Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.

Abstract: An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. Each of the star gears is supported on a respective journal bearing. Each journal bearing includes an internal central cavity and at least one passage that extends radially from the internal cavity to a peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.3.

Abstract: An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.

Abstract: A geared architecture with a flex mount for a fan drive gear system.

Abstract: An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing. The epicyclic gear train has a gear reduction ratio of greater than or equal to about 2.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages.

Abstract: A gas turbine includes at least one multi-stage compressor unit 2, with the compressor unit 2 including several, independent compressor modules 3-5, which, independently of each other, are rotatably borne on a drive shaft 1 and are each engageable with the drive shaft 1 by at least one clutch unit 9-11.

Abstract: A geared architecture with a flex mount for a fan drive gear system.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.

Abstract: A turbine engine includes an input shaft and a fan shaft rotatable about an axis. The fan shaft supports fan blades. An epicyclic gear train is connected between the input shaft and the fan shaft. The epicyclic gear train includes a plurality of star gears, a carrier supporting the plurality of star gears, a sun gear that meshes with the plurality of star gears and a ring gear surrounding and meshing with the plurality of star gears such that the sun gear is rotatable in a first direction and the ring gear is rotatable in a second, opposite direction. The ring gear includes first and second portions that each have an inner periphery with teeth. The first and second portions include respective recesses facing one another to provide an internal annular cavity.

Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.

Abstract: A bushing for use in a planetary gear system has a cylindrical body portion defining a bore extending along a central axis to be received on a planetary gear shaft. A tab extends axially beyond a nominal body portion of the bushing and is received in a notch in a thrust washer adjacent to the bushing to prevent rotation of the thrust washer. A gear cage and an air turbine starter incorporating the bushing, along with a method of installing the bushing are also disclosed.

Abstract: A pump for processing molten metal having an enlarged tubular body which houses a centrifugal lifting pump at its bottom end. The bottom end has a curved shape that aids in the formation and sustainability of: a) a forced vortex; b) a highly forced vortex; and c) a super forced vortex, depending on the application when it which receives the ejected molten metal from the lifting pump's impeller. The lifting pump is controlled to cause the vortex to climb up the inner wall of the body up to and out of an outlet formed in the upper end of the body. A recirculation centrifugal pump is mounted coaxially to and rotates with the lifting impeller.

Abstract: A compact, strengthened rotor assembly of a radiator fan, the radiator fan having a baseplate, a stator assembly, a rotor assembly and a reverse axle. The reverse axle is erected at the center of the baseplate or stator assembly and protruded upwards. The rotor assembly has a hub with a top wall and a circumferential wall. A magnetic ring is set annularly into the circumferential wall. Several blades are set annularly onto the exterior of the circumferential wall. A metal sleeve is located at the center of the top wall and protruded downwards. A mating portion is set at the top of the metal sleeve for mating with the top wall. A holding portion is formed within the metal sleeve for assembly and positioning of a bearing, and the bearing is used for pivoting of the reverse axle. The thickness of the top wall ranges between 0.2 mm and 0.5 mm.

Abstract: An exemplary turbine engine assembly includes a first shaft that is rotatably driven by a second shaft of a gas turbine engine and a compressor hub driven by the first shaft. The compressor hub is within a compressor section of the gas turbine engine. An epicyclic gear train is driven by the first shaft. A common attachment point secures the first shaft and the compressor hub to the second shaft.

Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four (4) stages.

Abstract: A combined axle structure of a stator assembly for a radiator fan, of which said radiator fan comprises: a pedestal, a stator assembly, a rotor blade unit and a reverse axle. The pedestal includes a sustaining face and a stator assembly face. The stator assembly includes silicon-steel sheet, coil and insulated frame. The insulated frame is mated with a metal bearing block, which is designed like a cup, and includes a bottom wall and a circumferential wall. The top of the circumferential wall is positioned into the insulated frame. An axle socket is set at the center of the bottom wall, allowing for insertion of the bottom of the reverse axle. An embedded locator is set centrally into the stator assembly face of the pedestal, allowing for mating with the bottom of the metal bearing block.

