Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: An impeller for use in conjunction with a percutaneously-insertable blood pump or other rotatable equipment includes a blade that is segmented into a plurality of overlapping or abutting bladelets. In some embodiments, the bladelets are foldable and one side of each bladelet is concave.

Abstract: An airfoil for a rotor blade including an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z to facilitate balancing performance and durability of the rotor blade and to facilitate improving an operating efficiency of a high-pressure turbine is provided. The profile is carried only to four decimal places, wherein Y represents a distance from a platform on which the airfoil is mounted, and X and Z are coordinates defining the profile at each distance Y from the platform.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: An impeller (10) for a cooling fan includes a hub (20) having a circular wall (22) and an annular sidewall (24) extending upwardly from a periphery of the circular wall, and a plurality of blades (30) extending radially from the sidewall of the hub. Each of the blades includes a first portion (32) near the hub and a second portion (34) away from the hub, wherein each of the second portions has a pair of opposite ribs (36) formed on two lateral sides thereof, thereby reducing a noise level generated by the impeller when the impeller rotates.

Abstract: The compressor blades of an aircraft engine are, in at least one natural-vibration critical area, designed such that at the blade leading edge (6), the leading edge shock wave (14) attaches to the leading edge (6), as a result of which a laminar boundary layer flow (7) on the suction side (13) quickly transitions into a turbulent boundary layer flow (9) which is kept constant and prevented from re-lamination by the further, continuous curvature of the suction side. Therefore, the transition, whose periodic movement is also suppressed, cannot communicate with a suction-side compression shock (10), preventing the compression shock from augmenting the natural vibrations of the blade occurring under certain flight conditions. The blade leading edge can, for example, be designed as an ellipse with a semi-axis ratio equal to or smaller than 1:4.

Abstract: In a gas turbine having a plurality of moving blades provided on a rotary shaft in a circumferentially adjoining condition, a seal pin is provided in a spacing between the shanks of the adjacent moving blades for preventing leakage of cooling air from a blade root portion side to an airfoil side; an arcuately depressed portion is formed on the shank of each of the moving blades; and vibration of each of the moving blades is suppressed in such a manner that the seal pin serves as a spring system while the airfoil portion, the platform, the shank, and the blade root portion serve as a mass system.

Abstract: The first stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and R set forth in Tables I and II, respectively, and second stage nozzles and buckets have nominal airfoil profiles substantially in accordance with Cartesian coordinate values set forth in Tables III and IV, respectively. The X, Y and R values are in millimeters. R represents distances along a radius from an axis of rotation of the turbine. For each airfoil, X and Y are distances which, when connected by smooth continuous arcs, define airfoil profile sections in planes normal to the radius at each distance R. The profile sections at the R distances for each airfoil are joined smoothly with one another to form the airfoil shape. The airfoil shapes given by the X, Y and R distances lie within envelopes of ±4.064 millimeters in a direction normal to any airfoil surface location therealong.

Abstract: A fan has an air conveying conduit (16) and a fan wheel (22) arranged therein, which wheel is rotatable about a central axis (25) and is formed with a central hub (20; 120) having an outer periphery (27) on which fan blades (26) are mounted. These extend with their radially outer rims (40) as far as a surface (17) that is substantially coaxial with the central axis (25) and delimits the air conveying conduit (16) externally. The blades (26) have a profile similar to an airfoil profile. A flow element (42) is provided along the radial outer edge (40) of a fan blade and serves as an obstacle to a compensating flow proceeding around that radial outer edge (40) from the delivery side to the intake side, and likewise has, in cross section, an airfoil profile.

Abstract: A cross flow fan of an indoor unit of, for example, an air conditioner includes a pair of disc-shaped end plates and a plurality of fan blades attached to the end plates in a ring-shaped arrangement. Each of the fan blades has a cross sectional area ratio of Sa/Sb in a range of 1.3 to 1.6, preferably, 1.4 to 1.5, in which Sa is a sectional area of a fan inner peripheral side half portion of the blade and Sb is a sectional area of a fan outer peripheral side half portion of the blade at a time when the fan blade is cut perpendicularly with respect to a longitudinal direction of the fan blade and divided into two sectional areas along a central division line in a blade chord direction.

