Abstract: A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.

Abstract: A tiltrotor has a range of motion between a forward flight position and a hovering position, where a pylon and the tiltrotor are coupled via a telescoping actuator, a rigid bottom bar, and a fixed hinge that is attached between the rigid bottom bar and the tiltrotor. The tiltrotor moves from the forward flight position to the hovering position includes extending the telescoping actuator so that the tilt rotor rotates about the fixed hinge.

Abstract: A pylon portion includes a first surface that attaches to an upper surface of a spar in a wing, where the pylon portion and a rotor portion protrude aft of the wing. A second surface attaches to a lower surface of the spar in the wing. The pylon portion also includes an intake air vent; a horizontal mounting surface; a rotor controller that is coupled to the horizontal mounting surface; and a heat sink that couples to the horizontal mounting surface and dissipates heat from at least the rotor controller. The rotor portion is moveably coupled to the pylon portion such that one or more rotor blades included in the rotor portion are able to move between: (1) a first position below the wing that is associated with a vertical flight mode and (2) a second position aft of the wing that is associated with a forward flight mode.

Abstract: A blower device includes a rotor rotatable about a central axis extending in a vertical direction, an impeller attached to the rotor, and an annular ring centered on the central axis. The rotor includes a rotor cylindrical portion that extends in the axial direction and a flange that extends radially outward from the rotor cylindrical portion. The impeller includes an annular impeller base centered on the central axis. The ring is connected to the impeller base in the axial direction. The flange is held between the impeller base and the ring in the axial direction.

Abstract: A wind turbine nacelle comprising a plurality of power generating components and a fluid system, wherein the nacelle includes a nacelle cover comprising a lower cover or ‘base’, a roof and side walls, thereby defining an interior space of the nacelle, wherein the fluid system includes a fluid tank that is integrated into the nacelle cover. The invention extends to a panel of a wind turbine nacelle cover, wherein the panel is configured to define at least apart of, or is coupled to, a fluid tank of a fluid system of the wind turbine.

Abstract: A utility power generator includes a flywheel that includes an outer perimeter that is operable between a planar position and a plurality of sinusoidal positions. A hub is concentrically positioned within the flywheel, wherein the hub defines a rotational axis of the flywheel. An axial fitting traverses relative to the hub and along the rotational axis in an axial direction as the flywheel operates between the planar position and the plurality of sinusoidal positions. The flywheel, the hub and the axial fitting are rotationally linked to synchronously rotate about the rotational axis. Rotation of the flywheel biases the axial fitting toward the planar position. A transfer fitting is coupled to at least one of the flywheel, the hub and the transfer fitting. Rotation of the flywheel about the rotational axis operates the transfer fitting to operate a tool.

Abstract: A propeller fan includes a cylindrical shaft portion provided on a rotation axis of the propeller fan; a plurality of blades provided on an outer peripheral side of the shaft portion; a connection portion provided adjacent to the shaft portion and connecting two of the plurality of blades that are adjacent to each other in a circumferential direction of the propeller fan; a first rib provided on at least one of a pressure surface of each of the plurality of blades and a surface of part of the connection portion that is located on a downstream side in the flow of air, and a second rib provided on at least one of a negative-pressure surface of each of the plurality of blades and a surface of part of the connection portion that is located on an upstream side in the flow of air.

Abstract: A gas turbine engine and a method of tuning a rotor in the gas turbine engine wherein the rotor includes an array of blades extending from a rotor hub each having an airfoil mounted to a blade platform. The method includes adding or removing material from bladed rotor projections to alter the mass of the rotor and change the frequency of the respective airfoil.

Abstract: An impeller includes: a main body portion which is increased in diameter from one side to another side in a rotation axis direction; a thinned portion, which is formed in a back surface of the main body portion so as to be oriented toward the another side in the rotation axis direction, and is recessed toward the one side in the rotation axis direction; a plurality of full blades which are formed on an outer circumferential surface of the main body portion so as to be oriented toward the one side in the rotation axis direction; and a plurality of splitter blades, which are formed on the outer circumferential surface, and have end portions being located on the one side in the rotation axis direction and being positioned on the another side in the rotation axis direction with respect to the full blades.

Abstract: In an axial flow fan according to the present invention, a plurality of blades rotate about a rotation axis of the blades to convey a fluid. In the axial flow fan, the plurality of blades each have a leading edge at a leading side in a rotational direction, a trailing edge at a trailing side in the rotational direction, and an outer peripheral edge connecting the leading edge and the trailing edge. The leading edge of one of the plurality of blades and the trailing edge of another blade adjacent to the leading edge of the blade in the rotational direction are connected by a plate-shaped connection portion. The plurality of blades each have at least one plate-shaped reinforcement rib extending from a periphery of the rotation axis toward the outer peripheral edge of the blade.