Abstract: A cranking pad assembly for a gearbox of a turbomachine including a cranking pad shaft rotatably secured in a gearbox housing and engageable with a gearbox drivetrain when urged inwardly into the gearbox housing. The cranking pad shaft includes an interface for a cranking tool. An interlock pin retains the cranking tool at the cranking pad shaft and a disconnect spring is operably connected to the gearbox housing to bias the cranking pad shaft outwardly from the gearbox housing.

Abstract: Independent axial preloading of compressor and turbine disks in a gas turbine engine rotor is achieved by a dual tie shaft arrangement wherein a forward tie shaft engages forward and aft portions of a compressor hub within which the compressor disks are disposed to axially and compressively preload the compressor disks between the forward and aft portions of the compressor hub. An independent tie shaft engages an aft portion of a turbine hub within which turbine disks are disposed and an aft portion of the compressor hub to axially and compressively preload the turbine disks between the turbine and compressor hubs.

Abstract: This invention relates to an augmenter system for the increase of power generation primarily used for utilizing wind energy. The augmenter system includes an augmenter having a plurality of walls, such as flexible walls, connected to each other with supporting horizontal elongated members. The augmenter is used in conjunction with a blade system and an air flow regulation or furling system to achieve optimal power output. The augmenter includes a relatively lightweight, low cost flexible wall structure to enhance an air flow into impact impellers associated with the blade system. In one arrangement, the blade system defines a swept area with a height to diameter ratio of greater than four. In one arrangement, the blade system defines a swept area with a height to diameter ratio of greater than ten.

Abstract: The present invention relates to a turbo blower and a high speed rotation body used in the turbo blower. The turbo blower includes: i) a motor having a motor shaft; ii) a gear housing accommodating a bull gear fitted on the motor shaft and a pinion gear engaged with the bull gear; iii) a high speed rotation body that includes a rotary shaft having the pinion gear on the external circumferential surface, an impeller fitted on one end of the rotary shaft, and a rotation body housing accommodating the rotary shaft, the pinion gear, and at least one first composite bearing and partially cut off to expose the pinion gear, and is partially accommodated in the gear housing; and iv) a scroll portion covering the impeller and discharging compressed air.

Abstract: A radiator fan assembly structure has a base board with a seating surface and a stator installing surface; a stator inserting and positioning part, configured in the center of the stator installing surface of the base board; a stator set, has a silicon-steel plate, a coil and an insulate frame; and a plastic assembly seat formed integrally on the stator set, which is formed through a projection from the center of the insulate frame of the stator set. The shape of the plastic assembly seat enables it to be inserted into the stator inserting and positioning part. An axis is combined with the plastic assembly seat, with its root part fixed on the center of the plastic assembly seat. A rotor blade assembly has a wheel hub, blades, a bush, a bearing assembly and a magnet ring. The radiator fan runs smoothly and quietly.

Abstract: A gas turbine engine according to an exemplary aspect of the present invention includes a gear train defined along an engine centerline axis, and a spool along the engine centerline axis which drives the gear train, the spool includes a low stage count low pressure turbine.

Abstract: A guiding apparatus (10) for guiding movement of a pool cleaner (not shown) of the kind set forth in a pool includes a fluid flow passage (12) having an inlet (14) and an outlet (16) to which portions (18) and (20) of a pool cleaner hose are connected in use and during which the hose portion (20) connected to the outlet (16) is connected to a suction side of a pump system of a swimming pool. A turbine wheel (22) is arranged to in use be driven by fluid flow through the fluid flow passage (12) into the pump system. Pivot members (24) are in use connected to each other and are operatively connected to the hose portions (18) and (20).

Abstract: Provided is a machine unit layout system that simplifies the layout of a compressor unit and an expander unit and is extremely effective in terms of not only the reliability of the entire machine but also maintainability. Two separate compressors, a low-pressure-side compressor and a high-pressure-side compressor (11A, 11b), are disposed on either side of a steam turbine (10). Two separate expanders, a low-pressure-side expander and a high-pressure-side expander (12A, 12B), are disposed outside the low-pressure-side and high-pressure-side compressors (11A, 11b). The steam turbine (10), the low-pressure-side and high-pressure-side compressors (11A, 11b), and the low-pressure-side and high-pressure-side expanders (12A, 12B) are coupled by rotor shafts comprising a single shaft. The torque distribution between rotator shafts is optimized.

