exhaust port.

Abstract: A boundary layer turbomachine can include a housing defining an interior space and having an inlet opening and an outlet opening to facilitate movement of a fluid through the housing. The boundary layer turbomachine can also include a rotor assembly disposed in the rotor chamber and configured to rotate about an axis of rotation. The rotor assembly can have a plurality of disks spaced apart along the axis of rotation and defining an interior opening along the axis of rotation. The fluid can pass through gaps between the disks and the interior opening as the fluid moves through the housing.

Abstract: A screw compressor includes: a screw compressor main body; a motor for driving the screw compressor main body; a gearbox interposed between the screw compressor main body and the motor to transmit a driving force of the motor to the screw compressor main body; and a gas cooler positioned below either the screw compressor main body or the motor and attached as a separate body to a side surface of the gearbox.

Abstract: A temperature destratification assembly can include an outer housing. An impeller can be positioned within the outer housing between the inlet and outlet of the outer housing. The impeller can have an impeller hub and a plurality of impeller blades extending radially outward from the impeller hub. The assembly can include an impeller motor configured to rotate the impeller blades about an axis of rotation. A stator can be positioned within the outer housing between the impeller and the outlet of the outer housing. The stator can include a plurality of vanes. The stator vanes can include an upstream edge at the upstream end of the stator, a first surface extending from the upstream edge to the downstream edge of the vane, and a second surface opposite the first surface and extending from the upstream edge to the downstream edge of vane. A plurality of the vanes can have a downstream edge at the outlet of the outer housing.

Abstract: An air turbine starter for starting an engine, comprising a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas. A gear train is drivingly coupled with the turbine member, a drive shaft is operably coupled with the gear train, and an output shaft is selectively operably coupled to rotate with the engine. A screen is located within the interior between the at least one turbine member and the set of outlets and adapted to mitigate ejection of ignited particles from within the housing.

Abstract: The catheter device comprises a drive shaft connected to a motor, and a rotor mounted on the drive shaft at the distal end section. The rotor has a frame structure which is formed by a screw-like boundary frame and rotor struts extending radially inwards from the boundary frame. The rotor struts are fastened to the drive shaft by their ends opposite the boundary frame. Between the boundary frame and the drive shaft extends an elastic covering. The frame structure is made of an elastic material such that, after forced compression, the rotor unfolds automatically.

Abstract: A fluid pump having at least two pump heads in series permits pumping fluid at both high pressure and high volumetric rate. Each pump head has at least two fluid conduits in fluid communication with a housing, the housing containing an impeller for drawing fluid through an inlet in the housing and moving the fluid through the fluid conduits. The at least two fluid conduits of one pump head combine fluid flow at the inlet of a neighboring pump head to provide a single flow of fluid through the inlet into the neighboring pump head. A drive structure passing through the inlets between two pump heads is configured to commonly drive the impellers in the housing of each pump head.

Abstract: A serial axial flow fan includes a first axial flow fan, a second axial flow fan, and a current plate. Hollow cells of the current plate are partitioned by a lattice-shaped partition, penetrate in an axial direction, and are uniformly two-dimensionally arranged at an outer edge. An axially lower end portion of a first housing of the first axial flow fan and an axially upper end portion of a second housing are directly coupled to each other, and the current plate is provided in a coupling unit of the first housing and the second housing. An axially lower end portion of the first tubular unit of the first housing is axially opposed to an axially upper end portion of the second tubular unit of the second housing with the current plate interposed therebetween. A recess recessed on an opposite side to the coupling unit in the axial direction is provided on an axially end surface of at least one of an axially lower end surface of the first tubular unit and an axially upper end surface of the second tubular unit.

Abstract: A fan includes an impeller, a drive device, and a frame structure. The driving device drives the impeller to rotate, and the frame structure accommodates the driving device. The frame structure includes a frame body, a first frame, a second frame, a base and a plurality of supports. The frame body has first engaging portions and second engaging portions, which are disposed annularly at the upper end and the lower end of the frame body, respectively. The first frame is mounted on the frame body and disposed corresponding to the first engaging portions. The second frame is mounted on the frame body and disposed corresponding to the second engaging portions. The base is disposed within the frame body and located adjacent to the second frame. The supports are disposed around the base. The material of the frame body is different from that of the first and second frames.