Abstract: Provided is a turbo fan capable of lowering difficulty in manufacturing and contributing an improvement in a reduction of costs while performance related to an improvement in ventilation efficiency, a decrease in operation noise, or the like. The turbo fan includes a main plate rotatably provided around a rotational axis, a side plate having a suction hole formed in a center thereof, and disposed to be separated from one surface of the main plate in a rotational axial direction and a plurality of blades disposed and fixed between the main plate and the side plate. The main plate is located inside the suction hole when viewed from the rotational axial direction.

Abstract: A hydrokinetic generator including: a submersible housing defining a conduit therethrough for the flow of a fluid; a turbine mounted to the housing comprising at least one impeller located in the conduit for rotation by said flow; and at least one electrical generator coupled to the at least one turbine for converting mechanical energy from the turbine to electrical energy, the electrical generator including a plurality of elongate members bearing one or more magnetic regions, the elongate members being disposed about the at least one impeller and fast therewith; and a number of windings located within material of the housing and arranged for electromagnetic interaction with said magnetic regions whereby in use rotation of the impeller moves the magnetic regions past the windings to thereby induce an electrical current in the windings.

Abstract: A method optimizing a composite material blade profile for a rotor wheel of a turbine engine, and a blade including a tang compensated by the method. The method includes: compensating a blade airfoil by subdividing the airfoil into slices, and for each airfoil slice and a predetermined rotation speed of a disk of the wheel, calculating centrifugal force applied to the slice, calculating an aerodynamic force moment acting on a bottom section of the slice, and calculating shift values to be applied to a center of gravity of the slice to cancel the aerodynamic force moment; and compensating the blade tang by calculating centrifugal force applied to a blade portion situated beyond the airfoil neck, calculating an aerodynamic force moment acting on a bottom section of the blade tang, and calculating shift values to be applied to a center of gravity of the blade tang to cancel the aerodynamic force moment.

Abstract: A compressor for a gas turbine, in particular of an aircraft engine, having a plurality of arrays (10-25) of flow-directing elements that are serially disposed in a through flow direction from a compressor inlet to a compressor outlet (1, 2); at least one upstream, mistuned array (20) of flow-directing elements and at least one downstream, mistuned array (22) of flow-directing elements each having at least two types of flow-directing elements that differ structurally from one another; and at least 80%, in particular at least 95% of the rotor blades (45) of a furthest downstream rotor blade array (25) that, in the through flow direction, is configured downstream of the downstream, mistuned array (22) of flow-directing elements, being mutually identically constructed.

Abstract: A mistuned airfoil assembly for a gas turbine engine is disclosed. The mistuned airfoil assembly may comprise a hub and airfoils extending radially from the hub. The airfoils may consist of first airfoils and at least one second airfoil. The first airfoils may be formed from a first titanium alloy and the at least one second airfoil may be formed from a second titanium alloy. The first titanium alloy and the second titanium alloy may have different natural frequencies.

Abstract: A rotor blade of an aerodynamic rotor of a wind turbine, comprising: at least a first and a second wing fence, with the first wing fence being arranged at the rotor blade in radial direction, in relation to an axis of rotation of the rotor, in a range between 25% and 40%, and the second wing fence being arranged at the rotor blade in radial direction, in relation to an axis of rotation of the rotor, in a range between 45% and 60%.

Abstract: Disclosed are embodiments of flow diverting lift elements which, when placed in the proper orientation and propelled through a fluid, produce a lift force with improved lift versus velocity performance. The flow diverting lift elements can produce lift for rotary lift devices such as aircraft. The flow diverting lift devices include an airfoil and a diversion wall extending from an upper surface of the airfoil. The airfoil can be an annular airfoil.

Abstract: A fan includes a stationary portion; a bearing mechanism; and a rotating portion. The rotating portion includes an impeller including a plurality of blades and an annular impeller cup arranged to support the blades. The rotor portion includes a cover portion and a cylindrical portion. The impeller is fixed to an outer circumferential surface of the cylindrical portion of the rotor portion. The outer circumferential surface of the cylindrical portion and an inner circumferential surface of the impeller cup have a joining portion therebetween. At least one of the outer circumferential surface of the cylindrical portion and the inner circumferential surface of the impeller cup includes a groove portion recessed radially from the joining portion. The groove portion includes an upward facing surface. An adhesive is arranged in the groove portion. At least a portion of the adhesive is arranged above the upward facing surface of the groove portion.