Abstract: A turbomachine blade with a profile skeleton line extending along a meridional flow line, the blade being radially divided into at least three zones (Z0, Z1, Z2) with profile skeleton lines of each zone (Z0, Z1, Z2) provided in each zone from the respective radially inner to the radially outer boundary to satisfy the equations: ? * = ? 1 - ? P ? 1 - ? 2 S * = s P S where P is any point of the profile skeleton line, ?1 is angle of inclination at blade leading edge, ?2 is angle of inclination at blade trailing edge, ?* is dimensionless, specific angle of total curvature, S* is dimensionless; specific extension, ?P is angle of tangent at any point P of profile skeleton line to central meridional flow line, sP is extension of profile skeleton line at any point P, and S is total extension of profile skeleton line.

Abstract: A turbine bucket is provided that can make centrifugal stress acting on a blade or dovetail not greater than a limit value of a material and that is provided with a shape of a blade root that can ensure a steam passage even if the blade is increased in length in order to increase an exhaust area. The turbine bucket is for a steam turbine low-pressure final stage and has an exhaust area exceeding 9.6 m2 (13.8 m2) in steam-turbine final-stage buckets for a rated speed 3600 rpm (3000 rpm) machine. The turbine bucket is made of martensite steel. A blade portion of the turbine bucket has a suction surface 7 and a pressure surface 8 which are each formed, at a turbine blade root, of three areas consisting of a steam inlet side area 12 with curvature, a steam outlet side area 13 with curvature and an approximately straightly formed area put between the two areas.

Abstract: A ceiling fan blade is disclosed that is twisted rather than flat and has a graduated dihedral. The dihedral is provided for a wider distribution of divergence of air in the space beneath the fan. The blade (10) is demarked to have three sections which include a mounting section (11) and two airflow sections (12) and (13). The two airflow sections (12) and (13) are twisted with the rate of twist from the root end to the tip end being nonuniform. The twist or ratio of the degree increase in the angle of attack over each inch in length deceases from root end to the tip end.

Abstract: A rotor blade having a wing and beam construction for a tip shroud is disclosed. Various construction details are developed for providing a transition zone that extends from the suction side and pressure side of the airfoil to provide a flow path surface of the shroud. In one detailed embodiment, the transition zone over substantially all of its extent between the leading edge region and the trailing edge region is contoured to extend to the sides of the wings to provide a spanwise taper that extends to the side of the wing.

Abstract: Twisted leaf shaped ceiling fan blades for low, medium and high speed operation of less than approximately 250 rpm. The novel blades twisted blades can be configured for 52?, 54?, 56?, 60? and 64? diameter fans, and have less blades (3 for example) than conventional flat type bladed fans having 4, 5 blades and have greater air flow and less power draw results than the conventional flat 54 inch fans. Any of the novel twisted blades of 48?, 52?, 54?, 56?, 60? and 64? can be run at reduced speeds, drawing less Watts than conventional fans and still perform better with more air flow and less problems than conventional flat type conventional leaf shaped blades.

Abstract: A wind turbine blade transversely subdivided into two or more separate modules (1-2) consisting of outer aerodynamic walls or hulls (4) and a longitudinal inner reinforcing structure (3). The modules include coupling means at the ends of the longitudinal reinforcing structure (3), which means consist of flanges (5-7, 6-8) projecting into respective portions with alignable openings (9) for receiving coupling elements.

Abstract: An impeller blade includes an elongate impeller blade body having opposing proximal and distal ends, opposing first and second edges extending from the proximal end to the distal end, and opposing upper and lower sides. The lower side includes a major generally concave channel extending from an open end thereof at the distal end of the impeller blade body to a closed end thereof adjacent to the proximal end of the impeller blade body.