Abstract: A fan system comprises a hub, a plurality of fan blades, a drive system, and a stationary tube. The hub is configured to rotate. The fan blades are mounted to the hub. The drive system comprises a rotatable hollow output shaft. The hollow output shaft is in communication with the hub, such that the drive system is operable to rotate the hub via the hollow output shaft. The stationary tube is inserted through the hollow output shaft. The stationary tube is configured to remain stationary as the hollow output shaft rotates. Wires and the like may be passed through the stationary tube, to reach an accessory mounted at the bottom of the stationary tube. The fan system may also include a detector, such as a heat detector, a smoke detector, or an accelerometer. The detector may power down the fan system in response to detecting certain conditions.

Abstract: The utilization of double fans for engine cooling of motor vehicles is known. Said fans generate a flow of air which then serves to cool a heat exchanger, in particular a coolant radiator for motor vehicles. The double fan is herein characterized by an optimal use of the surface of the coolant radiator that is to be cooled, so as to be able to achieve a cooling performance as high as possible. The assembly of the double fan has up to now been such that a separate electric motor is provided for each blower. The double fan (1) for a heat exchanger (2), in particular a coolant radiator of a motor vehicle, has a first blower (4) and a second blower (5). According to the invention, the first driven blower (4) drives the second blower (5) by way of a transmission element (10) provided on the outer surface (11) of the first blower and an outer surface (12) of the second blower (5). The double fan is provided for a heat exchanger, in particular a coolant radiator of a motor vehicle.

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 device for holding a hydraulic turbomachine in position, the turbomachine comprising a drive shaft along which are distributed turbines designed to rotate the drive shaft when they are immersed in a moving liquid, each turbine comprising drive blades distributed around the drive shaft, the device comprising at least one post extending along at least more than half of the length of the drive shaft and formed of the stacking of at least two post portions, each post portion being associated with a turbine or with an assembly of adjacent turbines; and a first linking mechanism attached to one of the post portions and to a bearing receiving the drive shaft and arranged between two adjacent turbines; and a second linking mechanism connecting at least one of the posts to the around by a rigid connection with respect to the ground along at least one axis parallel to the liquid motion direction.

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: An air turbine starter for starting an engine includes a housing, and a flow path communicating a flow of gas therethrough; a turbine member; a clutch; and a decoupler device at least partially housed within the output member of the clutch. The decoupler device includes a first shaft portion coupled to and rotating with the output member and a second shaft portion coupled to and rotating with the engine. The first and second shaft portions are axially aligned and configured to engage each another for rotation in a first direction and to separate from each other in a second direction to decouple the output member of the clutch from the engine. The starter further includes a bearing between the inner surface of the output member and the second shaft portion for reducing friction between the second shaft portion and the inner surface of the output member when the first and second shaft portions are decoupled.

Abstract: The invention relates to an assembly between a compressor shaft trunnion and a bevel gear for driving an accessory gearbox of a turbomachine. The assembly comprises a bevel gear, a compressor shaft trunnion arranged coaxially inside the bevel gear, torque transmission means between the compressor shaft trunnion and the bevel gear, a lock nut for preventing the bevel gear from moving axially on the compressor shaft trunnion, the lock nut being suitable for being screwed onto the bevel gear and including a shoulder projecting radially outwards and suitable for coming into axial abutment firstly upstream against a stop nut screwed onto an upstream end of the compressor shaft trunnion, and secondly downstream against a bearing surface of the compressor shaft trunnion, and an anti-rotation pin for preventing the lock nut from rotating.

Abstract: Hydrogen gas compression systems that each include a multistage centrifugal compressor in which each stage has an inlet-to-outlet pressure rise ratio of about 1.20 or greater. In one embodiment, the multistage compressor includes six high-speed centrifugal compressors driven at a speed of about 60,000 rpm. The compressor has an output of more than 200,000 kg/day at a pressure of more than 1,000 psig. The compressors for the compression stages are distributed on both sides of a common gear-box, which has gearing that allows axial thrusts from the compressors to be handled effectively. Each stage's compressor has a unique impeller, which is secured to a support shaft using a tension-rod-based attachment system. In another embodiment, the multistage compressor is driven by a combustion turbine and one or more intercoolers are provided between compression stages. Each intercooler is cooled by coolant from an absorption chiller utilizing exhaust gas from the combustion turbine.

