Abstract: Radial cross sections of front sides in rotational direction of impellers attached to a pump shaft obliquely to a circumferential direction from an upstream side toward a downstream side have concave shapes protruding toward the upstream side, and radial cross sections of rear sides in rotational direction of the impellers have concave shapes protruding toward the downstream side.

Abstract: A fan blade comprises an airfoil having an upper surface with region that has a generally elliptical curvature. In some examples, the lower surface has a convex region and a concave region. The curvature of the concave region corresponds with the generally elliptical curvature of the upper surface; while the curvature of the convex region is defined by a substantially constant radius. Some examples also include a trailing edge flap region, which may itself include a first flap portion and a second flap portion. When mounted to a rotating hub member fan, blades with elliptical curvatures may provide air movement at significant efficiencies.

Abstract: A bucket for a turbine is provided. The bucket includes an airfoil having a root portion, a tip portion, an airfoil shape, and a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table I, wherein Z is a distance from a platform on which the airfoil extends outwardly from, and X and Y are coordinates defining the profile at each distance Z from the platform. The bucket also includes a plurality of cooling passages extending between the root portion and tip portion of the airfoil, each of the plurality of cooling passages exiting at the tip portion, the plurality of cooling passages positioned in a camber line pattern.

Abstract: A mixed flow fan wheel has a convex hub, an axially-spaced away concave annular shroud, and a plurality of angularly distributed blades extending between and interconnecting the hub and shroud, all which cooperatively define a plurality of inter-blade flow channels. Each has a pressure surface and spaced suction surface extending not only between spaced inlet and discharge edges but also, crosswise thereto, spaced hub-side and shroud-side edges. Each discharge edge is convex relative a center of geometry of the blade therefor. Each inter-blade flow channel originates in a generally rectangular shape between flanking inlet edges and terminates in another generally rectangular shape between flanking discharge edges, with a procession of gradations of generally rectangular shapes forming a progressive transition therebetween. Moreover, each inter-blade flow channel twists or corkscrews from inlet thereof to the discharge.

Abstract: The invention teaches a turbine capable of receiving wind power and transferring wind power into mechanical energy, and capable of coupling with a generator. The turbine includes a generally flat horizontally mountable support plate capable of rotation about a central axis, the support plate having a plurality of pivot modifications located proximate to an outside circumference, and vanes coupled to the support plate at the pivot modification, each vane having a vane shaft coupled between a pivot modification on the first support plate and a pivot modification on a cap plate, each vane supported by a first rib and a second rib having an exterior edge defined as the exterior circumference edge of the head and the interior circumference edge of the tail, and a material attached between the exterior of the first rib and the exterior of the second rib.

Abstract: A vane assembly for a gas turbine engine, the assembly including a plurality of vanes 14 with an asymmetric organic metal/ceramic matrix composite lay up, such that when the vanes 14 are placed in tension or compression the profile of the vane 14 will alter by twisting or untwisting. Other materials may be provided for the vanes 14, and/or other methods may be used for placing the vanes 14 in tension or compression to provide positive changes to the profile thereof.

Abstract: A curved blade for use on horizontal wind turbines, the blade comprising a substantially semicircular tip portion, a substantially semicircular counter-tip portion opposite the tip portion, and a body portion extending between the tip portion and the counter-tip portion, the body portion being further defined by a concave curved trailing edge and a convex curved leading edge.

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: An impeller for a centrifugal fan includes a hub, impeller blades, and struts for supporting the blades in a circumferential array spaced apart from the hub. The number of struts can equal the number of blades, each strut extended from the hub to support two blades while each blade is supported by one strut nearer to its leading edge and another strut nearer to its trailing edge. Another arrangement features two struts per blade, with one of the struts coupled to the hub and a given blade, and the other strut coupled between the given blade and an adjacent blade. The struts are recessed inwardly from the leading and trailing edges to promote smoother air flow. The blades and struts are provided with aerodynamic thickness profiles to further improve air flow.

Abstract: A family of airfoils for a wind turbine blade. Each airfoil may include a blunt trailing edge, a substantially oval shaped suction side, and a substantially S-shaped pressure side.

Abstract: A now-noise blower is provided which reduces the turbulence of incoming air flow itself even if there is un-uniformity resulting from circumferential positions around a rotation shaft of air inlet passage. Such a blower includes a blade 1 having its outer circumferential edge 1c warped in a rotational direction and a bellmouth 5 covering the circumference of the blade at the air outlet side, wherein a surface of the bellmouth facing the blade has a convex-shaped first upstream expanding portion 5c upstream extending from a minimum inner diameter portion Pb3 and a concave-shaped second upstream expanding portion 5d further upstream extending, the second upstream expanding portion being continuous from the first upstream expanding portion.

