Abstract: A blower impeller employing curved radial blades defining an arc chord of 60 degrees, which circulate the air entering the circulation section to tangentially force the same through an exhaust section, wherein the multiple, overlapping, blades are of a modified Archimedes spiral design providing greater efficiency and lower generated noise.

Abstract: Impeller blades and a method for designing impeller blades wherein the blades comprise a plurality of specially designed airfoil sections, each section having along substantially the entire length thereof, a cross-sectional shape characterized by a maximum thickness located substantially constantly between about 16% chord to about 23% chord and a maximum camber located substantially constantly between about 40% chord to about 51% chord. The blades are designed so that the axial width of the blades is decreased while maintaining performance parameters and design constraints.

Abstract: A gas turbine engine has, in a cross section in the axial direction of an annular inner peripheral wall connected to a blade main body of a turbine blade, a concave part and a convex part on the front edge side and the rear edge side. The concave part has a negative curvature and is concave toward the axis, and the convex part has a positive curvature and is convex away from the axis. The flow rate on the upper face of the blade main body can be reduced in the concave part on the front edge side, thus suppressing generation of a shock wave, and the flow rate can be increased in the convex part on the rear edge side following the concave part, thus smoothly changing the flow rate on the upper face of the blade main body and thereby minimizing the pressure loss. In this way, the thickness of the blade main body can be reduced while ensuring the performance of the gas turbine engine, thereby contributing to a reduction in weight.

Abstract: A cooling fan includes a rotatable hub and a plurality of generally V-shaped impellers that are angularly displaced from each other and that extend outwardly from the hub. Each of the impellers has first and second impeller halves that extend outwardly from the hub and that are connected to each other so as to form cooperatively an angle therebetween.

Abstract: An efficient axial flow fan comprises a central hub, a plurality of blades, and a band, and is designed to operate in a shroud and induce flow through one or more heat exchangers—in an automotive engine cooling assembly, for example. The fan blades have a radial distribution of pitch ratio that provides high efficiency and low noise in the non-uniform flow field created by the heat exchanger(s) and shroud. The blade has either no sweep, or is swept backward (i.e. opposite the direction of rotation) in the region between the radial location r/R=0.70 and the tip (r/R=1.00). The blade pitch ratio increases from the radial location r/R=0.85 to a radial location between r/R=0.90 and r/R=0.975, and then decreases to the blade tip.

Abstract: The present invention is a turbine bucket for at the low pressure last stage of a steam turbine and in which the adjacent blades are connected without using a connecting member at a blade intermediate portion. A turbine bucket of the present invention is formed that the blade sectional configuration is twisted from a blade root portion to a blade tip side, and when assuming two axial directions in a blade section of the bucket on horizontal plane and taking one axial direction as X axis and the other axial direction perpendicular to X axis as Y axis, the blade sections at predetermined heights from the blade root portion of the turbine bucket are formed in a range of ±0.3 mm from respective points defining blade section configurations.

Abstract: A blade for a cooling fan is formed on an outer periphery of a rotor of the cooling fan and is curved. The blade has a convex outer surface and a concave inner surface. A curved angle of the blade between a line through the center of the rotor and a root of the convex outer surface and a line through the root and a tip of the convex outer surface is between 30° to 40°. A plane surface is formed on the concave inner surface and at a distal end of the blade. A first cutout is defined at a bottom side and a proximate end of the blade. A second cutout is defined at the upper side and the distal end of the blade.

Abstract: An electric fan having an electric motor and a fan wheel connected to the electric motor. The fan wheel has a hub and fan blades extending from the hub. The fan blades include a proximal section at the hub, a distal section and a middle section. The proximal section has a flat surface at a trailing edge of the blade. The trailing edge at the distal section is curved with an angle of curvature of about 10°. The trailing edge at the middle section is curved with an angle of curvature of about 36°. When the fan wheel is rotated by the electric motor at a constant speed, air pushed by each of the fan blades is propelled at a substantially same velocity and direction from the blade measured across a radial length of the blade.

Abstract: A propeller fan adapted to prevent abnormal air flow to thereby increase discharge of air flow but to decrease noise, the fan including a plurality of vanes, each vane fixed at a hub secured at a rotary axle, having a predetermined length toward external radial direction thereof and circumferentially spaced out at a predetermined gap, wherein each van has a cross-sectional shape like a flat surface at an external side of a leading edge thereof while an external side of a trailing edge thereof is bent with a predetermined radius of curvature (Rc).