Abstract: A multiple axle-sleeve driving bidirectional rotating wheel-shaped fan turbine and a bushing wheel-shaped fan compressor, including: a working component, a driving component, a structural and installed component and a starting component. A wheel-shaped fan of the turbine drives a corresponding wheel-shaped fan of compressor to rotate through a driving axle sleeve. A rotating direction of the wheel-shaped fan of the turbine is opposite to a rotating direction of a wheel-shaped fan adjacent to the wheel-fan and rotating speed of the plurality of wheel-shaped fan is different. Each of the auxiliary wheel-shape fans is respectively bushed on each of the wheel-shaped fans of the compressor. A turbojet assembled with this disclosure has a high functionality, a light weight, a quick heat dissipation, an excellent anti-surging and a low energy consumption.

Abstract: An accessory gear box configured to be mounted on a fan casing of a turbojet engine, including: an input shaft; a plurality of accessory drive shafts; and a compartment forming an interface with an accessory arranged on the housing of the accessory gear box at a site of the accessory, the interface compartment including an inlet and an outlet configured to allow air to circulate inside the compartment, to insulate the accessory gear box from heat generated by the accessories.

Abstract: Method and system for compressing a fluid in a gas phase and for pumping the fluid in a dense phase. The system includes a compressor part having an impeller; a compressor part inlet that receives the fluid in the gas phase; a compressor part outlet that provides the fluid in the gas phase; a temperature changing device that changes a phase of the fluid; a pump part having an impeller; a pump part inlet that receives the fluid in the dense phase from the compressor part outlet; a pump part outlet that outputs the fluid in the dense phase from the system; a single bull gear configured to rotate around an axial axis with a predetermined speed; plural pinions contacting the single gear bull and configured to rotate with predetermined speeds, and a pump shaft configured to rotate the at least one impeller of the pump part.

Abstract: A V-shaped arrangement of turbines adapted to orient in such a manner that crosswind enters the arrangement in a direction that is substantially parallel to the axis bisecting the arrangement is described. The V-shaped arrangement includes clockwise rotating turbines and counterclockwise rotating turbines.

Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170.

Abstract: A vacuum pump system for evacuating at least five volumes comprising a turbomolecular pump and a forevacuum pump arranged to pump an output of the turbomolecular pump arrangement to atmosphere. The turbomolecular pump has at least five pumping stages separated by rotor blades. Not more than three pumping stages have pumping speeds in excess of ? of the highest pumping speed when under vacuum and/or a pumping port cross section in excess of ? of the highest pumping port cross section, and at least two pumping stages have pumping speeds less than ¼ of the highest pumping speed when under vacuum and/or a pumping port cross section of less than ¼ of the biggest pumping port cross section. The ratio of pressures between the pumping stage with the highest pressure and the pumping stage with the lowest pressure is at least 100000:1 when under vacuum.

Abstract: A superconducting integrated ring turbine motor generator gas turbine engine stage of the present invention includes a combination of turbine vanes, rotors and blisk assemblies that prevent temperatures during operation from interfering with the extraction or control of power generation processes. The engine stage includes a ring having an evenly spaced array of aerodynamic vanes affixed on the inside or outside of the ring. The vanes are spaced apart by a nonmagnetic armature assembly spacer ring.

Abstract: A system includes a multi-stage turbine. The multi-stage turbine includes a first turbine stage with a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel, a second turbine stage with a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel, and an interstage seal assembly extending axially between the first and second turbine stages. The interstage seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first seal. The interstage seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate includes a second seal. The interstage seal assembly also includes a spacer wheel extending from a rotor shaft and configured to engage with the first coverplate and the second coverplate.

Abstract: A gas turbine engine includes a first shaft defining an axis of rotation and a second shaft rotatable about the axis of rotation and spaced radially outwardly relative to the first shaft. A speed change mechanism is driven by the second shaft. A fan includes a fan rotor driven by the speed change mechanism such that the fan and the first shaft rotate at a slower speed than the second shaft. At least one inducer stage is positioned aft of the fan and is coupled for rotation with the fan rotor.

