Abstract: A pitch controlled wind turbine comprising a tower, a nacelle mounted on the tower, a hub mounted rotatably on the nacelle, and at least three wind turbine blades is disclosed. Each wind turbine blade extends between a root end connected to the hub via a pitch mechanism, and a tip end. The wind turbine further comprises at least three blade connecting members, each blade connecting member extending between a connection point on one wind turbine blade and a connection point on a neighboring wind turbine blade, the connection points being arranged at a distance from the root end and at a distance from the tip end of the wind turbine blade. The wind turbine further comprises at least three pre-tension members, each pre-tension member being connected to one of the blade connecting members and to a hub part, the pre-tension members thereby providing pre-tension in the blade connecting members.

Abstract: Improvements relating to wind turbine blade manufacture 5 A method of making a wind turbine blade is described. The method involves providing a blade shell having an inner surface defining a mounting region and positioning a web in the mounting region. One or more web restraining devices are used to secure the position of the web in the mounting region. Each restraining device has a first portion attached to the web and a second portion attached to the inner surface of the blade shell. The 10 restraining devices are configured to prevent movement of the web in a first plane substantially parallel to the mounting region and to permit movement of the web in a second plane substantially perpendicular to the mounting region. The method further comprises moving the web in the second plane away from the mounting region and performing one or more preparatory operations on the mounting region with the web 15 moved away from the mounting region.

Abstract: A display method of a fan display apparatus includes detecting a present display section of a blade portion of the fan display apparatus; acquiring the image data to be displayed; determining whether the present display section and the previous display section are the same; changing a present display mode of the display elements, if the present display section and the previous display section are not the same; displaying the image data according to the changed display mode. A fan display apparatus and a fan display video wall system are also provided. The present disclosure makes the three-dimensional sense of the visual stronger; the visual effect is shocking and the experience is great; create a completely new 3D advertising solution; and at the same time, the installation method is flexible and can be installed in shopping malls, convenience stores, newspaper booths and other places.

Abstract: A blade member includes a leading edge, a trailing edge, and a blade body extending therebetween. The blade member also includes a dovetail, a transition region, and a transition relief. The dovetail includes a dovetail chord line extending between an axially forward face of the dovetail and an axially aft face of the dovetail. The dovetail chord line has a dovetail chord length. The transition region is formed between the blade body and the dovetail. The blade body and the transition region form a blade body transition chord line at the interface of the blade body and the transition region which has a blade body transition chord length. The transition relief includes a geometric relief in at least one of a forward and an aft end of the transition region and the dovetail. The dovetail chord length is less than the blade body transition chord length.

Abstract: A propeller fan includes a boss and a blade. The boss rotates about an axis. The blade is provided at an outer periphery of the boss. The blade has a first region in a radial direction. In the first region, a blade chord center line shifts downstream toward an outer peripheral side. In a cylindrical cross section about an axis, a cross-sectional shape of the blade at least in the first region is an airfoil shape. When a cross section taken along the blade chord center line and projected onto a plane including the axis is viewed, the blade chord center line is a curve having a convex on a downstream side in an entire region in the radial direction.

Abstract: An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 0° to 10° in a range of 10-20% span position. The trailing edge sweep angle is in a range of the trailing edge sweep angle is positive from 0% span to at least 95% span.

Abstract: The disclosure relates to a blade edge of at least one blade of an air-conveying wheel with an axial-side blade edge contour which extends from a blade leading edge to a blade trailing edge along a curve, wherein the blade edge contour has at least one front section which adjoins the blade leading edge in the radial direction, a rear section which adjoins the blade trailing edge in the radial direction, and a central section which lies between the front section and the rear section. The blade edge contour has an S-shaped curve progression in the central section in a lateral cross-sectional view, thus increasing an axial height of the blade in the direction of the blade trailing edge.

