Abstract: Thick airfoil families with desirable aerodynamic performance with minimal airfoil induced noise. The airfoil families are suitable for a variety of wind turbine designs and are particularly well-suited for use with horizontal axis wind turbines (HAWTs) with constant or variable speed using pitch and/or stall control. In exemplary embodiments, a first family of three thick airfoils is provided for use with small wind turbines and second family of three thick airfoils is provided for use with very large machines, e.g., an airfoil defined for each of three blade radial stations or blade portions defined along the length of a blade. Each of the families is designed to provide a high maximum lift coefficient or high lift, to exhibit docile stalls, to be relatively insensitive to roughness, and to achieve a low profile drag.

Abstract: A wind turbine blade having an aerodynamic profile (5) with a leading edge (11), a trailing edge (13) and suction and pressure sides (17, 19) between the leading edge (11) and the trailing edge (13) which has, on at least one part of the wind turbine blade, a Trailing Edge Region (TER), the transversal section of which increases in the direction of the trailing edge (13). Said trailing edge region (TER) preferably has a divergent form with a curved concave surface on its lower part.

Abstract: A system for reducing compressor noise includes a rotor having a plurality of blades. The blades have a nominal geometry characterized by a blade parameter. At least some of the blades are mistuned, such that they differ from the nominal geometry by greater than a manufacturing tolerance in the blade parameter. The blades produce shock waves at a blade passing frequency, and the mistuned blades shift acoustic energy away from the blade passing frequency to multiple lower amplitude tones at other frequencies. The system is configurable to be deployed with an inlet silencer that preferentially absorbs acoustic energy at some of the shifted frequencies.

Abstract: A rotor blade for a gas turbine engine includes an airfoil that extends in span between a root and a tip region. A leading edge and a trailing edge of the airfoil section extend between a chord line of the airfoil. A sweep angle is defined at the leading edge of the airfoil section, and a dihedral angle is defined relative to the chord line of the airfoil section. The sweep angle and the dihedral angle are localized at the tip region of the airfoil section.

Abstract: An airfoil for use as rotor blades in compressors for turbomachines, such as gas turbine engines. The airfoil includes increased forward sweep and forward dihedral effective to reduce losses generated by interaction of tip clearance flow, secondary flows and passage shocks.

Abstract: An aerodynamic profile and a wind turbine comprising a wind turbine blade with reduced sensitivity towards surface irregularities are provided. The invention is mainly directed towards pitch-regulated wind turbines, which are operated at variable rotor speed and have blades longer than about 30 meters.

Abstract: Sectional profiles close to a tip 124 and a part between a midportion 125 and a hub 123 are shifted to the upstream of an operating fluid flow in a sweep direction. Accordingly, an S shape is formed in which the tip 124 and the part between the midportion 125 and the hub 123 protrude. As a result, it is possible reduce various losses due to shook, waves, thereby forming a transonic airfoil having an excellent aerodynamic characteristic.

Abstract: Blades for rotorcraft are designed and/or implemented with rotor blades having a swept portion that occupies at least 20-40% of a length of the blade. Forward and aft sweeps are contemplated, with up to 20° or more of sweep. The swept portion preferably has a thickness ration of at least 10-20% at R80, and can have a tapered planform with a relatively outboard section having a smaller chord than a relatively inboard section. Contemplated design methods include optimizing or otherwise designing the rotor blade planform and lift distribution along the blade for efficiency in various flight conditions without taking into account the detrimental effects of high Mach numbers, and then using sweep angle, airfoil thickness and transonic airfoil shaping to maintain the lift distribution, low drag and low noise level at real Mach numbers at the various blade stations at the various flight conditions.

Abstract: A blade assembly including an outboard blade segment is provided. The outboard blade segment includes an outboard blade shell, first and second outboard bulkheads situated within the outboard blade shell, and an outer box supported by and aligned by the outboard bulkheads. The blade assembly also includes an inboard blade segment including an inboard blade shell, first and second inboard bulkheads situated within the inboard blade shell, and an inner box supported by and aligned by the inboard bulkheads. Further, the inner and the outer boxes are tapered to facilitate insertion of the inner box into the outer box and coupling of the inner and outer boxes.

Abstract: Disclosed is a surface of the blade having a cylindrical root portion, an airfoil portion and a transition portion connecting the root portion with the airfoil portion, wherein the blade comprises a shoulder at the border between the transition portion to the airfoil portion, wherein the blade comprises an element which is arranged substantially at the root portion and/or at the transition portion which creates a slot between the element and the surface of the blade.