Abstract: A fan includes a first motor portion, a first impeller fixed to a first rotating portion of the first motor portion, a second motor portion arranged along a central axis of the first motor portion, a second impeller fixed to a second rotating portion of the second motor portion, a tubular wind channel portion arranged to surround the first and second impellers, and support ribs arranged to join the wind channel portion to the first and second motor portions. The first impeller includes first blades arranged in a circumferential direction about the central axis and the second impeller includes second blades arranged in the circumferential direction, a rotation direction of the second impeller is opposite to a rotation direction of the first impeller. A surface of each first blade which faces the second impeller is concave. A surface of each second blade which faces the first impeller is concave.

Abstract: A supersonic compressor system. The supersonic compressor system includes a casing that defines a cavity that extends between a fluid inlet and a fluid outlet, and a first drive shaft that is positioned within the cavity. A centerline axis extends along a centerline of the first drive shaft. A supersonic compressor rotor is coupled to the first drive shaft and is positioned in flow communication between the fluid inlet and the fluid outlet. The supersonic compressor rotor includes at least one supersonic compression ramp that is configured to form at least one compression wave for compressing a fluid. A centrifugal compressor assembly is positioned in flow communication between the supersonic compressor rotor and the fluid outlet. The centrifugal compressor assembly is configured to compress fluid received from the supersonic compressor rotor.

Abstract: Exemplary embodiments of the present disclosure are directed to a 2-stage supercharging unit having a housing unit which integrates within it a high-pressure charger and a low-pressure charger. The rotor axes of the two chargers are vertical with respect to the housing unit, which can be screwed directly via the housing base to the side of an internal combustion engine. As a result, increased flexibility is made possible with regard to the connection of the supercharging unit to the cooler and to the internal combustion engine, whereby the structural volume of the supercharging assembly can be additionally reduced.

Abstract: A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to a bypass area is less than about 170.

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

Abstract: In one exemplary embodiment, a gas turbine engine includes a fan, a speed reduction device driving the fan, and a lubrication system for lubricating components across a rotation gap. The lubrication system includes a lubricant input. A stationary first bearing receives lubricant from the lubricant input and has a first race in which lubricant flows. A second bearing for rotation is within the first bearing. The second bearing has a first opening in registration with said first race such that lubricant may flow from the first race through the first opening into a first conduit. The first bearing also has a second race into which lubricant flows. The second bearing has a second opening in registration with the second race such that lubricant may flow from the second race through the second opening into a second conduit. The first and second conduits deliver lubricant to distinct locations.

Abstract: Provided is a compression system including: at least one impeller; a gear train configured to the at least one impeller; a main drive shaft configured to drive the gear train; and a housing comprising an impeller container configured to house the at least one impeller and a gear train container configured to house the gear train.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan.

Abstract: A fluid-driven power generating apparatus is a power generator in form pipes with either water wheels or balls with circumferential indents rotating therewithin. The water wheels or the balls are rotated by the fluid flow within the pipes. Each of the water wheels or each the balls has a wheel axle or a ball wheel axle which is encircled by a metal coil. Each metal coil is rotated by the fluid flow within a magnetic field produced by the electromagnetic layer attached to each of the pipes. Through the rotations of the metal coil within the magnetic field, electricity is thus created and stored in an energy storage device. Another variation of the present invention is a closed-system fluid-driven power generating apparatus with mercury as the driving fluid. The present invention can be incorporated into plumbing, dip, sprinkler systems as well as watercrafts such as ships, submarines, jet skis, etc.

Abstract: A fluid heating and pumping system comprising a housing that has an inlet and outlet opening as well as a plurality of turbine chambers. Each of the turbine chambers has: an inlet end, outlet end, is mounted to a driveshaft, a stator and rotor, and is constructed to create a circuitous flow path for fluid flow. Each of the rotors is: designed to move the fluid through the housing, and has a plurality of rotor vanes with each having a fin at the inlet end. The fin extends past the plane of an adjacent rotor vane to extend the circuitous flow path through the rotors. The fins, shearing plane, and outlet orifice all create thermal energy as the fluid is transferred along and between the rotor and stator vanes, through the shearing plane and between the adjacent turbine chambers as the fluid flows.