Abstract: An optical device includes a reflector and a rotation member that dissipates the heat of the reflector. The rotation member includes a base portion placed on the reflector and a plurality of blade portions that project to the side opposite to the base portion. The plurality of blade portions each include an inclined portion that is inclined with respect to the base portion.

Abstract: A power tool having a built-in fan, the fan including a plurality of blades at uneven pitches. The fan includes a centrifugal fan which blows out air in all radial directions. The fan is provided with means for correcting unstable outflow which may be caused by the uneven pitches between the blades. The blades have unevenly configured inducers for correcting unstable outflow.

Abstract: A composite cooling fan includes a frame, a fan blade and a lateral valve. The frame has an air hole penetrating the frame and a lateral air outlet locating on one side of the frame and connecting with the air hole. The fan blade is disposed in the air hole and includes an impeller, multiple axial blades surrounding the impeller and multiple centrifugal blades surrounding the axial blades. The lateral valve is disposed on the lateral air outlet and includes a valve stem and a switch baffle linked with the valve stem. The valve stem is used for making the switch baffle at the lateral air outlet open or close.

Abstract: A gas turbine engine and a method of tuning a rotor in the gas turbine engine wherein the rotor includes an array of blades extending from a rotor hub each having an airfoil mounted to a blade platform. The method includes adding or removing material from bladed rotor projections to alter the mass of the rotor and change the frequency of the respective airfoil.

Abstract: According to the present invention, use is made of a drag-type blade in which the blade is constituted vertically and in multiple blocks while the inside thereof is formed so as to have an overlapping region, thereby achieving an aerodynamic characteristic whereby there is a large initial torque for rotating the blade of the wind energy electricity generator from the stationary state such that the rotational moment is increased. On the outside thereof, use is made of airfoil-type blades, thereby obtaining rapid rotational acceleration with tip-speed ratio no less than 1.0 and effecting wind energy electricity generation even with a low wind velocity regardless of the wind direction, and thus the present invention is economic and can be installed at low cost unaffected by place or position and is environmentally friendly while nevertheless being able to effect highly efficient wind energy electricity generation.

Abstract: Turbines and methods for their use, for generating power utilizing the flow of water or other fluids. In certain embodiments, turbines with helical blades oriented to efficiently intercept off axis or angular fluid flow, such as presented by whirlpool water flow patterns. In certain preferred embodiments, turbines having helical blades with major blade surfaces oriented to take advantage of whirlpool or circular-angle flow patterns, depending on geographic location of installation in the northern or southern hemisphere. In still other embodiments, turbines in which the pitch of rotor and/or helical blade surfaces is variable.

Abstract: A method of determining a common blade frequency of a rotor of a wind turbine is provided. The method includes measuring a vibration quantity representative of a vibration of a component of the wind turbine, and determining the common blade frequency based the measured vibration quantity.

Abstract: A heat-dissipation fan including a base and an impeller disposed at the base, wherein the impeller includes a plurality of first blades, a plurality of second blades and a plurality of connection ribs. Each of the first blades and each of the second blades are arranged alternately. Each of the connection ribs comprises a first edge, a second edge and a third edge. The first edge is connected with the first blade, the second edge is connected with the second blade, the third edge is connected with the first edge and the second edge, and the third edge and the second blade are spaced apart to form a first vent. The first edge comprises a first length, the second edge comprises a second length, and the first length is larger than the second length.

Abstract: A structural duct apparatus includes a cross flow turbine for use in a fluid flow. The turbine has at least one straight vertical aerofoil blade and at least one helical aerofoil blade slanted toward the direction of rotation. Inner and outer walls of the duct apparatus provide an inner diffuser flow passageway that houses turbine power take off modules with the outer surfaces of the duct influencing flow direction so that where there are at least two ducts an open flow barrage is advantageously formed.

Abstract: A centrifugal boost pump inducer section includes a plurality of inducer main blades, and a plurality of splitter blades, each of which includes normal to the blade mean line cross sectional surfaces distributed over the length of the blades, the cross sectional surfaces defined as a set of R-coordinates, theta-coordinates and Z-coordinates relative to an impeller outer diameter set out in one set of tables. A centrifugal boost pump impeller section includes a plurality of impeller main blades, a plurality of primary splitter blades, and a plurality of secondary splitter blades, each of which includes normal to the blade mean line cross sectional surfaces distributed over the length of the blades, the cross sectional surfaces defined as a set of R-coordinates, theta-coordinates and Z-coordinates relative to an impeller outer diameter set out in another set of tables.