Abstract: The axial flow fan (1) comprises a central hub (3), a plurality of blades (4), each blade (4) having a root (5) and an end (6) and being delimited also by a convex edge (7), whose projection onto the plane of rotation of the fan is defined by a parabolic segment, and by a concave edge (8) whose projection onto the plane of rotation of the fan is defined by circular arc. The blades (4) consist of sections having aerodynamic profiles (18) with a face (18a) comprising at least one initial straight-line segment (t) and a blade angle (&bgr;) that decreases gradually and constantly from the root (5) towards the end (6) of the blade (4) according to a cubic law of variation as a function of the fan radius.

Abstract: A rotor is intended to rotate in a fluid flowing in a flow direction and comprises a plurality of rotor blades, at the most four blades, which are arranged to rotate about an axis of rotation. Each blade forms a single-curved surface, the generatrix of which extends in a plane normal to the axis of rotation, and an imaginary plane interconnecting the leading edge and trailing edge of the blade forms an acute angle with the axis of rotation. In addition, each blade is pivotally mounted for pivotal movement about a pivot shaft in order to adjust the acute angle, the pivot shaft extends in a plane that is normal to the axis of rotation and is parallel to and spaced a distance from an imaginary radius radiating from the axis of rotation. The rotor is very silent and provides efficient energy conversion, for example extraction of wind power.

Abstract: The axial flow fan (1; 30) comprises a central hub (3; 33) a plurality of blades (4; 34) which have a root (5; 35), and an end (6; 36). According to one embodiment, the blades (4; 34) are spaced at unequal angles (&thgr;i . . . , n) which can vary in percentage (&thgr;%) from 0.5% to 10%, compared to the configuration with equal spacing angles (&thgr;=) for fans with an equal number of blades. Preferably, the blades (4; 34) are delimited by a convex edge (7; 37), whose projection onto the rotation plane of the fan is defined by a parabolic segment and a concave edge (8; 38) whose projection onto the rotation plane of the fan is defined by a circular arc.

Abstract: A blade for a cooling fan is formed on an outer periphery of a rotor of the cooling fan and is curved. The blade has a convex outer surface and a concave inner surface. A curved angle of the blade between a line through the center of the rotor and a root of the convex outer surface and a line through the root and a tip of the convex outer surface is between 30° to 40°. A plane surface is formed on the concave inner surface and at a distal end of the blade. A first cutout is defined at a bottom side and a proximate end of the blade. A second cutout is defined at the upper side and the distal end of the blade.

Abstract: Disclosed is a blade part in a turbofan, which includes a hub coupled with a rotating axis of a driving part, a plurality of blades arranged radially at a circumferential part of the hub, and a shroud coupled with a plurality of the blades and arranged so as to confront the hub wherein the blades lie between the hub and the shroud, and wherein each of the blades form an airfoil constructed with a top camber line defined by an NACA 4-digit airfoil and a bottom camber line lying closer to the top camber line than a bottom camber line defined by the NACA 4-digit airfoil, thereby enabling to cost and time of product.

Abstract: The fourth-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.

Abstract: A compressor stator includes an outer casing supporting a row of stator vanes extending radially inwardly therefrom. Each vane includes pressure and suction sides extending axially between leading and trailing edges and radially between a root and a tip. The root and tip are twisted relative to a pitch section disposed therebetween. Each vane tip is radially convex adjacent a leading edge for defining an axially concave outer flowpath in the casing for reducing peak velocity of airflow for enhanced efficiency.

Abstract: A turbomolecular pump capable of maintaining a maximum discharge rate even in a higher pressure has rotor blades or stator blades formed such that surface angles on a first surface of the blades facing the direction of rotation differ between an inlet port side of the blades and an outlet port side. The surface closer to the inlet port has a larger angle than on a side closer to the outlet port. One side of the blades has a plurality of surface portions each with different angles. The angles of the surfaces are in the range of 20° to 50° on the inlet port side, 10° to 40° on an intermediate portion, and 10° to 90° on the outlet port side. The angles of the first and second surface portions are larger than that of the intermediate surface portion.

Abstract: The present invention employs improved fan blade shapes to improve fan blade performance in one or more manners (i.e., increased fan efficiency, lower fan noise, greater fluid moving capability, and the like). In some embodiments, the fan blade has a front side, a rear side, an inner attachment portion, an outer edge, a curved leading edge and a curved trailing edge. The outer edge can define an arc between a forward position and a rearward position of the fan blade. In some embodiments, the leading edge extends outward and intercepts the arc of the outer edge at the forward position, and the trailing edge extends outward to the rearward position. Various angles, lengths, and other dimensions of the blade can have selected values to produce superior fan performance.