Abstract: An axially-split radial turbine includes a forward rotor section and an aft rotor section being mechanically and abuttingly coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split radial turbine. The axially-split radial turbine can be provided as part of a gas turbine engine.

Abstract: The ribbon drive generation apparatus is comprised of a ribbon-like curved shape, composed either of metal or other suitable material, attached to a containment tube, peripheral rings, shaft, or porous central tube, with the complete apparatus being contained in a tube having a constant diameter for the length of the tube. The ribbon can be peripherally mounted to the containment tube and optionally to a central porous tube. In this form the containment tube rotates and can form part of a rotor for a generator apparatus. The optional central porous tube can also be used as a bearing surface or, if attached to the inside edge of the ribbon, a power take-off shaft.

Abstract: Arrangements of turbines are described. The turbines are staggered or aligned in the downwind direction.

Abstract: A blower apparatus comprises a box-like main frame provided with a main-frame inlet port and a main-frame outlet port in positions confronting each other, and a plurality of centrifugal blower units for suctioning through a blower inlet port air taken inside of the main frame from the main-frame inlet port and discharging the air from a blower air outlet toward the main-frame outlet port. The main frame is provided with a maintenance opening in one of the surfaces other than the surfaces having the main-frame inlet port and the main-frame outlet port for the purpose of checking the inside of the main frame, and the plurality of centrifugal blower units are disposed one another in a direction toward the maintenance opening so that a difference in discharging spatial distances from the blower air outlets of the adjoining centrifugal blower units to the main-frame outlet port is equal to or greater than an outer diameter of an impeller of the centrifugal blower unit located nearest to the maintenance opening.

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 power-generation system is provided. The system includes a plurality of vertical axis wind turbines (VAWTs). Each VAWT includes an upstanding support structure, a central shaft positioned along a central axis of the VAWT, a plurality of struts extending from the central shaft, and a plurality of blades, each blade positioned at an end of a corresponding strut and oriented substantially vertically. The VAWTs are grouped in sets that are arranged in rows, and are separated from each adjacent VAWT by a distance of approximately one rotor diameter.

Abstract: A serial axial fan includes first and second axial fans. The first axial fan preferably includes a first motor portion, a first impeller, and a first housing. The second axial fan preferably includes a second motor portion, a second impeller, and a second housing. In the first impeller, an angle defined by a rotational plane of the first impeller with a chord of each blade of the first impeller on an imaginary cylindrical surface centered about a central axis increases as the radius of the imaginary cylindrical surface increases.

Abstract: The ribbon drive generation apparatus is comprised of a ribbon-like curved shape, composed either of metal or other suitable material, attached to a containment tube, peripheral rings, shaft, or porous central tube, with the complete apparatus being contained in a tube having a constant diameter for the length of the tube. The ribbon can be peripherally mounted to the containment tube and optionally to a central porous tube. In this form the containment tube rotates and can form part of a rotor for a generator apparatus. The optional central porous tube can also be used as a bearing surface or, if attached to the inside edge of the ribbon, a power take-off shaft.

Abstract: A fan assembly includes a first fan and a second fan stacked together. Each of the first fan and the second fan includes a frame and a supporting base received in the frame. Several extending portions extend from a bottom of the frame of the first fan. A buckling block is formed on an inner side face of each of the extending portions. Several receiving portions are formed at a top of the frame of the second fan corresponding to the extending portions, respectively. A positioning groove is defined in each of the receiving portions. The buckling blocks are engagingly received in the positioning grooves.

Abstract: A centrifugal blower system includes: a) a series of blower units, each blower unit in the series comprising a casing having an axial inlet and a radial outlet, an impeller disposed within the casing for drawing a gaseous medium at a first pressure into the inlet and expelling gaseous medium at a second higher pressure through the outlet and a motor for driving the impeller; and, b) a duct connecting the outlet of at least one blower unit in the series with the inlet of at least one other blower unit in the series.

Abstract: A fan includes a fan frame, a front impeller and a rear impeller. The fan frame has a frame body and a plurality of connecting elements. The front impeller has a first bushing disposed at the central portion of the frame body. Two ends of each connecting element are respectively connected with the frame body and the first bushing. The rear impeller has a second bushing partially telescoped into the first bushing.