Abstract: A fan module, particularly for cooling motor vehicle engines allows for improved cooling of the fan motor. The fan housing (101) in which the fan motor (105) is arranged has fixed air-channeling elements (109) which are arranged in the region of a fan hub (2) of the fan wheel (1) driven by the fan motor (105) and which only partially cover an outlet cross section (102, 118) defined by the fan housing (101).

Abstract: An improved rotor blade used in combination with a submersible electrical generator comprises a rotor base with width BW, a leading edge, a tip, and a trailing edge. The leading edge and the trailing edge are defined as elliptical curves having a radius of 8.0 BW. The rotor has a surface area profile substantially in accordance with the Cartesian coordinate values X and Y set forth in Table I. The rotor blade can be functionally connected to a rotor shaft through a pivotal support axial which allows the pitch of the blade to be set and maintained. The pitch is set to harness the kinetic energy of flowing water for generating electricity.

Abstract: A wind turbine rotor blade is provided which includes a root end and a tip end located opposite the root end. A leading edge extends from the root end to the tip end. A trailing edge extends from the root end to the tip end. A span direction is defined by a line extending linearly from the root end to the tip end. A chord direction is perpendicular to the span direction and lies in the plane extending through the leading edge and the trailing edge. A shoulder is the point of the maximum chord-wise extension. An airfoil portion extends from the shoulder to the tip end. The airfoil portion comprises a span-wise interval begging before the tip end and extending to or close to the tip end and in which the distribution of the chord-wise extension is increased as compared to the load optimised distribution of the chord-wise extension.

Abstract: A method of fabricating an airfoil is provided. The method includes fabricating at least one airfoil including a suction side and a pressure side coupled together at a leading edge and a trailing edge, wherein the airfoil includes a plurality of first and second chord sections each extending between the trailing and leading edges, wherein at least one of the first chord sections extends outward from the pressure side of the airfoil at the trailing edge, and at least one of the second chord sections extends outward from the suction side of the airfoil at the trailing edge.

Abstract: A method for manufacturing of a fiber reinforced laminate is provided. A part of the laminate is build up to a determined thickness. A layer of wrinkle-preventing material is placed on top of the partially completed laminate. The layer of wrinkle-preventing material has a greater stiffness than the stiffness of a layer of similar thickness of the uncured laminate. Further on a new part of the laminate is build up to a determined thickness. In case the thickness of the laminate built up is not as large as a desired thickness of the completed laminate, the placing of the layer and the building of a new part of laminate is repeated until the thickness of the laminate built up is equal to the desired thickness of the completed laminate.

Abstract: A ceiling fan comprising a disc-like stator provided with a fixed shaft at the center, an annular rotor disposed in proximity to the periphery of the stator, a supporting frame fixed to the rotor and rotatably supported by the fixed shaft; a fan blade fixed to the supporting frame; and a retaining member having one end fixed to the supporting frame together with the fan blade and the other end coupled to the fan blade, wherein the fan blade comprises a root portion fixed to the supporting frame, a blade portion coupled with the retaining member, and an offset portion formed by bending between the root portion and the blade portion, thereby preventing the fan blade from being damaged easily even when it is impressed with a load and ensuring the safety even if the fan blade is broken since the blade portion is held coupled to the rotor side.

Abstract: A rotor blade for a wind turbine is disclosed. The rotor blade includes a flange section configured to connect the rotor blade to a rotor hub; and an airfoil section extending outward from the flange section. The flange section is comprised of a carbon reinforced polymer.

Abstract: A fan apparatus includes a fan section having a hollow housing with an inlet and an outlet, and a hollow duct section disposed on the outlet side of the fan section. The housing and the duct section are coupled by a coupling member.

Abstract: The course of the leading edges of turbomachine components, such as rotor blades and stator vanes is defined mathematically exactly and repeatedly as well as aerodynamically advantageously by the respective axial coordinate in the direction of the machine axis in relation to the blade height in percent, extending from the blade tip as per equation (1): axial ? ? coordinate ? [ % ? ? blade ? ? height ] = 1 5 ? ? extension ? [ % ? ? blade ? ? height ] ? ? tan ? ? sweep tip ( 1 - ? - 5 ? ( 100 ? % - blade ? ? height ? [ % ] ) extention ? [ % ? ? blade ? ? height ] ) and extending from the blade hub as per equation (2): axial ? ? coordinate ? [ % ? ? blade ? ? height ] = 1 5 ? ? extension ? [ % ? ? blade ? ? height ] ? ? tan ? ? sweep hub ( 1 - ? - 5 ? ? blade ? ? height ? [ % ] extention ? [ % ? ? blade ? ? height ] ) where sweep

Abstract: The suction surface blade angle of a transonic fan blade, subject in use to a shock wave, progressively reduces along part of the suction surface, beginning at a position upstream of the shock wave position. The increased area variation at the location of the shock results in the shock position becoming less sensitive to small geometric imperfections. The reduced shock sensitivity reduces the variation in aerodynamic load and hence reduces the untwist variation with respect to small geometric imperfections. This has the effect of stabilising the untwist deflections of the fan.