Abstract: A turbine blade for a gas turbine engine. An existing blade was found to exhibit bowing, or a concave configuration facing the pressure side, along its trailing edge. The invention reduces bowing by (1) changing tilt, (2) changing lean, (3) reducing the number of cooling holes, while (4) changing the diameters of the cooling holes, to maintaining the total cooling flow unchanged.

Abstract: The pressure distribution curve of the blade suction-side surface excluding the leading edge portion and the trailing edge portion drops in two stages in the area from the leading edge to the minimum pressure point.

Abstract: The third-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinates defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.

Abstract: This invention is characterized by a very compact blower assembly architecture designed to operate at low Reynolds numbers. The assembly includes an impeller with forward-curved blades and a hub that is shaped to minimize the overall package volume of the assembly. The impeller is driven by a low-power, brushed, direct-current motor. A shroud part includes a generally cylindrical inlet that directs the air into the impeller, and a surface that forces the air leaving the impeller to turn from a generally radial and tangential direction to a generally axial and tangential direction. The shroud part directs the air into a single stage of stator blades that reduces the tangential component of the air velocity and produces a static pressure rise.

Abstract: The second-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X and Y values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket. The second-stage wheel has sixty buckets.

Abstract: Disclosed herewith is a micro-fan. The micro-fan includes a hub attached to a rotating shaft and a plurality of blades extended from the side surface of the hub. In the micro-fan, if a leading edge is defined as the foremost edge of each of the blades consisting of a straight line portion and one or more arc portions, a trailing edge is defined as the rearmost edge of each of the blades, a chord line is defined as a line connecting two opposite points respectively situated in the leading and trailing edges and a blade angle is defined as an angle formed by the chord line and the horizontal line passing through the same point of the leading edge as that through which the chord line passes and lying in the same vertical plane as that in which the leading edge lies, the straight line portions of the leading and trailing edges are perpendicular to the hub and form a predetermined inside angle.

Abstract: Disclosed is a turbo fan of a ceiling-embeded cassette type air conditioner. The turbo fan has a shroud for guiding a fluid introduced into the turbo fan, a hub having an outer diameter smaller than an inner diameter of the shroud, so as to facilitate an integral injection molding of the turbo fan, and blades extending between the shroud and the hub and being perpendicular to the shroud and the hub. Each of the blades has an inner diameter decreasingly inclined from the shroud to the hub, so that a quantity of sucked-air and a static pressure can be increased. The turbo fan not only can be integrally formed by injection molding but also can be manufactured at a reduced manufacturing cost. Further, the turbo fan can effectively overcome the undesired problem of the prior art due to the modification in dimensions of the turbo fan, thereby providing a turbo fan exhibiting a quantity of blown-air and a static pressure which are the same or increased in comparison with the prior art.

Abstract: An axial flow fan 10 for producing airflow through an engine compartment of a vehicle includes a hub rotatable 12 about an axis 22. An annular band 16 is concentric with the hub and spaced radially outward from the hub. A plurality of fan blades 14 are distributed circumferentially around the hub and extend radially from the hub to the annular band. Each blade is constructed and arranged to ensure that the fan can operate at high speed and low torque.

Abstract: A turbine vane with an enhanced profile including a trailing edge is curved inwards towards the suction face in the vicinity of the head, as if it was twisted, which opens the vane and limits leakage currents above the head. The flow is thus improved since the eddies formed by the irregular flows in front of the vane are reduced.

Abstract: The blade has such a shape that the diameters of circles inscribing the belly and back sides at different positions of adjacent blades decreases as one goes from the front edge to the rear edge. Since the blade has such a shape, even if the influent angle and effluent angle of gases are increased, a deceleration passage is not formed in the passage between the adjacent moving blades.

Abstract: The present invention provides an axial flow fan structure having an optimal airflow rate and pressure head. The axial flow fan structure includes a rotor provided with a plurality of fan blades which are overlapped with each other. In such a manner, variations of the chord angle, the air inlet angle, and the air outlet angle of the fan blade together with adjustment of the span of the fan blades co-operate with rotation of the fan blade to produce an optimal airflow rate and pressure head. In addition, the fan blades of the rotor may co-operate with a set of stator guide vanes, thereby further increase the pressure head of the airflow, while the airflow having a high flow rate and high pressurization is guided to a predetermined direction more efficiently.