Abstract: A fan apparatus includes a casing and a fan unit. The casing is a hollow member having an inlet and an outlet. The fan unit has an inlet and an outlet, and includes a plurality of axial fans. The fan unit is disposed on the inside of the casing, and the inlet of the fan unit is disposed in the vicinity of the inlet of the casing. The position of the fan unit within the casing can be varied in order to alter the air flow and static pressure of the air discharged by the fan apparatus.

Abstract: An electric turbine compressor fan for hybrid propulsion wherein the compressor contains one or more rotor stages (compressor and diffuser), each being driven by one or more electric ring motors, such that the compressor rotor stages are designed and tuned more precisely to the compression ratio to be attained within the turbine design operating characeristics, thrust requirements and flight envelope.

Abstract: A flow-guiding device, connected between two fans disposed in series and rotating in the same rotation direction, includes a main frame and a plurality of flow-guiding pieces. The flow-guiding pieces are connected with the main frame. Each of the flow-guiding pieces is disposed corresponding to the stationary flow guiding device of the above fan so as to form a completed flow guiding device. A fan assembly including the flow-guiding device is also disclosed.

Abstract: A fan assembly includes two fans, and a number of rigid bars. The fans are connected in series. Each of the fans includes an impeller. The impellers of the fans rotate in opposite directions. The rigid bars extend through the fans and are fixed to the fans, to counteract opposing torque forces produced by the fans.

Abstract: A fan frame has at least one protrudent connector and at least one recessed connector. The at least one protrudent connector is formed on a corner of a surface of the fan frame. The at least one recessed connector is formed on another corner of the same surface of the fan frame, opposite to the at least one protrudent connector and corresponding to the at least one protrudent connector of another same fan frame. Two fan frames can be securely connected against each other by engaging corresponding protrudent and recessed connectors.

Abstract: A novel supersonic compressor is provided by the present invention. In one embodiment, the novel supersonic compressor comprises a fluid inlet, a fluid outlet, and at least two counter rotary supersonic compressor rotors, said supersonic compressor rotors being configured in series such that an output from a first supersonic compressor rotor having a first direction of rotation is directed to a second supersonic compressor rotor configured to counter-rotate with respect to the first supersonic compressor rotor.

Abstract: A stacked pump arrangement for mixed-media flow includes a first, self-priming, centrifugal pump with a volute having an inlet and an outlet and a second straight centrifugal pump mounted to an upper portion of the first centrifugal pump, the second straight centrifugal pump also having a volute with an inlet and an outlet. A transition chamber is connected, at one end, to the first centrifugal pump volute outlet and is connected, at another end, to the second straight centrifugal pump volute inlet.

Abstract: A stacked pump arrangement for mixed-media flow includes a first, self-priming, centrifugal pump with a volute having an inlet and an outlet and a second straight centrifugal pump mounted to an upper portion of the first centrifugal pump, the second straight centrifugal pump also having a volute with an inlet and an outlet. A transition chamber is connected, at one end, to the first centrifugal pump volute outlet and is connected, at another end, to the second straight centrifugal pump volute inlet.

Abstract: A method of operating variable pitch fans in series to cool an operating computer system. The method comprises running a first variable pitch fan with blades positioned at an operational pitch to induce airflow through the computer system and through a second variable pitch fan disposed in series with the first fan, and, simultaneously, not running the second variable pitch fan with blades positioned for minimal impedance to the airflow. In response to detecting a failure condition of the first fan, the method includes running the second fan with blades positioned at an operational pitch to induce airflow through the computer system and through the first fan, and, simultaneously, not running the first fan with blades positioned for minimal impedance to the airflow. Preferably, the method includes locking the rotor of a fan that is not running, and locking the blades of the non-running fan in a minimal impedance position.

Abstract: A serial axial fan unit includes first and second motors with their base portions, i.e., first and second base portions axially facing each other. A motor gap is arranged axially between the first and second base portions. An axial length of the motor gap is preferably in a range from approximately 0.3 mm to approximately 2.0 mm. This configuration reduces transmissions of vibration of each of the first and second motors to the other, thereby reducing vibration interference between the first and second motors.