Abstract: A rotor blade for a wind turbine is disclosed. The rotor blade includes a root, a tip, and a body extending from the root, the body including a pressure side and a suction side extending between a leading edge and a trailing edge. The rotor blade further includes a winglet extending between the body and the tip, the winglet including a pressure side and a suction side extending between a leading edge and a trailing edge. The winglet further includes a transition section and defines a height, a sweep angle, an outboard cant angle, and a twist angle. The sweep angle, the outboard cant angle, and the twist angle change continuously throughout the transition section.

Abstract: A tip device to act as an outboard continuation of an aircraft wing or other aerodynamic lifting surface has a downward cant angle, a leading edge swept back in relation to the leading edge of the inboard lifting surface, and a chord reducing in the outboard direction of the device. A favourable balance between induced drag reduction and increased wing root bending moment can thereby be achieved. Preferably the device also has an upwardly canted portion at its root end so that the downward cant commences from a relatively elevated spanwise location, thereby alleviating any ground clearance problems.

Abstract: A rotor blade for a wind turbine is disclosed. The rotor blade may comprise a root portion, a tip, and a body extending between the root portion and the tip. The body may include a pressure side and a suction side. Additionally, a winglet may be defined by the body. The winglet may terminate at the tip of the rotor blade and extend inwardly in a direction of the suction side of the body. Further, a bend may be defined in the body such that a portion of the body extends outwardly in a direction of the pressure side of the body.

Abstract: In an axial flow fan, a line extending from a center axis and passing a corner where a following edge and a radially outer edge of a blade of an impeller meet is arranged forwardly in a rotational direction from an another corner where a leading edge of the blade and a radially outer surface of a hub meet. Furthermore, a camber ratio of the blade, which is minimum at a joint with the hub across the blade, monotonically increases to be maximum at the radially outer edge of the blade.

Abstract: A wind turbine apparatus reactive to fluid flow comprises a turbine assembly (64) rotatably supported for generating energy and a fluid flow control assembly (104, 106, 108, 110, 112) to control fluid flow acting upon the turbine assembly (64). The turbine assembly (64) includes turbine blades (84) that extend from first ends (86) with chords (C) coincident to first end radials (R1) to second ends (88) disposed on second end radials (R2) with the chords (C) coincident to the turbine axis (B). The turbine blades (84) present faces (98) at varying angles of attack between the first end radials (R1) and the turbine axis (B) to always position or present a portion of the turbine blades (84) perpendicularly to fluid flow at various transverse angles to the turbine axis (B).

Abstract: Rotor blades are pre-bent in at least one of a flap direction and a lag direction, wherein the pre-bent portion comprises at least 20-60% of the length of the blade. Preferred methods include analyzing the rotor dynamic behavior using computational methods, deciding on the operational case (rotor lift load, forward speed, etc.) in which the loads and vibration reductions are desired, and using the computed results to decide on an amount of pre-bending of the unloaded blade so that it comes closer to the feather axis under load. Another class of preferred methods models the bending of a first blade in flight loading conditions, and then designs a second blade having a pre-bend in approximately an equal in magnitude and opposite in direction to the bending. It is contemplated that such “pre-bent” blades can significantly reduce rotor loads and vibration levels of rotorcraft equipped with semi-rigid or rigid rotors.

Abstract: A shroud includes a body portion 5B, a mount 7 positioned at a center of the body portion 5B and supporting rotary vane wheel driver 6, and multiple support beams 10 radially extending from the mount 7 and joining the mount 7 and the body portion 5B, where each of the support beams 10 becomes thicker from an upstream side of a flow direction of air toward a downstream side thereof, and an edge portion 10ti of each of the support beams 10 on the downstream side of the flow direction of the air discharged by the rotary vane wheel 8 is oriented in a direction parallel to a rotation axis of the rotary vane wheel 8, and the edge portion on the upstream side is oriented in a direction opposite to a rotation direction of the rotary vane wheel 8.

Abstract: A turbine wheel for a gas operated medical handpiece includes a plurality of blades which extend in radial direction from a hub and extend in axial direction from a side ring web of the turbine wheel, and the front side of which is substantially concavely curved about an approximately radially running first axis of curvature. In order to increase the drive power or to better exploit the drive power at least one blade has at least in an axial end region an inclination surface which is inclined in the axial direction towards the front side.