Abstract: A submersible centrifugal pump is disclosed. The submersible centrifugal pump includes a pump housing having a pump intake disposed generally opposite a pump outlet. A shaft extends at least partially through the pump housing and is adapted to be driven by a submersible motor. A centrifugal impeller is attached to the shaft and has an opening for fluid intake. A diffuser is disposed corresponding to the centrifugal impellers to form a pump stage. And an auger is coupled to the shaft.

Abstract: A fan, for a ventilation assembly has blades extending from a cup-shaped central hub. The hub has an annular side wall and a bottom wall defining a receptacle for an electric motor. The hub has internal ribs for ventilation of the motor. Each rib has a longitudinal portion which extends along the side wall, a radial portion which extends along the bottom wall and an intermediate portion having an arcuate, transversely protruding profile. The longitudinal portion has a profile whose spacing from the side wall of the hub increases, from a minimum value remote from the bottom wall to a maximum value adjacent the bottom wall.

Abstract: A fan module includes a housing and at least one impeller. The housing includes first and second air channels. The housing further includes an axial air inlet in communication with the first air channel and a radial air inlet in communication with the second air channel. The housing further includes at least one radial air outlet in communication with the first and second air channels. The at least one impeller draws external air into the housing via the axial air inlet or the radial air inlet and expels air out of the housing via the at last one radial air outlet. By such an arrangement, external air can be guided into the fan module via different directions, providing an enhanced cooling effect.

Abstract: A rotor for a gas turbine engine includes a plurality of turbine blades extending radially outwardly of a rotor body. A plurality of purge blades are positioned to rotate with the rotor body, and to drive air radially outwardly toward the turbine blades.

Abstract: A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between the passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, hi other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.

Abstract: An improved automotive pump assembly includes a volute pumping chamber configured to operably contain a rotatable impeller which, when driven, draws fluid into a fluid inlet and pumps the fluid to and through a fluid outlet. The volute chamber has an exterior sidewall with a constant internal first radius over a first sidewall portion and transitions to a second sidewall portion of increasing radius. The chamber's second sidewall portion defines a first end at a sidewall transition point tangent to the constant radius sidewall segment to define a second end which is tangent to the volute chamber's fluid outlet with a second radius that is greater than the first radius.

Abstract: A fan-turbine rotor assembly includes one or more turbine ring rotors. Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring includes axial installation and radial locking of each turbine ring rotor.

Abstract: Exhaust apparatus for exhausting “dirty” exhaust gases accept a core flow of such exhaust gases and combine that with an annularly-surrounding “rooftop” flow of ambient air for diluting the exhaust gases as well as expelling the diluted flow in a forcibly expelled plume in order to ensure that the “effective” expulsion distance of the expelled diluted flow is at least the physical length of the exhaust apparatus plus the gains gotten from efflux velocity and flowrate.

Abstract: A blade arrangement for a turbo engine, in particular a gas turbine, with a rotor and several blades fastened thereto, which are configured to be systematically different, wherein at least two adjacent blades have systematically different shrouds (12, 22) and/or inner blade platforms (11, 21).

Abstract: A wind turbine has a spindle, a first fan device and a second fan device. The first fan device is rotatably mounted around the spindle and has a first pivot hole and at least two first blades. The first pivot hole is formed through a center of the first fan device and is mounted around the spindle. The at least two first blades are radially mounted on and protrude from an external surface of the first fan device. The second fan device is rotatably mounted around the spindle, abuts with the first fan device and has a second pivot hole and at least two second blades. The second pivot hole is formed through a center of the second fan device and is mounted around the spindle. The at least two second blades are mounted on and protrude from an external surface of the second fan device.

Abstract: Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.

Abstract: A wind power turbine includes a frame, a drag-type fan unit and a lift-type fan unit. The frame has a base, a shaft, an electricity generator and a plurality of air-guiding plates. The air-guiding plates are disposed on the base, and the shaft has one end connected to the electricity generator. The drag-type fan unit has a plurality of drag-type blades coupled to an outer circumference of the shaft. The lift-type fan unit has a plurality of lift-type blades disposed around the drag-type blades. Each of the air-guiding plates has a first side and a second side, and the first and second sides are parallel to the shaft. An air inlet is formed between the first sides of adjacent two of the air-guiding plates, and an air outlet is formed between the second sides of adjacent two of the air-guiding plates. The air inlet is larger than the air outlet.