Abstract: An object is to provide a turbomolecular pump with rotor and stator blades alternatively arranged that can prevent collision between the adjacent rotor and stator blades due to air inrush, which may take place due to vacuum break in a system operation, prevent excessive centrifugal force to a hub portion of a rotor, and further enhance pumping performance. A blade cross sectional profile taken along the circumferential direction of each of the rotor blades of a rotor blade stage has an upstream portion curved convexly backward in a rotational direction of the rotor and a downstream portion curved convexly forward in the rotational direction of the rotor, thereby forming the blade cross sectional profile into an S-shape or inversed S-shape.

Abstract: A turbine blade particularly useful in a vertical-axis wind turbine, characterized in that the blade includes a central region of a symmetrical airfoil configuration, and opposite end regions of a non-symmetrical airfoil configuration effective to increase the drag forces produced by the wind at the end regions when the turbine blade is used in a vertical-axis wind turbine provide a self-starting capability, and a speed-limiting capability, to the wind turbine. In one described embodiment, the non-symmetry in the sharp trailing edge of the blade is produced by a deep recess extending inwardly past the chord line of the blade to enhance the self-starting and speed-limiting capabilities; whereas in another described embodiment, the non-symmetry is produced by a shallow recess and outwardly-flared ends enhancing the efficiency of the wind turbine during normal wind conditions.

Abstract: The invention relates to an aerodynamic profile for the root of a wind turbine blade having a double leading edge, including a leading edge (13), a trailing edge (15) and suction and pressure sides (17, 19) between the leading edge (13) and the trailing edge (15). The profile (5, 5?, 5?) has a relative thickness in the 30%-50% range in at least one section (37) of the root region (31). In addition, the convex portion (21) of the pressure side (19) is configured such that the curvature thereof decreases from a value C0 at the leading edge (13) to a value C1 at a first point P1 and subsequently increases to a value C2 at a second point P2, after which it decreases to a value 0 at the end of the convex portion (21).

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: 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: Apparatus for treating solids, in particular mixing, pelletizing or drying, includes a vessel receiving a solid product, and a driveshaft which is arranged in the vessel. Disposed in fixed rotative engagement with the driveshaft is at least one mixing member which rotates in a rotation direction and has two mixing arms. Each mixing arm includes a main vane of generally triangular cross section to define an apex which is directed in the rotation direction of the mixing member.

Abstract: A first bent portion bent toward an intrados and a second bent portion located in the rear of the first bent portion and bent toward an extrados are provided on a camber line on a trailing edge in the rear of 90% of a chord length of a turbine blade having an extremely low aspect ratio for an axial-flow turbine. The inclination of the camber line immediately in the rear of the second bent portion on the side of a blade root is substantially equal to the inclination of the camber line immediately in front of the first bent portion, and the curvature of the second bent portion is decreased from the side of the blade root toward a blade tip. As a result, a higher-pressure portion on the intrados which is a pressure surface of the turbine blade is displaced toward the trailing edge, and thus a secondary flow from the side of the blade tip toward the blade root can be suppressed, whereby a pressure loss particularly in the vicinity of the blade root can be suppressed to the minimum.

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 (10) for a cooling fan includes a hub (20) having a circular wall (22) and an annular sidewall (24) extending downwardly from a rim 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 first portions is identical to an adjacent one of the first portions, and each of the second portions is different from an adjacent one of the second portions regarding a height thereof, thereby reducing a noise level of the impeller when the it operates.

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 fan blade includes an airfoil having opposite pressure and suction sides extending in span between a root and tip, and extending in chord between opposite leading and trailing edges. From root toward tip, the airfoil includes increasing stagger and decreasing camber, and increasing chord length to barrel the airfoil along both the leading and trailing edges. The airfoil further includes forward aerodynamic sweep at the tip, and non-forward aerodynamic sweep between the maximum barrel and the root.

Abstract: The present invention relates to a rotorcraft blade (P) provided in succession with a radial segment (1) and then a swept segment (2), said swept segment (2) being provided with at least one forwardly-swept segment (2?) and/or rearwardly-swept segment (2?). In addition, the blade has a single spar coming from the blade root. The invention is remarkable in that the single spar comprises a radial spar (10) in the radial segment (1), after which the single spar splits where the radial segment (1) becomes the swept segment (2) to form thereafter in the swept segment (2) a primary spar (11) and a secondary spar (12).

Abstract: A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.

Abstract: A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.

