Abstract: A fan impeller is part of a fan assembly designed to maximize both intake and expelled air during use. The fan impeller employs a distinct airfoil shape for the fan blades to substantially move the ambient air. A low constant blade angle and overlapping blades are employed to improve the blade lift and consequent mass flow and exit pressure. The blade stall is eliminated, as evidenced by a smoothened fan curve, for more efficient operation. The blade sweep angle is optimally arranged to control radial flow characteristics of the ambient air. Housing sidewalls are removed from the fan assembly to remove parasitic drag and improve the motion of air passing through the fan.

Abstract: The present invention relates to an integrally bladed rotor for use in a gas turbine engine. The integrally bladed rotor comprises a plurality of pairs of airfoil blades. Each pair of blades has a spar which extends from a first tip of a first one of the airfoil blades in the pair to a second tip of a second one of the airfoil blades in the pair. The rotor further comprises an outer shroud integrally joined to the first and second tips in each pair of airfoil blades and an inner diameter hub.

Abstract: A heat-dissipating device and its manufacturing process are provided for significantly increasing the number and size of blades so as to enhance the heat-dissipating performance. The heat-dissipating device has a plurality of blades arranged around the hub of the heat-dissipating device and there is an overlapped region formed between every two adjacent blades. A single mold is used to manufacture such a heat-dissipating device so that not only can the manufacturing cost be reduced but it can significantly increase the number and size of blades so as to increase the heat-dissipating efficiency.

Abstract: A crack-resistant vane segment assembly member for an industrial turbine engine is disclosed. The vane segment includes at least one internally-cooled body portion and inner and outer shroud portions. The body portions include end regions characterized by blending and transition zones that ensure heat is transferred at a non-crack-inducing rate from the shroud portions to the body portions. The vane segment assembly also includes a cooling arrangement that reduces the impact of thermal gradient-induced stresses acting at the interface between the body portions and shroud portions. The cooling arrangement cooperates with the transition and blending zones to produce synergistically-enhanced crack resistance properties.

Abstract: The flow pump has an impeller, driven in a pump chamber and having a ring of blades spaced apart from one another in the circumferential direction on at least one end face and ending at the face end of the impeller and cooperate therewith to define blade chambers. In the pump chamber, at least one feed conduit in the form of a split ring cooperates with the ring of blades on the impeller, and at least one intake opening discharging into the feed conduit is embodied in a pump chamber wall that defines the pump chamber in the direction of the pivot axis of the impeller. In an initial region at the at least one intake opening and/or in the circumferential direction of the impeller, adjoining the impeller, the feed conduit extends radially farther inward than the blade chamber bottom of the impeller, and the transition between a radially inner blade chamber bottom of the blade chambers and the associated face end of the impeller has a chamfer or rounded corner.

Abstract: A rotor shaft/hub unit for a wind energy plant with a rotor shaft provided with a rotor bearing seat which is connected to a rotor hub provided with a blade or blade bearing connection, wherein the rotor hub and rotor shaft are manufactured in one piece from bonded fiber fabrics.

Abstract: A cooling fan has a ring-shaped metal spacer, a boss of substantially a cylindrical shape made of a synthetic resin that is molded integrally with the spacer as an insert and lural blades that extend outwardly from the boss. A deep-drawn part is provided on an outer circumferential part of the spacer at an inside of the boss. A thickness of the boss is made large at around a front end side of the blade on which the largest stress is applied. A rib at an inner periphery of the boss at around the front end side of the blade is made thicker than the other ribs. Moreover, an interval between that rib and an adjacent rib is made narrower.

Abstract: The arrangement features a centrifugal impeller that exhibits relatively high operating efficiency and high pressure capability, and can be easily constructed as a single piece. The arrangement is useful where relatively high operating efficiency and low cost construction are required, and it is particularly suited for manufacture by injection molding plastic. The impeller is characterized by: a) a hub that extends to a radius less than that of the impeller inlet, allowing one piece construction by an injection molding tool with no slides or action; b) blades that extend from a radius less than the hub radius at the base of the blades, allowing the base of the blades to connect to the hub; c) an impeller top shroud that has curvature in a plane that contains the impeller axis; and d) a cylindrical area ratio between 1.0 and 2.0. The blower assembly is characterized by a separate base plate positioned in close proximity to the base of the impeller blades.