Abstract: A tip turbine engine (10) and a method of operating the engine provides increased efficiency while eliminating or educing the number of axial compressor (122) stages by moving the core airflow inlet (27) aft of the fan (24). As a result, the core airflow entering the core airflow inlet is the fan exhaust, which is already at an increased pressure. A portion of the fan exhaust is guided radially inward, then axially forward and then radially outward through compressor chambers (72) in the hollow fan blades (28) for further, centrifugal compression.

Abstract: Provided is a gear-driven turbo compressor capable of increasing a natural frequency of a shaft by shortening the length of an overhang from a radial bearing to a shaft end, reducing an effort of replacing lubricant and an environmental burden by greatly reducing the amount of the lubricant, and reducing the necessity for maintenance by reducing a problem of the radial bearing caused by depleted materials of the lubricant. The gear-driven turbo compressor includes: a gas bearing 32 which is in communication with a compressed gas compressed by an impeller 16 and rotatably supports both ends of a pinion shaft 13; and an inner gas seal 34 which is positioned between the gas bearing and a thrust collar, maintains the gas bearing to be compressed by the compressed gas, and prevents intrusion of lubricant for gears due to the compressed gas.

Abstract: A lubricating and cooling epicyclic stepdown gearing, for example in an aeroengine turbomachine, including a cylindrical casing mounted on a planet-carrier of the gearing and forming a centrifugal scoop surrounding stationary oil-delivery strips, the cylindrical casing including radial ducts feeding nozzles pointing towards zones where the planet gears mesh with outer ring(s) of the gearing.

Abstract: An example gear arrangement includes a gearbox shaft and a journal shaft. The journal shaft establishes an opening that receives an end portion of the gearbox shaft. The gearbox shaft is configured to rotate the journal shaft. The journal shaft is configured to selectively rotatably couple with another shaft. The journal shaft is allowed to align to the bearing surface while the gearbox shaft allows for misalignment between the accessory and gearbox drive.

Abstract: A passive fan includes a frame, at least one impeller and at least one driving device. The impeller is disposed in the frame. The driving device is disposed in the body of the frame and separated from the impeller, and drives the impeller to rotate. The driving device is an independent motor, a driver, a rotating wheel or a driving gear.

Abstract: The present invention relates to a charging device (1), in particular an exhaust-gas turbo charger for a motor vehicle, comprising a shaft (3) which is supported in a housing (2), and which carries a turbine wheel (6) on the turbine side, and a compressor wheel (8) on the compressor side, wherein the shaft (3) is supported by means of at least one bearing device (9) in the housing (2), wherein a lubricant supply channel (10) is provided through which the bearing device (9) is supplied with lubricant, wherein in the lubricant supply channel (10), a filter device (11) with at least one filter element (12) is arranged.

Abstract: The invention describes a turbo-machine with blade wheels, comprising a housing (2), a rotor (4) which is held in a rotatable manner by the housing (1), at least two rotatably arranged blades which are distributed uniformly along a circular line of the rotor (4) and which are mounted with their axis parallel to the axis of the rotor, transmission means (7, 8, 9, 10) between each axis of the blade (4) and a sleeve (12) which is rotatable on the shaft (14) of the blade wheel. According to the invention, the first rotor (4) is assigned a second rotor (20) which is held in a rotatable manner by the first rotor (4), wherein the second rotor (20) comprises at least two rotatably arranged blades (22) which are distributed uniformly along a circular line of the rotor (20) and which are mounted with their axis parallel to the rotor, transmission means (24, 25, 26, 27, 28) between each axis of the blade (22) and the sleeve (12) which is rotatable on the shaft (14) of the rotor.

Abstract: The present invention relates to an intermediate casing of a turbojet comprising, between an inner hub and an outer cylindrical shroud, a plurality of radial arms at least one of which is hollow, a radial transmission shaft for driving the auxiliary machines being mounted rotatably in said radial arm, a first end of the transmission shaft passing through the inner hub and the second end passing through the outer cylindrical shroud. The housing is notable in that the inner volume consists of a single compartment housing the transmission shaft and forming a passageway for a lubrication fluid.

Abstract: Provided is a turbo compressor that includes: a compressor unit compressing a gas; a motor driving the compressor unit; and a motor casing accommodating the motor. In the turbo compressor, the motor casing includes: a body portion which is molded in a cylindrical shape; an annular diameter reduced portion which is connected to at least one end portion of the body portion in the rotation axis direction of the motor and of which the diameter is reduced as it moves away from the body portion; and a flat portion which is connected to the central end portion of the diameter reduced portion and is molded in a planar shape.