Abstract: A turbofan includes a row of fan blades extending from a supporting disk inside an annular casing. Each blade includes an airfoil having opposite pressure and suction sides extending radially in span between a root and tip and axially in chord between leading and trailing edges. Adjacent airfoils define corresponding flow passages therebetween for pressurizing air. Each airfoil includes stagger increasing between the root and tip, and the flow passage has a mouth between the airfoil leading edge and the suction side of an adjacent airfoil and converges to a throat aft from the mouth. The row includes no more than twenty fan blades having low tip solidity for increasing the width of the passage throat.

Abstract: An improved ceiling fan blade for use on a ceiling fan having a reversible motor and a plurality of said fan blades is provided in which each ceiling fan blade is in the shape of a trapezoid and the bottom part of the fan blade is wider than the tip of said fan blade. Each of the fan blades has two side edges that are connected to a central region of the fan blade, one of the side edges folds upwardly from the central region and the other side edge folds downwardly from the central region wherein each of the edges folds in opposite directions from the central region.

Abstract: A wind turbine includes a rotor having a hub and at least one blade having a torsionally rigid root, an inboard section, and an outboard section. The inboard section has a forward sweep relative to an elastic axis of the blade and the outboard section has an aft sweep.

Abstract: The invention relates to a rotor having at least three blades disposed between a front cover plate and a rear cover plate, the art of the suction edge of at least one blade, in the top view of the inlet side of the pumping medium, following a sinusoidal path with a single turning point W. The present invention is also directed to the use of the rotor in a centrifugal pump to pump coolant in a motor vehicle.

Abstract: A rotor blade for a gas turbine engine includes a blade root (3) and an aerofoil projecting therefrom, the aerofoil having a leading edge and a trailing edge (5), a generally concave pressure surface (2) and a generally convex suction surface (1). The aerofoil shape of the blade varies in section along the length thereof such that: the chord-wise convex curvature of the rear suction surface decreases towards the tip (4) of the blade; the convex curvature of the early to mid suction surface increases towards the tip; the stagger of the aerofoil section increases towards the tip; and the trailing edge (5) is a straight line.

Abstract: A method for reducing vortex promotion of a rotor blade used in high core PR fans comprises shifting a curvature distribution of a blade section immediately adjacent to the hub such that a major turning of the suction side of the section is located near a trailing edge of the blade.

Abstract: An exit guide vane array for a turbine engine includes a set of guide vanes 28 having a solidity and defining fluid flow passages 74 with a chordwisely converging forward portion 80. The high solidity and convergent passage portion 80 resist fluid separation. The vanes may also cooperate with each other to restrict an observer's line of sight to planes upstream of the vane array.

Abstract: The invention describes a supercavitating propeller with adjustable cup, and a method to adjust the cup. The trailing edge of the propeller blade is characterised by a protuberance with a limited section compared to the blade's section at the conventional trailing edge. The protuberance height can be adjusted, hereby reducing the propeller blade's cup.

Abstract: Disclosed is an axial-flow fan having a central hub coupled to a rotational shaft of a motor, a plurality of blades extending radially outwardly from the outer circumference of the hub for blowing air in an axial direction, the plurality of blades being integrated with the hub into a single body, and a circular fan band fixedly coupled to the peripheral ends of the plurality of blades for surrounding the plurality of blades, each of the plurality of blades having a leading edge line (L.E.L.) and a trailing edge line (T.E.L.) that are formed in a corrugated shape along almost the same direction to each other and have at least two or more pairs of inflection points formed along the lines, wherein the inflection points of the trailing edge line (T.E.L.) formed on each of the plurality of blades are placed in such a manner as to be closer to a blade tip than those of the leading edge line (L.E.L.) formed on each of the plurality of blades.

Abstract: A wind turbine operable as either a vertical axis wind turbine or a horizontal axis wind turbine is disclosed.

Abstract: A variable pitch fan, particularly for propulsion, of the type comprising a rotor and at least two stages of stator blade rows positioned upstream and downstream of the rotor, wherein the rotor blades (8) are of the variable pitch type and have a sinusoidal shape, are of the twisted type (1) or of the constant deflection type (2) and the stator blades (25), positioned downstream of the rotor, are of the twisted type. This rotor blade design allows a reduction of both the torque necessary to activate the variable pitch systems (lither actuator system) and the turning moments due to the centrifugal force. The proposed fan can be set in rotation by a conic couple of gears, contained in a gear oil sump positioned downstream the rotor, by means of one power shaft contained inside the stator blade. The variable pitch fan further provides a stator row upstream the rotor which are twisted in a manner that allows increased efficiency.