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 turbine blade for an axial-flow turbine includes an intrados generating a positive pressure, and an extrados generating a negative pressure, wherein the intrados and the extrados are provided between a leading edge and a trailing edge. An inflection point is provided between a concave portion on an upstream side and a convex portion on a downstream side in a region extending from a position of 80% on the intrados to a rear throat, and the length of a normal line drawn downwards from the intrados of one of the turbine blades to an extrados of the other turbine blade has at least one maximum value in a region extending from a front throat of the one turbine blade to a rear throat. Thus, it is possible to disperse a shock wave generated from the intrados at the trailing edge to prevent the generation of a strong shock wave, thereby reducing the pressure loss caused by the shock wave.

Abstract: The invention concerns a rotor blade and a wind power installation having a rotor blade provided with a rotor blade trailing edge, wherein the rotor blade tapers towards the rotor blade trailing edge. The invention is distinguished in that, in the region of the rotor blade trailing edge, the degree of taper of the rotor blade increases in a direction towards the rotor blade trailing edge, and there is no stair-like step in the rotor blade at least in the region of the rotor blade.

Abstract: There is disclosed herein an impeller for a centrifugal pump such as water pumps for automotive internal combustion engines or a centrifugal pump for liquids other than water. The impeller has a circular base and a series of similar vanes extending vertically from the base. Each vane extends rearwardly from its inner end to its outer end with respect to the direction of rotation of the rotor and is wider at its midpoint than its ends. The leading edge of each vane is concave at least at its inner end while the trailing edge of each vane is convex.

Abstract: An Improved impeller which imparts energy to or receives energy from a multiphase fluid comprising at least one gas phase and at least one liquid phase is disclosed. The impeller comprises an inlet section and an outlet section, at least one flow channel delimited by at least one boss and two successive vanes. The impeller has an axial length Lt and a mean radius of curvature Rh(z), taken in the meridian plane, the radius of curvature Rh(z) being determined over at least part of length Lt so as to limit separation of the phases of said multiphase fluid inside the channel.

Abstract: Airfoils 10 having high lift to drag characteristics at low Reynolds number are disclosed. The airfoils including a leading edge 12, a trailing edge 14 spaced from the leading edge, an upper surface 16 extending from the leading edge to the trailing edge, and a lower surface 18 extending from the leading edge to the trailing edge. An airfoil designed for a tip region of a blade has a thickness in a range of 3% to 13%, a Reynolds number in a range from 120,000 to 400,000, and a maximum lift coefficient in a range from 1.0 to 1.2. An airfoil designed for a midspan region of a blade has a thickness in a range of 3% to 13%, a Reynolds number in a range from 90,000 to 200,000, and a maximum lift coefficient in a range from 1.4 to 1.6. An airfoil designed for a root region of a blade has a thickness in a range of 5% to 15%, a Reynolds number in a range from 60,000 to 120,000, and a maximum lift coefficient in a range from 1.8 to 2.0.

Abstract: A steam turbine that passes more turbine driving steam by off-setting the turbine moving blade throat-pitch ratio before operation and, when a blade untwist is generated during operation, causing more turbine driving steam to flow by maintaining an appropriate value, and, at the same time causing the turbine moving blade throat-pitch ratio to swell by giving the blade untwisting angle to the blade cross-sections in regions where the aerodynamic loss is small. The steam turbine is one in which the throat-pitch ratio (S/T) distribution of a turbine moving blade is offset by forming a curve providing at least one minimal value and maximal value by giving blade twist angle to the blade cross-sections in the blade height direction from blade root to blade tip and, at the same time, the distribution of throat-pitch ratio (S/T) taking into consideration blade untwist generated during operation.

Abstract: A propeller fan adapted to prevent abnormal air flow to thereby increase discharge of air flow but to decrease noise, the fan including a plurality of vanes, each vane fixed at a hub secured at a rotary axle, having a predetermined length toward external radial direction thereof and circumferentially spaced out at a predetermined gap, wherein each van has a cross-sectional shape like a flat surface at an external side of a leading edge thereof while an external side of a trailing edge thereof is bent with a predetermined radius of curvature (Rc).

Abstract: A fan blade includes an airfoil having a root and an integral platform. The platform includes forward and aft ends and arcuate first and second sides therebetween. The airfoil root is laterally offset closer to the platform first side than the second side. Impact loads with a trailing blade during a blade-out failure are accordingly distributed for reducing peak loading in the trailing blade and damage thereto.

Abstract: A compressor casing includes an axially convex inner surface for surrounding a row of rotor blades with radial gaps therebetween. The tip of the blades complement the casing contour for reducing blade tip losses and flow blockage.