Abstract: An apparatus is provided for generating electricity in response to a fluid flow. The apparatus includes a top rotor element coupled to a center axis with an arm extending substantially perpendicular to a center axis. The arm moves in response to the fluid flow to rotate the center axis. The apparatus also includes a bottom rotor element coupled to the center axis also having an arm extending substantially perpendicular to the center axis. The arm of the bottom rotor element is substantially fixed in a position relative to the arm of the top rotor element, wherein the position is offset about the center axis by about 90° from the top rotor element.

Abstract: The invention concerns a rotor blade of a wind power installation and a wind power installation. One advantage of the present invention is to provide a rotor blade having a rotor blade profile, and a wind power installation, which has better efficiency than hitherto. A rotor blade of a wind power installation, wherein the rotor blade has a thickness reserve approximately in the range of between 15% and 40%, preferably in the range of between about 23% and 28%, and wherein the greatest profile thickness is between about 20% and 45%, preferably between about 32% and 36%.

Abstract: An axial impeller (1), with enhanced flow, rotating in a plane (XY) about an axis (2) comprises a central hub (3), whose diameter is smaller than the diameter of the drive motor (3a), a plurality of blades (4) having a base (5) and a tip (6), the blades (4) being delimited by a convex leading edge (7) and by a convex trailing edge (8), whose projections onto the plane of rotation of the impeller are each defined by circular arc segments; the blades (4) are composed of sections having aerodynamic profiles (18) each having a decreasing length and an increasingly curved shape starting at the edge towards the hub; towards the hub each blade (4) has a box-shaped portion (20) that forms a wide scat (21) providing housing for an drive motor (3a) having a diameter that corresponds substantially to the seat (21).

Abstract: A blade (10, FIG. 1) for a gas turbine engine includes an aerofoil portion (12, FIG. 1) and a root portion 14 defined by concave and convex walls 16, 18 having opposing inner surfaces 16a, 18a. A reinforcing member 20 is located between the concave and convex walls 16, 18 and is bonded to the inner surfaces 16a, 18a thereof, and the root portion 14 includes an unbonded region 24a, 24b in which the reinforcing member 20 contacts an inner surface 16a, 18a of one of the concave and convex walls 16, 18 but is not bonded thereto.

Abstract: An impeller for a pump, particularly for a cooling water pump of an internal combustion engine, includes a hub (11), a cover disc (14) which is disposed on the intake side and is provided with a central opening (15) for sucking in a conveyed medium, and at least one blade (13) that is connected to the cover disc (14) located on the intake side so as to form a single piece therewith and is provided with an inner section (13a) located in the region of the central opening and an outer section (13b) located in the region of the cover disc (14). The impeller achieves a high degree of efficiency yet is easily produced by embodying the impeller (5) in a completely open manner on the pressure side lying opposite the cover disc (14) and by configuring the inner section (13a) of the blade (13) in a three-dimensionally bent manner while configuring the outer section (13b) thereof in an essentially two-dimensionally bent manner.

Abstract: A turbine wheel for driving rapidly rotating tools, in the form of a circular disk or ring, configured for mounting so as to be rotatable about an axis. Disposed thereon in circular formation are turbine blades having axially parallel front and back faces curved in the radial direction. The front face has a lesser radius of curvature (R3, R4), at least in portions, than the back face. This feature allows the turbine wheel to fit into the conventional turbine housings without relatively major redesign and with, at most, slight modifications. The turbine wheel can achieve higher torque than previous turbine wheels at the required high rotational speeds. Thus, a greater quantity of material can be applied to the spraying dome or a spraying disk without a detrimental braking. Surfaces to be sprayed can be provided with a uniform coat of material in shorter time.

Abstract: A gas turbine engine blade is laser shock peened by laser shock peening a thin airfoil of the blade, forming a laser shock induced twist in the airfoil, and shot peening a portion of the airfoil to counter the laser shock induced twist in the airfoil. The shot peening may be performed before or after the laser shock peening. The shot peening may be applied over a laser shock peened surface formed by the laser shock peening. The shot peening may be performed asymmetrically on asymmetrically shot peened pressure and suction side areas of pressure and suction sides, respectively, of the airfoil. A shot peened patch near a blade tip may be formed on one of pressure and suction sides of the airfoil wherein the airfoil extends radially outwardly from a blade platform to the blade tip of the blade.