Abstract: The present disclosure provides a subsonic rotor and/or stator blade profile of an axial turbomachine compressor, such as a turbojet. The blade comprises a leading edge with an S-shaped lateral profile in its mid-plane. Specifically, the profile includes, from its inner end to the outer end, a first convex portion including the foremost point of the blade, and a second concave portion including the rearmost area of the blade. This profile enables the fluid flow between 20% and 80% of the blade's length to be redistributed. This so-called “sweep” profile increases the performance of the stage with such blades because it reduces blade tip vortex losses as well as secondary losses.

Abstract: A swept wind turbine blade (20) includes a blade body (24) extending along a length between a root (26) and a tip (28) of the blade (20). A pitch axis (36) extends through the root (26) of the blade (20). A reference line (48) defines a deviation from the pitch axis (36) and corresponds to a swept shape of the blade (20) along its length. The reference line (48) has a zero sweep at the root (26), a zero slope at the root (26), and a positive curvature (66) along a segment within 25% of the length from the root (26) to the tip (28) of the blade (20).

Abstract: A blade of a propeller fan includes a blade root portion, a front edge portion, a blade tip end portion, a rear edge portion, a blade rear edge portion, and an outer edge portion. A blade surface of the blade has an inner region including the blade root portion, an outer region including the blade rear end portion, and a coupling portion extending from a front end portion located close to the blade tip end portion to a rear end portion located close to the rear edge portion and coupling the inner region and the outer region to each other such that a side of a positive pressure surface of the blade surface is projecting and a side of a negative pressure surface of the blade surface is recessed.

Abstract: A propeller fan includes a boss hub portion and a blade including a front edge portion, a rear edge portion, and an outer edge portion. The outer edge portion has a front outer edge portion, a rear outer edge portion, and a connection portion connecting the front outer edge portion and the rear outer edge portion to each other. In a plan view of the blade along a central axis, a maximum radius R1max of the outer edge portion in a portion corresponding to the front outer edge portion and a maximum radius R2max of the outer edge portion in a portion corresponding to the rear outer edge portion satisfy a condition of R1max>R2max. With such a construction, a propeller fan which generates wind less in pressure fluctuation and is capable of sending comfortable wind and achieving lowering in noise is provided.

Abstract: A one-block bladed disk includes blades, a leading edges of which has sweep and dihedral angles, both strongly variable and increasingly large upon approaching a connection to a hub to improve mechanical strength of the whole and obtain good distribution of gas flow over the height of the blade.

Abstract: A leading edge of a blade has a first curved portion provided with a leading-edge rearmost point, and a trailing edge of the blade has a second curved portion located on the inner circumferential side of the trailing edge and a third curved portion located on the outer circumferential side of the blade on the trailing edge. The third curved portion has a trailing-edge foremost point, and the second curved portion has a trailing-edge rearmost point. The trailing edge and a first concentric circle, which is one of concentric circles having as their center an axis of rotation and passes through the leading-edge rearmost point, intersect each other at a first intersection. The first intersection is located between the trailing-edge rearmost point and the trailing-edge foremost point.

Abstract: A blade for a blade row of a turbomachine having wired sections, in particular a blade of a compressor rotor blade, as well as a method for wiring sections of such a blade, is disclosed. Sections of a blade are wired in such a way that a first central component of a second section is selected according to at least one central component of a first section.

Abstract: An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope crosses an initial axial stacking offset that corresponds to the 0% span position at a zero-crossing position. A first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve. A second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve. A ratio of the second to first axial stacking offset X2/X1 is between 1.5 and 2.0 or less than 1.4.

Abstract: An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starting at the 0% span position is either zero or positive. The first critical point is in the range of 5-15% span.

Abstract: A turbomachine rotor blade including a blade root and a blade tip spaced apart by a blade height, including at least one intermediate segment between the blade root and the blade tip that presents forward sweep over at least 50% of the blade height, and a distal segment with backward sweep between the intermediate segment and the blade tip, the distal segment also presenting a positive tangential angle of inclination.