Abstract: The present invention relates to an integrally bladed rotor for use in a gas turbine engine. The integrally bladed rotor comprises a plurality of pairs of airfoil blades. Each pair of blades has a spar which extends from a first tip of a first one of the airfoil blades in the pair to a second tip of a second one of the airfoil blades in the pair. The rotor further comprises an outer shroud integrally joined to the first and second tips in each pair of airfoil blades and an inner diameter hub.

Abstract: An integrated boot, seal and impeller system is adapted for being driven by a pump shaft. The system includes an impeller unit having a plurality of radially extending blades, a hub portion, a recess in the hub portion and a tubular portion extending from the hub portion. The tubular portion is engaged to the shaft and has an outer diameter with at least one flat in the outer diameter. A seal head is slidingly engaged to the tubular portion. The seal head also has an inner diameter with at least one flat on the inner diameter to engage the outer diameter of the tubular portion. A flexible boot extends from the elastomeric blades. The boot has a distal portion adjacent to the seal head. Additionally, a biasing member is disposed in the recess and urges the seal head into engagement with the seal washer.

Abstract: A method for manufacturing an integrally bladed rotor includes fixturing a plurality of blade blanks having radially inwardly facing blade conical surfaces into a segmented blade ring assembly circumscribed around an axis. A rotor ring having a radially outwardly facing ring conical surface circumscribed around the axis is rotated to a contact speed. The rotor ring is fictionally engaged under an axially applied weld load with the blade ring assembly to effect a conical inertia weld along the mating blade conical surfaces and ring conical surface. The integrally bladed rotor includes a plurality of airfoils circumferentially distributed about and integral with a rim. The airfoils extend radially outwardly from respective airfoil bases on a radially outer flowpath surface of the rim to airfoil tips. A conical inertia weld is located between the airfoil tips and a radially inwardly facing rim surface of the rim.

Abstract: Front edges 212b of blades 212 are so constituted as to be deviated toward the upstream side in the air stream beyond an axial end surface 211a, as viewed from a direction at right angles to the axial direction of a boss 211, and the blades 212 on the root side thereof are continuous to the axial end surface 211a through smoothly curved surfaces 213. This enables the air to flow from the side of the axial end surface 211a toward the root side of the blades 212. Due to the air flowing from the side of the axial end surface 211a to the root side of the blades 212, therefore, the resistance decreases between the air and the surfaces of the blades 212 on the root side, making it possible to suppress the occurrence of stalling on the root side of the blades 212. The air on the front side of the boss 211 is effectively guided toward the outer direction (toward the blades 212), preventing a drop in the flow rate and in the fan efficiency of a blower 200.

Abstract: A method for manufacturing an integrally bladed rotor includes fixturing a plurality of blade blanks having radially inwardly facing blade conical surfaces into a segmented blade ring assembly circumscribed around an axis. A rotor ring having a radially outwardly facing ring conical surface circumscribed around the axis is rotated to a contact speed. The rotor ring is fictionally engaged under an axially applied weld load with the blade ring assembly to effect a conical inertia weld along the mating blade conical surfaces and ring conical surface. The integrally bladed rotor includes a plurality of airfoils circumferentially distributed about and integral with a rim. The airfoils extend radially outwardly from respective airfoil bases on a radially outer flowpath surface of the rim to airfoil tips. A conical inertia weld is located between the airfoil tips and a radially inwardly facing rim surface of the rim.

Abstract: An impeller assembly for reducing blockage at the inlet of a centrifugal pump includes an impeller having an inlet side and a bearing hub, wherein the bearing hub extends axially outwardly from the inlet side of the impeller. A conical floating sleeve is mounted on the bearing hub and held in place by a detachable retainer. The mating surfaces of either the bearing or the conical floating sleeve may be coated with a polymer to reduce surface friction. The bearing hub of the impeller may also be bored to receive a drive shaft.