Abstract: Twisted ceiling fan blades for low, medium and high speed operation of less than approximately 250 rpm. The novel blades twisted blades can be configured for 60? and 64? diameter fans, and have less blades (3 for example) than conventional flat type bladed fans having 4, 5 blades and have greater air flow and less power draw results than the conventional flat 54 inch fans. Any of the novel twisted blades of 54?, 60? and 64? can be run at reduced speeds, drawing less Watts than conventional fans and still perform better with more air flow and less problems than conventional flat type conventional blades.

Abstract: A method for laser shock peening a gas turbine engine blade includes laser shock peening a thin airfoil of the blade, forming a laser shock induced twist in the airfoil, and altering a root of the blade to counter the laser shock induced twist in the airfoil. The altering may be done after the laser shock peening. The altering may be done before the laser shock peening during casting or forging of the blade or during a machining or broaching procedure which cuts a shape of the root. One embodiment of the altering includes forming the root with an altered root centerline having an altered centerline angle with respect to a predetermined root centerline designed for a non-laser shock peened airfoil of the blade.

Abstract: A Francis turbine with an improved shape of blades, which can reduce cavitations generated on the surface of the blades or reduce the secondary flow around the blades, is provided. A Francis turbine comprises a rotating shaft, a crown, a plurality of blades, and a band. The crown can rotate with the rotating shaft. The blades are circumferentially arranged on the crown, each of which including an inner end as a trailing edge. The band is coaxially coupled with the crown by the blades. The rotating shaft, the crown, the blades, and the band as a whole rotate toward a turbine direction during a turbine operation. A projected profile of the trailing edge on a perpendicular plane, which is perpendicular to a center axis of the rotating shaft, is curved toward a direction opposite to the turbine direction at least in the crown side.

Abstract: A Francis runner and a hydraulic turbine equipped with such a runner, wherein the runner includes a ceiling, a belt, and blades which extend between the ceiling and the belt and which define liquid flow channels therebetween. A ratio (e/L) of a maximum thickness Ce) of each blade to an average developed length (L) of an average fibre of each blade is between 0.1 and 0.2. At a leading edge of each blade, the average fibre is oriented, over essentially an entire height of the leading edge, along a straight line (?23), which forms an angle (?) greater than 90° relative to a line (U) defining a direction of rotation of the leading edge of the runner.

Abstract: A molten metal pump system which includes a particle relief passageway between the vanes on the impeller and the pump base, the particle relief passageway being a predetermined size to allow particles of a predetermined size to pass between the plurality of vanes and the interior walls of the impeller aperture of the pump base. Part or all of the particle relief passageway may, but need not, be as a result of a shoulder on the radially outward end of the plurality of vanes in the inlet side of the impeller.

Abstract: A rotor blade having a wing and beam construction for a tip shroud is disclosed. Various construction details are developed for providing the shroud with a depression in the shroud and a transition zone that extends from the suction side and pressure side of the airfoil to provide a flow path surface of the shroud. In one detailed embodiment, the tip shroud has a depression generally outwardly of the airfoil and generally following the curve of the pressure and suction sides of the airfoil from the leading edge region to the trailing edge region.

Abstract: Ceiling fan energy consumption efficiency is enhanced with fan blades that have an angle attack that decreases from root end to tip end at higher rates of decrease nearer their tip ends than at their root ends.

Abstract: A sky turbine, having impeller blades with a plurality of panels that can telescope inward and outward. The pitch of the panels can be adjusted, and the pitch of each panel on a blade, passing from the innermost panel to the outermost panel, differs from the pitch of the previous panel by a certain adjustable amount. The sky turbine is preferably mounted above a city at a sufficiently high elevation that air current will be generally faster than just above the ground. In the preferred embodiments, a wing with two pods is pivotally mounted on a tower. Each pod has front and rear shafts, from which four blades extend. Servomotors cause the wing to turn so that its center of symmetry is parallel to the direction the sky is moving, cause the pitch of the panels of the blades to change, and cause the panels of the blades to telescope.