Abstract: A blade includes a plurality of first fibers, wherein each of the plurality of first fibers is angled between about 5° and about 35° with respect to a pitch axis of the blade, and a plurality of second fibers, wherein each of the plurality of second fibers is angled between about 95° and about 125° with respect to the pitch axis of the blade.

Abstract: The present invention provides an axial fan including a hub adapted for rotation about a central axis and a plurality of blades extending radially outwardly from the hub and arranged about the central axis. Each of the blades includes a root, a tip, a leading edge between the root and the tip, and a trailing edge between the root and the tip. Each of the blades defines a blade radius between the blade tips and the central axis. Each of the blades defines a decreasing skew angle within the outer 20% of the blade radius. The ratio of blade pitch to average blade pitch increases from a lowest value to a highest value within the outer 20% of the blade radius. The highest value is about 30% to about 75% greater than the lowest value.

Abstract: A rotor blade of a wind power installation in which the rotor blade, in particular in the central region of the rotor, the so-called main board, has a lift-drag ratio which in the region of about ±2° from the optimum pitch angle has a lift-drag ratio value of more than 80%, preferably 90% and more of the maximum value of the lift-drag ratio.

Abstract: A turbine blade is provided, comprising a stator-side end located toward a stationary stator cylinder of the turbine, a rotor-side end located toward an axial rotor of the turbine, a leading edge located between the stator-side end and the rotor-side end, a trailing edge located between the stator-side end and the rotor-side end and located down-stream of the leading edge with respect to a fluid flow direction, wherein the rotor-side and stator-side ends have a negative sweep angle as measured between the instantaneous tangent of the blade surface and the fluid flow direction.

Abstract: A compressor, particularly a high-pressure compressor, of a gas turbine, particularly of an aircraft engine, includes at least one rotor and a number of blades (11, 12), which are assigned to the or to each rotor and which rotate together with the respective rotor. Each blade (11, 12) is delimited, in essence, by a flow entry edge or leading edge (16), a flow exit edge or trailing edge (17), and by a blade surface (20), which extends between the leading edge (16) and the trailing edge (17) while forming a suction side (18) and a pressure side. The leading edges (16) of the blades (11, 12) are slanted at a sweep angle that changes with the height of the respective blade (11, 12) in such a manner that the leading edges (16) comprise, in a radially external area (23) of the same, at least one forward sweep angle, a backward sweep angle or zero-sweep angle following in a radially external manner, and a forward sweep angle following, in a radially external manner, the backward sweep angle or the zero-sweep angle.

Abstract: A heat dissipation device (1) includes an electric fan (20) and a heat sink (10). The fan includes a fan impeller (40) which includes a hub (41) and a plurality of blades (42) extending radially and outwardly from the hub (41). The hub (41) includes an upper portion (417) and a bottom portion (413). An air inlet (411) is formed near the upper portion (417) and an air outlet (412) is formed near the bottom portion (413). The blades (42) have portions on the bottom portion of the hub which are extended toward a center of the air outlet for driving more air to the center of the air outlet (412), whereby more air can flow to a center of the heat sink.

Abstract: The present invention provides an axial fan assembly including a motor having an output shaft rotatable about a central axis and a shroud coupled to the motor. The shroud includes a substantially annular outlet bell centered on the central axis. The axial fan assembly also includes an axial fan having a hub coupled to the output shaft for rotation about the central axis, a plurality of blades extending radially outwardly from the hub and arranged about the central axis, a substantially circular band coupled to the tips of the blades, and a plurality of leakage stators positioned radially outwardly from the band and adjacent the outlet bell.

Abstract: The blades of a turbomachine comprise airfoils, which are bent such that the lean angle (?), defined as the angle which the stacking line of the airfoil includes with the radial direction, and measured in the direction of rotation (?), is variable along the width of the flow channel and decreases from the hub towards the housing.

Abstract: An improved rotor blade used in combination with a submersible electrical generator comprises a rotor base with width W, a leading edge, a tip, and a trailing edge. The leading edge and the trailing edge are defined as elliptical curves having a radius of 8.0(W). A straight line drawn from the front of the base to the lip forms a forty five degree angle with respect to the rotor base. The rotor blade is functionally connected to a rotor shaft through a pivotal support axial which allows the pitch of the blade to be set and maintained. The pitch is set to harness the kinetic energy of flowing water thereby generating electricity.