Abstract: A blisk combining gas turbine blades and disk in a single structure comprises a disk and a number of blades integrally affixed to the disk. Each blade includes an airfoil made at least in part of an open-cell solid ceramic foam formed of ceramic cell walls, and an intracellular volume therebetween. The ceramic cell walls are preferably alumina, and the intracellular volume is preferably filled at least in part with a nickel-base superalloy. Another portion of the intracellular volume may be empty porosity.

Abstract: A single piece impeller that includes an integrally formed hub, back plate, inlet support ring and a plurality of impeller blades. The impeller blades each extend radially from an inner, leading edge to an outer, trailing edge. An extended portion of each impeller blade extends past the outer edge surface of the back plate such that the extended portion is not support along a lower edge surface. The top edge surface of the extended portion of each impeller blade is integrally formed with the support ring. The support ring provides support for each of the impeller blades and is sized to allow the single piece impeller to be removed from a mold.

Abstract: A modified side exhaust fan structure with multiple flush and rectangular blades in whirling arrangement provided in a guide frame having side exhaust topped by a hood. Each blade indicates upright to the plane of the hood. Air current created as the fan turns is fully drained crossing the vertical plane of each blade offering an effective solution to the problem of insufficient air drain due to back-draft found in the prior art with blades each with an exit inclination.

Abstract: In an exemplary embodiment, a motor assembly includes a shaft and a compound fan assembly that provides axial and centrifugal air flow. The fan assembly includes a body including an outer surface, a cavity defined by the body outer surface, a plurality of first blades extending radially outwardly from the body outer surface, and a plurality of second blades disposed within the cavity. The shaft is concentric with the body and the second blades are rotatably coupled to the shaft.

Abstract: A compressor wheel (10) for a turbocharger having a prestressed hub (16) with an interference fit insert sized to provide the predetermined stress at zero rotational speed. The predetermined prestress then results in a reduced operating stress level during high speed rotation of the wheel, reducing the potential for reaching failure level stresses in operation and increasing wheel life.

Abstract: A blisk includes a disk having a rim. A row of blades extends outwardly from the rib in a unitary construction. The blades are spaced apart in the disk rim to define fluted inner flowpath channels extending axially between the blades to bound corresponding flow passages therebetween.

Abstract: A rotor for a propulsion plant has hybrid rotor blades arranged circumferentially around and extending essentially radially from a rotor. To reduce vibrations, the rotor blade has a metallic blade root and each blade has a metallic blade section that forms at least a portion of the blade leading edge and the area of the blade surface adjacent to the blade leading edge, and a blade section made of fiber-reinforced synthetic material or composite material. The blade sections (3, 4) of each blade (1) are so correlated to each other that damage or loss of the composite material blade section (4) still enables the propulsion plant to deliver a required emergency power.

Abstract: A rotor assembly for a gas turbine engine operates with reduced circumferential rim stress. The rotor assembly includes a rotor including a plurality of rotor blades extending radially outward from an annular rim. A root fillet extends circumferentially around each blade between the blades and rim. The rim includes an outer surface including a plurality of concave indentations extending between adjacent rotor blades and forming a compound radius. Each indentation extends from a leading edge of the rotor blades towards a trailing edge of the rotor blades.

Abstract: The efficiency of a fan clutch is improved by having a central finned cover attached to the fan clutch at its rotational axis with fins or blades thereon to disperse air radially outwardly from a dead air bubble at the rotational axis of the fan. This is achieved by a cover having a disk-shaped body with fan fins extending from the rotational axis outwardly to the rim of the disk-shaped body to move air from the rotational axis to prevent the build-up of a negative pressure at the rotational axis and this air flow from the rotational axis into the clutch fan blades appreciably increases the total air flow by the fan clutch. The preferred fins are curved between their inner ends at the rotational axis and their outer ends which extend to the fan blades of the fan clutch. The fins may wrap around the rim of the disk-shaped body and the latter may have a curved outer, front surface.

Abstract: A blisk for use in a turbine engine. The blisk includes an annular disk, an inner row of blades including a plurality of circumferentially spaced airfoils integrally formed with the disk, an annular splitter integrally formed with the inner row of blades and surrounding the tips of the plurality of airfoils thereof, and an outer row of blades including a plurality of circumferentially spaced airfoils integrally formed with the splitter. There are more airfoils in the outer row of blades than in the inner row of blades.