Abstract: A Francis turbine with a improved shape of blades to reduce the secondary flow around the blades and improve the hydraulic efficiency is provided. A Francis turbine comprises a rotating shaft, a crown, a plurality of blades and a band. The band is coaxially coupled with the crown by the blades and the rotating shaft, the crown, the blades, and the band as a whole are driven by water and rotate toward a turbine direction during a turbine operation. On a leading edge of at least one of the blades, a local maximum point exists between the crown and the band. The leading edge leans toward the turbine direction from the band connecting point, where the band and the leading edge are connected. And, a circumferential distance in the rotating direction between the band connecting point and the leading edge is the largest at the local maximum point.

Abstract: A compressor blade (26) comprises an aerofoil (36) and a root (38). The aerofoil (36) comprises a concave wall (40) extending from a leading edge (44) to a trailing edge (46) and a convex wall (42) extending from the leading edge (44) to the trailing edge (46). The aerofoil (36) defines at least one internal chamber (48). The root (38) is connected to the aerofoil (36) and the root (38) has a base (50) remote from the aerofoil (38) and at least one aperture (52) extends from the base (50) to the at least one internal chamber (48) in the aerofoil (36). The dimensions, shape and position of the least one aperture (52) are selected such that the root (38) is deformable. This reduces the weight of the containment region of a fan casing (28).

Abstract: An impeller is applied to a centrifugal fan and includes fan blades and a hub. Each fan blade includes a first portion and a second portion. The first portion is located relatively close to the hub and the first portion is coupled to the second portion. The first portion has a windward side and a leeward side, and the windward side is parallel to the leeward side. The second portion is located relatively far away from the hub. The second portion has a windward side and a leeward side, and the windward side and the leeward side are two curved surfaces with different specific curvatures.

Abstract: An easily producible turbine nozzle for a gas turbine engine is provided, which is capable of preventing flutter of the turbine nozzle during operation of the gas turbine engine. The turbine nozzle comprises airfoils stacked along the stacking axis. The high curvature portions on suction surface in airfoil section successively formed along the stacking axis of the airfoil describe a parabola line that curves toward the pressure side of the airfoil when seen from the front or rear of the turbine nozzle. The high curvature portions on suction surface in airfoil section curve most at the center along the stacking axis of the airfoil from a straight line that connects with a first intersection between the parabola line and an inner band in the turbine nozzle and with a second intersection between the parabola line and an outer band in the turbine nozzle. The maximum curvature falls within a range from 0.02 to 0.03-fold of the stacking axis of the airfoil.

Abstract: A rotary turbojet blade comprises a plurality of blade sections extending along a line of the centers of gravity of said sections between a base and a tip, said blade presenting along a radial axis a bottom portion, an intermediate portion, and a top portion, said bottom portion presenting a longitudinal angle of inclination for a leading edge line, said intermediate portion presenting a backward longitudinal angle of inclination for said leading edge line, and said top portion presenting a backward longitudinal angle of inclination for said leading edge line and a tangential angle of inclination for said line of the centers of gravity in a direction opposite to the direction of rotation of said blade.

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 high-turning and high-transonic blade for use in a blade cascade of an axial-flow compressor, wherein a distribution of flow speed on an extrados at a leading edge of the blade has a supersonic region of a substantially constant flow speed in the rear of a first large value of the flow speed and inside a position corresponding to 15% of a chord length from the leading edge. The supersonic region is established so that a value obtained by the division of a difference between Mach numbers at front and rear ends of the supersonic region by a chord-wise length of the supersonic region is smaller than 1, and the maximum Mach number in the supersonic region is smaller than 1.4. A first large shock wave is positively generated at a position where the flow speed assumes a first maximum value, whereby a second shock wave generated in the supersonic region of the substantially constant flow speed in the rear of such a position can be weakened.