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 Straight blade type turbine has at least one two-dimensional blade positioned in parallel with and around a central axis of the turbine. The two-dimensional blade has a cross section with a blade chord turned around a center of the two-dimensional blade by an angle of 3° to ?2° relative to a line perpendicular to another imaginary line connecting the central axis with the center of the two-dimensional blade. A distance between a fore end and the center of the cross section is 15 to 40 percent of a chord length of the blade. NC/R, which is calculated by a radius R extending from the axis to the center of two-dimensional blade, the chord length C, and the number N of the two-dimensional blades, is between 0.5 and 2.2. A maximum thickness of the two-dimensional blade is between 20 and 25 percent of the chord length.

Abstract: A turbomolecular vacuum pump (1) has an inlet (3) and an outlet (4) and rotor and stator vanes (5 and 6), situated between the inlet and outlet. The rotor vanes (6) have front sides (11) and rear sides (12) in relation to the direction of rotation. At least a part of the rotor vanes (6) have a rear side (12) which is convex on the suction-side and concave on the delivery side. Alternately, at least part of the rotor vanes (6) have a front side (11), which is concave on the suction side and convex on the delivery side.

Abstract: Disclosed is an axial flow fan capable of achieving reduction of noise while having a high blowing efficiency compared to the power consumption of a motor adapted to drive the axial flow fan. The axial flow fan includes a hub, and a plurality of blades extending radially around the hub. Each blade has a sweep angle varying gradually from a backward angle at a root of the blade connected to the hub to a forward angle at a tip of the blade, while having a flow dispersion region having a plurality of regions where the sweep angle is alternately changed, at a region defined between a backward sweep angle region at the root of the blade and a forward sweep angle region at the tip of the blade. Each blade has a longitudinal cross section curved to have a wave structure between the root of the blade and the tip of the blade. The axial flow fan may further include a fan band connecting tips of the blades.

Abstract: A compressor airfoil includes opposite pressure and suction sides joined together at leading and trailing edges and extending in span between a root and tip. The airfoil includes stagger increasing above the root and decreasing above a midspan pitch section thereof.

Abstract: The present invention provides component parts for a mixing assembly adapted to be used with clean in place techniques. The component parts may include an impeller assembly, an adjustable hub assembly and a steady bearing assembly. In one embodiment, the blades of the impeller assembly may be adapted to direct a portion of the water initially aimed at the top surface of the blade towards the bottom surface of the blade.

Abstract: In a high turning airfoil capable of being suitably applied to each of blades constituting a blade row of an axial flow-type compressor, both of an intrados generating a positive pressure and an extrados generating a negative pressure exist on one side of a chord line, and the curvature of the extrados made non-dimensional by a chord length has a maximum value between a position corresponding to 10% of the chord length and a position corresponding to 35% of the chord length, and a minimum value in the rear of the position of the maximum value and between a position corresponding to 30% of the chord length and a position corresponding to 50% of the chord length. Preferably, a difference between the maximum value and the minimum value of the curvature is equal to or larger than 0.5, and a turning angle is equal to or larger than 40°.

Abstract: A novel concept for a propeller blade configuration incorporates the model of the natural wave behavior. The leading edge of the propeller blade has a convex segment followed by a concave segment, as seen in a plan view. The leading and trailing edges are rounded so as to promote proper fluid sheet formation along the flat surfaces and to reduce undesirable vortice formation. Best results are obtained by modeling the surfaces along a sine or tangent function.

Abstract: A turbine stator vane for use in an axial flow gas turbine. The vane has an aerofoil, the pressure face of which is convex between platform and tip regions in a plane which extends both radially of the turbine and transversely of the general working fluid flow direction between the vanes. The trailing edge of the aerofoil is straight from platform to tip, and the spanwise convex and concave curvatures of the aerofoil pressure and suction surfaces respectively are achieved by rotational displacement of the aerofoil sections about the straight trailing edge. However, the axial width of the aerofoil is substantially constant over substantially all of the aerofoil radial height and the chord line at mid-height aerofoil sections is shorter than the chord lines in aerofoil sections at platform or tip regions. Reducing chord length at the mid-height region in this way lowers aerodynamic profile losses without unduly affecting vane performance.

Abstract: A novel concept for a propeller blade configuration incorporates the model of the natural wave behavior. The leading edge of the propeller blade has a convex segment followed by a concave segment, as seen in a plan view. The leading and trailing edges are rounded so as to promote proper fluid sheet formation along the flat surfaces and to reduce undesirable vortice formation. Best results are obtained by modeling the surfaces along a sine or tangent function.

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 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: A hollow blade for a ceiling fan is made from a selected material and has a hollow interior structure to result in a reduced weight for decreasing motor loading and saving electric power consumption, and saving material consumption for reducing costs.

Abstract: A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.