Abstract: A blisk includes a disk having a rim. A row of blades extends outwardly from the rib in a unitary construction. The blades are spaced apart in the disk rim to define fluted inner flowpath channels extending axially between the blades to bound corresponding flow passages therebetween.

Abstract: An inducer having a hub and a plurality of blades is provided. In one embodiment, the thickness of the blades is defined such that during the operation of the inducer each of the blades is positioned underneath a cavitation vapor line so as to improve the performance of the inducer. In another embodiment, the hub is contoured or ramped according to a fifth order polynomial to provide improved performance. In another embodiment, the flow passage area of the inducer, as taken normal to the flow of fluid, is varied according to a fifth order polynomial to provide improved performance.

Abstract: Disclosed is an axial-flow fan including a hub coupled to a rotating shaft and integral with the rotating shaft, and blades arranged around the outer peripheral surface of the hub and integral with the hub, the axial-flow fan having design parameters given under the condition using an outer fan diameter of 110 mm±10 mm and a number of the blades corresponding to five or more. A sweep angle, which is included in the design parameters, is calculated using particular calculation equations, to reduce noises resulting from a “blade passing frequency” and a “blade vortex interaction” generated during an air sucking operation.

Abstract: A blisk includes a disk having a rim from which extends a row of blades. The rim includes axially opposite overhangs one of which includes an arcuate balance land disposed eccentrically to the centerline axis of the disk for balancing the blisk.

Abstract: A cooling fan assembly (10) includes a hubless polymer fan body molded around the perimetrical flange (20) of a metallic mounting hub (12). The fan body includes a circumferential ring (18) interlocked with the flange (20) and a plurality of fan blades (16) projecting outwardly from the ring (18). The fan body (14) is formed in an injection mold with molten polymer material being introduced into the mold at hot runner locations (25) disposed between the circumferential ring (18) and the root diameter (17) of the fan blades (16). At one face of the hubless fan (14), the circumferential ring (18) includes a plurality of uniformly spaced raised bosses (30). Each boss (30) defines a bore (31) configured to receive a balancing weight therein, preferably in the form of a balancing screw (35) threaded into the bore. The bosses (30) are interconnected by a stiffening ring (33) having a height substantially equal to the height (h) of the bosses (30).

Abstract: Turbine is added to the spinner of a propeller to provide a contribution to propulsive thrust of the propeller. The turbine comprises a group of turbine modules, which are mounted on the periphery of the spinner between root portions of the propeller blades. Each module includes a curved row of angulated turbine vanes held between a curved base plate and a curved outer plate.

Abstract: An improved vane system comprising of two or more vanes being part of a spherical section related to a hub characterized in that an operative concave surface of the vane being part of the spherical section. An operative convex surface of the vane being part of a spherical section and the vane having an operative anterior lateral border with an operative posterior lateral border having a free superior tip and an inferior edge related to the hub by which the vane is angularly displaced around an axis being parallel to the velocity and the drift of the fluid.

Abstract: A propeller including, in one embodiment, a flare having a sinusoidal, or tulip, shape is described. The flare is located at a trailing edge of the propeller, and the sinusoidal flare shape of the propeller trailing edge has reduced stresses as compared to stresses associated with known flare rings. Specifically, stress is reduced in the sinusoidal flare shape due to smooth trailing surfaces and the uneven edge of the flare. As a result, and during fabrication, potential for cracking the trailing edge of the flair is reduced. In addition, the flare has greater strength as compared to at least some known flare rings in that stresses are more evenly distributed along the tulip shaped trailing edge.

Abstract: This invention provides a compact, flat axial fan which is not limited by the shape of an incorporated rotor magnet and ensures a sufficiently large air flow and wind pressure, wherein the slide (under) piece of a mold that forms the under-molding portions of the vanes of the impeller of the axial fan is pulled out while being twisted (while performing a helical motion) in the direction of central axis of the base portion of the impeller, so that the mold can be formed simple to realize a multi-cavity mold, and the vanes can be formed into an ideal form by setting vane angles depending on different rotating peripheral velocities of the vanes, so that air can be supplied form the under-molding portions of the vanes to the vanes on the outer circumferential side during rotation of the impeller and a method of manufacturing an impeller for the axial fan.