Abstract: A compressor airfoil includes pressure and suction sides extending from root to tip and between leading and trailing edges. Transverse sections have respective chords and camber lines. Centers of gravity of the sections are aligned along a double bowed stacking axis for improving performance.

Abstract: An axial flow fan for an air conditioner is disclosed. This axial flow fan is capable of changing the shape of blades by varying a design factor such as a chord length, a sweep angle, etc., generating an enough flowing amount of a fan for implementing an efficient heat radiation of a heat exchanger, and decreasing a noise which occurs during an air flowing operation of the fan, so that it is possible to implement a high efficiency and low noise fan system. The above-described axial flow fan according to the present invention includes a hub engaged to a rotary shaft of a motor, and a plurality of blades engaged to the hub, wherein assuming a coordinate which is obtained by computing a distance R in a radial direction of the blade into a distance from a radius Rh to a radius Rt at a blade tip BT based on a non-dimensional method as “r” (r=(R−Rh)/(Rt−Rh), a maximum camber ratio Hc(r) which is a ratio between a maximum camber Cmax and a chord length 1 has 0.02±0.

Abstract: Non-planar propellers or windmill blade assemblys are proposed which have tips that are curved to point in the same direction as the axis of rotation of the propeller. This non-conventional design results in a stronger, stiffer, and more efficient propeller or windmill.

Abstract: A stator wheel for a hydrodynamic torque converter comprises a stator wheel hub arrangement and a plurality of stator wheel blades arranged successively in the circumferential direction of the stator wheel hub arrangement. Each stator wheel blade has a radial inner flow-around profile area and a radial outer flow-around profile area such that a flow-around profile in the radial outer flow-around profile area differs from a flow-around profile in the radial inner flow-around profile area.

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 thin motor-driven centrifugal blowing fan apparatus draws in air in a rotation-axis direction and discharges the air in a radial direction. In this fan apparatus, blades are fitted on a peripheral face of a rotor, and each section of the blades in the vicinity of the peripheral face is implanted at an acute angle to the rotation direction so as to form an axial blade section. A section extending from the axial blade section is arranged perpendicular to the rotation direction so as to form a centrifugal blade section.

Abstract: A blade for a gas turbine includes an internally formed passage (a) for cooling the blade with steam. The ratio (t/c) of blade thickness (t) to chord length (c) should fall within the range of 0.10 to 0.15.

Abstract: A glass coated gas dispersing impeller. The impeller comprises a hub, having a centrally located hole. The hole has a central axis and is sized for passage over a drive shaft having an essentially vertically extending longitudinal axis so that the central axis of the centrally located hole corresponds with the longitudinal axis of the shaft. The impeller has a plurality of angles and edges, all of which have a rounded configuration. The impeller further comprising a plurality of blades secured to the hub that extend radially outward from the central axis. Each of the blades has a leading concave surface and a trailing convex surface both of which are defined by a lower edge, an upper edge, an inner edge and an outer edge. The concave surface is configured so that the upper edge overhangs the lower edge. The blades may be connected to the hub directly or by intermediate connecting means such as a disk or arm integral with the hub and extending radially outwardly from the central axis.

Abstract: A novel concept for a propeller blade configuration incorporates the model of the natural wave behavior. The leading edge of the propeller blade is parallel to the trailing edge, but offset by a given amplitude. The surfaces between the leading and trailing edges are rounded so as to promote proper fluid sheet formation along the surface and to reduce undesirable vortice formation. Best results are obtained by modeling the surfaces along a sine or tangent function.

Abstract: A novel concept for a propeller blade configuration incorporates the model of the natural wave behavior. The leading edge of the propeller blade is parallel to the trailing edge, but offset by a given amplitude. The surfaces between the leading and trailing edges are rounded so as to promote proper fluid sheet formation along the surface and to reduce undesirable vortice formation. Best results are obtained by modeling the surfaces along a sine or tangent function.

Abstract: An air cleaner includes a housing having an upper wall and side walls, an air filter mounted with respect to the housing, a fan including a vane-wheel having a plurality of vanes, a supporting plate extending substantially between at least two side walls for supporting the fan. An air flow directional member directs an air flow output from the fan. The vane is formed to have a winglike cross-section, and the vane-wheel includes not more than four vanes. The vane-wheel has a base plate and a shroud. Each of the base plate and the shroud is formed to have a reinforcement portion on its circumference. A U-shaped balance weight is attached to a flattened portion formed on the curled portion. The air cleaner of the present invention can reduce noise and vibration and improve efficiency of the fan.