Abstract: A pump may include a rotatable pumping part, a drive shaft, and a coupling for transmitting rotational movement of the drive shaft to the pumping part. The coupling may include a first part which is connected to the pumping part and a second part which is connected to the drive shaft, the first part having an electrically conductive material and the second part having an element for generating a magnetic field. The second part may be moveable relative to the first part to vary the degree of interaction between a magnetic field generated by the element and the electrically conductive material. Movement of the second part relative to the first part may be caused, at least in part, by a fluid controlled actuator having a piston moveable within a cylinder which is substantially non-rotating, such that the drive shaft and the second part are rotatable relative to the cylinder.

Abstract: A turbo compressor includes an impeller fixed to one end portion of a rotation shaft by a predetermined fastening member, and a regulating portion which is used to regulate rotation of the rotation shaft during fastening of the fastening member and is provided in the other end portion of the rotation shaft. The regulating portion is formed as a recessed portion recessed from an end surface of the other end portion of the rotation shaft.

Abstract: A sealless-type centrifugal pump provides a centrifugal pump that is free from leakage without using a shaft seal mechanism. The centrifugal pump includes a casing that forms a pump chamber having a liquid inflow port and an outflow port, an impeller disposed in the pump chamber and rotatably supported by a pivot bearing, and a magnetic coupling device including a driven permanent magnet built into the impeller and a driving magnet that rotationally drives the driven permanent magnet through a partition. The impeller supported in the direction of the rotation axis with respect to the casing is driven by the magnetic coupling device, and pressure is applied to liquid introduced from the direction of the rotation axis through the inflow port to send the liquid through the outflow port in a radial direction. The magnetic coupling device is disposed on a line inclined from an impeller rotating surface to the inflow port side toward the center of the rotation axis.

Abstract: A method of assembling together titanium parts and steel parts by diffusion welding, the method interposing two thin layers of niobium or vanadium and copper respectively between a titanium part and a steel part, evacuating the assembly of parts and interposed metal layers, and subjecting the assembly to hot isostatic compression at a temperature lying in a range 900° C. to 950° C. and at a pressure lying in a range 1000 bars to 1500 bars for about two hours. The method can be applied to fabricating turbine shafts for turbomachines.

Abstract: A Savonius vertical axis wind turbine rotor, that is effective yet relatively easy to manufacture, includes spokes, vanes, and fasteners. Each spoke has a hub having a central opening, three arcuate ribs extending radially outwardly from the hub with inner (concave) and outer (convex) surfaces, and channels defined in at least one of the inner and outer surfaces. The vanes of sheet material generally conform to an inner or outer surface of a rib and have openings aligned with the channels. First fasteners pass through the openings and cooperate with second fasteners in the channels. Two of the spoke pieces may be joined by a bridging piece, and two spoke pieces by a clamp. A Savonius or helical rotor includes a generator, and a drive connecting the generator and rotor. The drive automatically increases the effective gear ratio between the generator and rotor as the speed of rotation increases.

Abstract: A casing provided centrally with a sealed structure chamber. Small-sized separate four filter elements are arranged each on opposite sides of the chamber such that inflow air from a suction section into the casing is introduced via the filter elements into the chamber. Each filter element is detachably fitted over a filter-element mount having openings at its outer periphery. Upon filter-element replacement, the filter elements are replaced individually by opening a window. An integral cast casing having compressing sections and compressed air passages integrally fabricated therewith by casting is formed with receptacles for first and second intercoolers and an aftercooler. The intercoolers and aftercooler are received in the receptacles. Outlets of the intercoolers are connected with suction sides of second- and third-stage compressors through second- and third-stage suction pipes, respectively. A blowoff silencer is arranged between the integral cast casing and an oil tank.

Abstract: According to an aspect of the present invention, there is provided a gas expander system suitable for use in a turbomachine, the gas expander system comprising: a gas expander provided with a moveable part; a magnetic gear arrangement; and a shaft; the moveable part of the gas expander being connectable to a load via the magnetic gear arrangement and the shaft, and movement of the moveable part of the gas expander being arranged to cause movement of the shaft.