Abstract: A centrifugal boost pump inducer section includes a plurality of inducer main blades, and a plurality of splitter blades, each of which includes normal to the blade mean line cross sectional surfaces distributed over the length of the blades, the cross sectional surfaces defined as a set of R-coordinates, theta-coordinates and Z-coordinates relative to an impeller outer diameter set out in one set of tables. A centrifugal boost pump impeller section includes a plurality of impeller main blades, a plurality of primary splitter blades, and a plurality of secondary splitter blades, each of which includes normal to the blade mean line cross sectional surfaces distributed over the length of the blades, the cross sectional surfaces defined as a set of R-coordinates, theta-coordinates and Z-coordinates relative to an impeller outer diameter set out in another set of tables.

Abstract: A turbo-molecular pump, includes a blade pumping section having a plurality of rotor blades and a plurality of stator blades which are alternately arranged in plural stages along an axial direction of the pump, and a thread groove pumping section having a cylindrical-shaped screw stator, and a rotor cylinder adapted to be rotated inside the screw stator. The rotor cylinder has a lower edge surface located on an upstream side relative to a downstream edge of the screw stator with respect to the axial direction. The turbo-molecular pump of the present invention can minimize flying-out of broken pieces of the rotor cylinder from a discharge port.

Abstract: A vertical wind power generator with automatically unstretchable blades is disclosed. The vertical wind power generator includes a generator, a linkage mechanism, a lifting type blade assembly, a resistance type blade assembly and a drive unit. The drive unit provides power for driving the linkage mechanism. The drive unit has an output shaft movable between a first position and a second position. When the output shaft is moved to the first position, the linkage mechanism is driven to move the resistance type blades to a stretched position. When the output shaft is moved to the second position, the linkage mechanism is driven to move the resistance type blades to an unstretched position.

Abstract: A machine train includes a drive unit, preferably a steam turbine with axial exhaust flow, a geared turbine machine, and an additional compressor. The geared turbine machine has an integrated gear train with a drive pinion for driving turbine machine rotors via a large gear, and an output pinion of a rotational speed reduction power gear for driving the additional compressor.

Abstract: Method for configuring the constituent elements of hollow helical wheels or their cages, which is based on using geometrical figures whose centers serve as reference for constructing them and defining their areas. Values of angles, offsets of the centers, and pitches, make it possible to control all the constituent elements.

Abstract: A high-speed air spindle including a spindle 1 supported by a first bearing 3 at the leading end side in the axial direction and a second bearing 2 at the rear end side, a driving air turbine 4 fixed in a spindle portion between the first bearing 3 and the second bearing 2, a speed-increasing air turbine 5 fixed in a spindle portion ahead of the first bearing 3, and an air passage 9 of an exhaust of compressed air supplied in the driving air turbine 4, flowing in the sequence of the first bearing 3 and the speed-increasing air turbine 5.

Abstract: Disclosed are an impeller of a suction-enforced type, and a fan-motor for a vacuum cleaner having the same. The fan-motor having the impeller of the suction-enforced type includes: a motor housing; a motor installed in the motor housing; an impeller casing coupled to the upper portion of the motor housing; the impeller of the suction-enforced type installed in the impeller casing and connected to a rotation shaft of the motor; and a guide vane installed at the lower portion of the impeller of the suction-enforced type, for guiding the air sucked into the impeller casing to the motor side. As a result, suction efficiency of the impeller is improved, and thus efficiency of the fan-motor for the vacuum cleaner is improved.

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: An enhanced pump assembly includes an impeller and volute casing designed to provide high operating pressures (“P”) and flow rates (“Q”) with low energy usage. The impeller has a central shaft carrying radially projecting curved primary vanes, and each primary vane also has a twist in the radial direction. Secondary impeller vanes define triangular connecting fillet-like wall segments connecting each primary vane to the impeller shaft. The casing of the pump has a slight spiral deviation so that the pump chamber's radial sidewall flares away from the swept area of the impeller's vanes to define a fluid outlet that contributes to higher P-Q performance, especially when pumping colder fluids.

Abstract: Disclosed is a compact and integrated fan, pump, and heat exchanger system where air-cooling is performed via the fan, liquid cooling is performed via a pump, and heat exchange fins in thermal contact with a fluid channel act as a heat exchanger. Heated fluid is carried inside the fluid channel, where heat therein is conducted to the fins. The air flows around the outside surfaces of the fins so that the heat transfers from the heated fluid into the air stream.