Abstract: An HVLS fan system uses STOL technology for airfoils and angle of attack thus optimizing air movement efficiency and reducing drag. The HVLS fan system includes wingtip fence end caps to the airfoils for improving efficiency by reducing drag. The HVLS fan system also includes an interconnection of the airfoils to a securing plate thus providing a failsafe and reduced potential for damage or injury resulting from failure of the connection between the airfoil array and a drive unit such as an electric motor and associated gearing.

Abstract: An axial fan is provided. The axial fan includes a hub, an impeller having a plurality of blades mounted on an outer peripheral surface of the hub, and a housing surrounding the impeller. Each of the blades has a front edge angle (?) within a range of ?8° to ?20°, a mounting angle (?) within a range of 36° to 50°, and a twisted angle (?) within a range of 10°±2°.

Abstract: A blade (1) for a tail anti-torque device of a helicopter, said device comprising a ducted rotor (13). The blade (1) has an assembly of sections, a leading edge (2) and a trailing edge (3); a stacking line (4) of the profiles extending at a distance lying in the range 25% to 50% of the chord (C). The stacking line (4) presents a shape that is curved having successively from the root (5) to the end (6) of the blade a back sweep, a forward sweep, and a last back sweep; and a chord (C) that becomes larger going towards the end (6) of the blade (1) over at least the end profile (1a).

Abstract: The impeller wheel is rotatably supported about a central axis and has a hub on which vanes are arranged. The vane has across its radial length at least similar profiled sections, viewed in cylindrical section through the vane. The radial outermost profiled section which is positioned on a cylindrical enveloping surface of the impeller wheel has a greater displacement relative to the neighboring profiled section than this neighboring profiled section to its neighboring profiled section. The impeller wheel can also be provided on the radial outer edge with at least one projecting flow element whose axial height has a maximum in the area of the leading edge and of the trailing edge of the vane. The impeller wheels, while having a simple constructive configuration, provide a great noise reduction in operation of the ventilator.

Abstract: Certain embodiments of the present disclosure include a system having a turbomachine including a plurality of turbomachine blades coupled to a rotor, wherein each turbomachine blade has a blade base portion and a flared blade tip portion flared relative to the blade base portion. Additionally, a trailing edge of each turbomachine blade extends along a common plane.

Abstract: A turbine engine blade comprising an airfoil extending axially between a leading edge and a trailing edge and extending radially between a root and a tip. The leading edge of the airfoil presents a sweep angle that is positive and that increases continuously from the root to a first radial height of the airfoil situated in the range 20% to 40% of the total radial height of the airfoil as measured from the root to the tip, and decreases continuously from this first radial height of the airfoil to the tip.

Abstract: Large diameter axial Super Low Noise flow fans and commercial air cooled apparatuses incorporating such fans are provided. The large diameter axial flow fan is mounted on the air cooled apparatus for generating an axial air flow in the air cooled apparatus for accomplishing the cooling. The fan has a diameter of at least four feet. The fan has plurality of blades. Each blade includes a leading edge opposite a trailing edge. The entire of the leading edge of each of the blades is linear and forward swept, and each blade includes a metallic outer surface.

Abstract: In at least one implementation, a method of making a turbine blade may include providing a preform having a hollow cross-section, hydroforming the preform to form a turbine blade body comprising a shell that includes a continuous hollow portion along its interior, and providing a mounting portion attached to the body to mount the turbine blade to a hub. In one or more implementations of the method, the mounting portion may be provided during the step of hydroforming the preform and the mounting portion may be formed from the same preform as the turbine blade body.

Abstract: A blade for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a platform and an airfoil that extends from the platform. The airfoil extends in span between a root and a tip region and in chord between a leading edge and a trailing edge. A sweep angle is defined at the leading edge and a dihedral angle is defined relative to the chord of the airfoil. The sweep angle and the dihedral angle are localized at the tip region and extend over a distance of the airfoil equivalent to about 10% to about 40% of the span.