Abstract: A fan motor with an increased amount of air drawn in toward fan blades so as to obtain a desirable airflow characteristic. A fan motor includes a rotor and a plurality of fan blades provided radially therefrom. Each fan blade is provided with an air intake part on a proximal side and a radial part on a distal side, including a first front surface on the former side and a second front surface on the latter side. The first and second front surfaces have different curvatures. Thus, air F can be impelled out toward a perimetric direction, and at the same time the intake of air toward the fan blades is promoted. Accordingly, the amount of air to be drawn in toward the fan blades is increased, thereby obtaining desirable airflow characteristic.

Abstract: An axial flow fan of high efficiency and low noise level is provided. The fan includes a motor, an impeller having a plurality of blades around a hub fitted to the motor, and a fan casing having an air inlet on one side and an air outlet on the other, wherein a radial position with a maximum setting angle in a blade section, and a radial position with a contour of a leading edge portion in a fluid flowing direction forming a projecting apex in the flowing direction are located between 60% and 80% of the outside diameter of the impeller.

Abstract: A novel modification of a Savonius rotor used as a wind turbine provides an exhaust channel in each vane. The vane of the modified Savonius rotor is formed into an “S” shape. The air that enters a given end of the vane exits that end through the new exhaust channel into the freestream. A plurality of modified Savonius rotors are stacked one on top of the other for self-starting and greater power output. The outer surfaces of the entire assembly may be coated with photo voltaic cell material for additional energy production. In one embodiment of the invention, a cone shaped solar collector is placed on top of the entire modified Savonius rotor assembly.

Abstract: The present invention relates to a ceiling fan blade capable of producing full wind pressure and much wind. The solution of the present invention is to form a front and a rear wind receiving surfaces on the ceiling fan blade. A tangent angle of the rear wind-receiving surface is bigger than that of the front wind-receiving surface. A wavy wind guide surface is formed between the two wind receiving surfaces. The wavy wind guide surface and the two wind receiving surfaces can effectively increase the wind pressure and the wind; in addition, sinuous flow is substantially reduced when the blade is rotating.

Abstract: A monodirectional impeller for centrifugal electric pumps having a permanent-magnet synchronous motor, having vanes which are deformable at least along part of their extension so as to change their curvature, when loaded, in one direction of rotation, so that the power required for rotation in that direction is greater than the maximum power that can be delivered by the motor.

Abstract: The present invention is directed to a tickler impeller and agitation system for use in stirred slurry reactors and storage tanks. The tickler impeller when mounted on a shaft is effective for providing an inward and downward swirl in a slurry medium which directs solids suspended in the slurry towards the bottom of the tank and towards the shaft on which the impeller is mounted. Directing solids suspended in a slurry downwards and towards the center of the tank rather than pushing those solids away from the center reduces solid deposits on the side of the tank, facilitates draining of the tank, and reduces nozzle starving and pump starvation.

Abstract: Fans according to some embodiments of the present invention include a spider, a central hub coupled to the spider, and two or more fan blades. One or more fan design features can be employed (alone or in combination) in the fans of the present invention, including the use of spider arms and/or fan blades having twisted shapes, spider lobes having cupped shapes, spiders and/or fan blades having thinner dimensions than conventional spider and fan blades in similarly-sized fans, fan blades having narrower widths, larger camber-to-chord ratios and/or tapering camber-to-chord ratios, and embossments located on the spider or the fan blades of the fan. In addition, pre-balanced spider assemblies can be employed as an alternative to balancing a fan after assembly.

Abstract: The present invention relates to a structural reinforcement of the fan wheel of a mixed flow fan. The structure of the fan wheel comprises a hub and several blades attached to the outer rim of this hub. One side of the hub consists of a hollow space, the other side consists of a flat surface. The blades are attached to the outer rim of the hub in equal distances. The outer rim of the hub is beveled. The flat surface acts as the air inlet side, the hollow side acts as the air outlet side. The surfaces of the blades are to bend. The part connecting the blades to the hub is also to bend. Therefore cambered channels form in the gaps between the blades, which are arranged in equal distances. Through use of this structure the operational area for the characteristic curve of the mixed flow fan is increased and the possibility of a loss of speed is reduced. Thus the overall performance of the fan is improved.