Abstract: An axial-flow fan comprises a hub having an axial dimension T.sub.N, and including a planar portion extending in a radial direction. Axial blades connected to the hub, and each axial blade has an axial dimension T.sub.Sch in a vicinity of a radially outermost portion of the hub. The axial dimension T.sub.Sch of each axial blade is greater than the axial dimension T.sub.N of the hub. Each axial blade has a projection U beyond the planar portion of the hub. The projection U extends axially from a leading edge of each axial blade to the planar portion of the hub.

Abstract: An impeller having flexible impeller blades with a stiffness which allows the blades to flex into a backward-curved impeller configuration at the maximum intended rotational speed of operation, and to return to a more radial blade configuration at lower rotational speeds, thereby enabling efficient operation at a broad range of rotational speeds.

Abstract: A high efficiency axial flow fan includes a hub, fan blades and a circular band. The hub rotates about a rotational axis when torque is applied from a shaft rotatably driven by a power source. The circular band is concentric with the hub, connected to the tip of each blade, and is spaced radially outward from the hub. The blades are configured to produce an airflow when rotated about the rotational axis. Each blade has a chord length distribution, stagger angle and dihedral distribution which varies along the length of the blade. The dihedral distance of each blade varies as a function of blade radius from the rotational axis.

Abstract: A structure of a ventilation fan provided with a plurality of blades has a performance curve characterized by a gentle slope throughout the wide operating range instead of an S-hysteresis curve, in order to overcome a fluctuation phenomena of the operating flow rate. The blade tip cross-section lies on a first imaginary cylindrical surface and an angle of attack and pitch angle of the blade tip are formed as respective trajections by intersecting the first cylindrical surface by a second cylindrical surface whose center axis has been rotated about two axes.

Abstract: A method of making an integrally bladed disc for a gas turbine engine, the disc having at least one blade the radially outermost surface of which is coated with a material harder than that of the blade, the method comprising the steps of: providing a forged disk blank of a first material; friction surfacing at least part of the circumference of the blank with a second material harder than the first material; and machining the blank so as to provide an integrally balded disc wherein the radially outermost surface of at least one blade is coated with said second material.

Abstract: To manufacture a turbine wheel having blades made of a ceramic or composite material and inserted into a metal hub, firstly blades (16) are manufactured that are right cylindrical, each blade having a base (18) through which a hole is formed; a cylindrical ring (20) is formed, the ring being provided with orifices through which the bases (18) of the respective blades (16) are inserted; the blade bases (18) are successively threaded onto an open annular rigid metal wire (30); the resulting assembly (16, 20, 30) is disposed inside a sealed housing (161); hot isostatic compaction is performed so as to compact a metal alloy in powder form (41) inside the sealed housing (161) so as to make the hub of the turbine wheel (100) while embedding the blade bases (18) and the metal wire (30) by using the powder metallurgy technique; and the outside portion of the sealed housing (161) delimiting the hub of the turbine wheel (101) is machined. Application, in particular, to the field of aeronautical or space engineering.

Abstract: A centrifugal pump impeller for delivering solids-containing media includes a blade having a beginning portion. In the plane of the middle blade surface, there is, in front of the blade beginnings, a very fiat transition from the impeller covering disks to the blade beginnings.

Abstract: A propeller for use on low power motors, such as two-horsepower or less electric trolling motors, is provided with three or more blades on a hub wherein the hub diameter to the blade length (i.e. the length of the blade from the hub to the outermost tip) is in the ratio of at least 1.250 to 1. The hub diameter to blade length ration is such as to produce a propeller having increased performance and is substantially weedless. The width of each blade at its root is equal to or greater than the blade length and the ratio of the sum of the widths of the blades to the circumference of the hub is approximately 1.2 to 1. The true or actual pitch of the blades is measured at 0.7 the radius of the propeller and produces the best results as far as performance and weedlessness is concerned within the range of 2" to 7". The leading edge of one blade forms a junction with the hub in close proximity to a plane containing both the longitudinal axis of the hub and the junction of the trailing edge of the next adjacent blade.