Abstract: A wind turbine rotor blade extension portion having a plurality of segments, located adjacent one another in a span-wise sense. An interface between adjacent segments is configured to minimise disruption to fluid passing thereover and to inhibit transmission of longitudinal loads between segments. Each segment has a first surface and a second surface. The first surface is spaced from the second surface at a proximal region of the extension portion and the first surface is connected to the second surface at a distal region of the extension portion to thereby generate a fair surface for a rotor blade to which the extension portion is connected, in use.

Abstract: A marine propeller is provided with three blades, a skew angle of approximately 33 degrees, a rake angle of approximately 28.5 degrees, and a blade area ratio (BAR) of approximately 60 degrees. The rake is preferably progressive. Each of the blades is preferably tail loaded.

Abstract: A cooling fan has a metal spacer, a boss made of Nylon integrally formed with the spacer by an insert molding and seven blades extending outward therefrom. A skew angle of about 30 degrees is provided at a connecting portion or a base end portion of the blade to the boss so as to be inclined backward in relation to a rotating direction of the cooling fan. To the contrary, a skew angle of about 8 degrees is provided at a portion extending from the connecting portion to the leading end of the blade so as to be inclined forward in relation to the rotating direction.

Abstract: Main rotor blades of the dual, counter-rotating, rigid coaxial rotor system exhibit a unique unconventional combination of positive and negative twist gradients in which the rotor system rotor Figure of Merit (hover efficiency) is improved by providing a dissimilar twist distribution between the lower rotor blade and the upper rotor blades. This improvement is specifically a result of reduced profile drag of the lower rotor system, achieved by driving the effective operating condition of the lower rotor blades to be similar to the upper rotor blade such that the tip drag losses of the lower main rotor have been reduced considerably using a mathematically vigorous approach. While minimal induced power consumption resulted due to the dissimilar lower main rotor twist, a significant profile power benefit is realized, resulting in the improved hover efficiency with essentially no reduction in rotor forward flight performance.

Abstract: Blades mounted on a circumferential outer surface of a hub of an axial flow fan do not deform even when rotated at high speed, thus promoting structural stability. The direction of the sweeping angle of each blade alternately changes between the blade root and tip. A chord length between the blade leading and trailing edges gradually decreases from the blade root to an intermediate portion of the blade, and the chord length gradually increases from a predetermined position on the intermediate portion of the blade to the blade tip.

Abstract: An impeller rotatable in a direction of rotation in a centrifugal compressor including an intake ring. The impeller includes a back plate having a shaft portion and a plurality of blades. Each blade extends from the back plate and includes an inducer portion adapted to draw fluid into the impeller and including a leading edge and an exducer portion adapted to discharge the fluid from the impeller and including a trailing edge. A blade pressure side is defined between the leading edge, the trailing edge, the back plate, and a blade tip. The pressure side is convex from the back plate to the blade tip. A blade suction side opposite the pressure side is defined between the leading edge, the trailing edge, the back plate, and the blade tip. The suction side being concave from the back plate to the blade tip.

Abstract: A rotor blade for a wind turbine is provided, wherein the rotor blade has radial bores in a wall of a blade root portion, the radial bores being staggered in a longitudinal direction of the rotor blade, and longitudinal bores in the wall of the blade root portion, wherein each of the longitudinal bores extends from a blade flange to a corresponding radial bore.

Abstract: A turbine fuel pump includes an impeller having blades, each including a linear blade portion extending linearly in the radial direction of the impeller and a curved blade portion extending circularly curvedly from the head of the linear blade portion to the forward side of the impeller as viewed in the direction of rotation of the impeller. The linear blade portion has a length of (? to ?)×H, where H is an overall length of the impeller.

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: An axial fan (1) rotating in a plane (XY) about an axis (2) comprises a central hub (3), a plurality of blades (4), which have a root (5) and a tip (6), the blades (4) being delimited by a convex leading edge (7) and by a concave trailing edge (8), their projections in the fan rotation plane each being formed by circular arc segments; the blades (4) are made from sections with aerodynamic profiles, each with decreasing length and more curved from the perimeter to the hub.

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 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 cooling system includes a cooling fan with an outlet and an inlet and a shroud surrounding at least a portion of the cooling fan. The cooling fan includes a plurality of fan blades, and each fan blade includes an inlet portion and an outlet portion that define an outer periphery of the fan blade. The outlet portion has a profile defined by a radial distance, perpendicular from a central axis of the fan, increasing in a direction towards the outlet. The average angle, relative to a central axis of the fan, of either a profile of the outlet portion or a profile of a portion of the shroud surrounding the outlet portion is between about ±15° of an average angle to the central axis at which a flow of fluid exits the outer periphery of the fan blades or between about 20° and about 70°.