Abstract: An axial flow fan device capable of reducing the stagnant flow at the root area of blades. These blades 18 are arranged so that they extend radially from a boss portion 14 so that they are circumferentially spaced along the circumference of the boss portion 14. Each of the blades 18 has an arc shaped cross section having a bending ratio value .alpha., that is a ratio of the bending height h of the arc shape to the length l of the chord of the arc shape. The value of the bending ratio rapidly increases from the middle portion of the blade to the root portion. The value of the bending ratio at the root portion is about 12%.

Abstract: The invention is directed to an impeller of an axial-flow type fan, in particular for appliances for drying and dressing hair, in which adjacent blades overlap each other completely over the radial extent of the blades in the edge regions of the blades. To ensure that the injection-molded impeller is capable of being ejected from the mold, the angle of opening is required to be smaller than or equal to the angle of rotation.

Abstract: A weed resistant boat propeller is disclosed. The propeller includes a generally circular hub that is adapted for mounting to and being rotatably driven by a boat motor. There are a plurality of blades mounted to a circumferential surface of the hub and extending therefrom in a spiral configuration. Each blade includes a curved leading edge that has an arc dy/dx<1 for the entire length of the leading edge.

Abstract: A fixed pitch propeller has blades that are not solely dependent on the blade angle dictated by the helical path of the blade tip. An outboard portion of the blade has a range of blade angles that are relatively flat to operate most efficiently at lower aircraft speeds.

Abstract: An engine-cooling fan is made of a synthetic resin, and includes a cylindrical hub, a plurality of fan blades provided integrally and radially on an outer peripheral wall of the hub and an integral member provided on an inner peripheral wall of the hub for mounting the fan on a drive shaft extending at a right angle relative to a plane in which the fan blades lie. At least one reinforcing rib is integrally molded between the outer peripheral wall of the hub and a heel portion of each of the blades.

Abstract: An axial flow air impeller for automotive radiator fan use and the like comprising a hub carrying a plurality of integrally formed similar circumaxially spaced and generally radially outwardly projecting air moving blades. Each blade has a root end portion integral with the hub and a radially outwardly disposed tip end portion with smoothly curving leading and trailing edges extending therebetween. The leading edge curves substantially forwardly while the trailing edge extends substantially radially to provide for a blade projected width at the tip end portion approximately 40% greater than at the root end portion. The thickness of each blade varies from a maximum at the root end portion to a minimum at the tip end portion with the latter being at least three times the thickness at the blade edge. An integral orifice ring circumscribes the plurality of blades and has a bell mouth at its upstream or downstream end.

Abstract: A bucket wheel assembly for use in a flow measuring device is disclosed wh comprises a one-piece, lightweight molded plastic disk having a plurality of roughly conical cups connected to a central ring. The central ring is mounted on a shaft and the disk rotates in response to fluid pressure in order to generate a signal proportional to flow velocity. The bucket wheel is advantageous over prior art versions in that it is responsive only to the horizontal component of flow velocity, when rigidly held, and thus gives truer and more accurate information with regard to current flow, particularly when used in current meters measuring flowing streams and rivers.

Abstract: A multi-bladed marine propeller designed for efficient operation in intermediate, partially cavitating flow regions between fully cavitating flow and noncavitating flow. Each of the blades has a radially inner subcavitating section and an outer section which is configured to have a higher angle of attack and tapered trailing and leading edges so that it supercavitates at high speeds either with or without ventilation and subcavitates at low speeds. Various other features of each blade include different length chords on the pressure and suction sides of the outer section and an inclined trailing surface area extending between the chord ends for improved off design, design point, and astern operation. A minimized transition area is included between the inner and outer sections, and narrow chord lengths are provided in the tip area to minimize and balance overall tip section drag.

Abstract: Compact fan and shroud package for radiators with fan blades curved rearwardly to position rotating shroud at optimized distance from radiator for improved air flow through radiator.