Abstract: The present disclosure provides an improved first stage airfoil for a compressor blade having a unique chord length (CD) stagger angle (?) and camber angle (??). The stagger angle (?) and camber angle (??) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.

Abstract: A trillium wind turbine has an electricity-generating nacelle and swept-back, complexly-curved blades. Each blade has a main blade, a trailing edge blade, and a diversion blade. Wind is directed down the length of the blade and exits the tip. The main blade resembles a portion of a cylinder in form, the cylinder being twisted to change the angle of attack, thereby adding more lift throughout the length of the blade. The trailing edge and diversion blades are pitched relative to the wind and produce lift. Additionally, wind hitting the diversion blade is diverted behind the blade. Because the surface area and volume of the blade are larger near the nacelle and smaller at the tip, the air that travels along the blade increases in velocity as it travels producing more thrust/lift. The turbine also automatically faces into the wind without the need for sensors or positioning motors.

Abstract: The present disclosure provides an improved second stage airfoil for a compressor blade having a unique chord length (CD) stagger angle (?) and camber angle (??). The stagger angle (?) and camber angle (??) provide improved aerodynamics while the chord length (CD) provides for reduced airfoil weight.

Abstract: An air boost device such as a turbocharger, wherein the compressor wheel thereof is re-designed to permit die inserts (20), which occupy the air passage and define the blades (4, 5) during a process of forming a wax pattern (21) of a compressor wheel, to be pulled without being impeded by the blades. This modified blade design enables the automated production of wax patterns (21) using simplified tooling. The compressor wheel improves low cycle fatigue, withstands high temperatures and temperature changes, and permits operation at high boost pressure ratio while, on the other hand, having low weight, low inertial drag, and high responsiveness.

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: A compressor impeller and a method of manufacturing the compressor impeller. The magnesium alloy compressor impeller as a die-cast part comprises a hub shaft part, a hub disk part having a hub surface extending from the hub shaft part in the radial direction, and a plurality of vane parts disposed on the hub surface. The impeller can be manufactured by a die-cast method in which a magnesium alloy heated to a liquidus temperature or higher is supplied into molds with cavities corresponding to the shape of the impeller for a filling time of 1 sec. or shorter, a pressure of 20 MPa or higher is applied to the magnesium alloy in the cavities, and the pressurized state is maintained for a time of 1 sec. or longer.

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 stage of a steam turbine, having a rotor extending along a longitudinal axis, has a fixed stage and a movable stage arranged successively along a flow channel for feeding steam in a direction substantially parallel to the longitudinal axis; the fixed stage has an inner ring coaxial with the longitudinal axis, and a number of stator blades arranged radially about the inner ring; each stator blade is fixed to an annular top portion of the inner ring, which has a top surface facing the flow channel and crosswise to the longitudinal axis; and the movable stage has a number of rotor blades arranged radially about the rotor and fixed to the rotor.

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 system including an airfoil portion of an unshrouded turbine bucket, which includes a pressure-side surface and suction-side surface each extending from a root surface to a tip surface and joined at a leading edge and a trailing edge, the pressure-side surface having a generally concave shape and the suction-side surface having a generally convex shape; the airfoil portion having an increasing stagger angle in a span-wise direction from the root surface to the tip surface and an increasingly loaded suction-side surface as the suction-side surface approaches the tip surface and the tip surface approaches the leading edge, the airfoil portion having a resultant lean in a direction of the suction-side surface as the leading edge approaches the tip surface, and the pressure-side surface and the suction-side surface each having a locally reduced or reversed curvature in a direction of the pressure-side surface at their intersection with the tip surface.

Abstract: A method of designing an airfoil for a gas turbine engine according to one embodiment of this disclosure can include localizing a sweep angle at a leading edge of a tip region of the airfoil, and localizing a dihedral angle at the tip region of the airfoil. The dihedral angle can be applied by translating the airfoil in direction normal to a chord of the airfoil.

Abstract: A fluid turbine comprises a rotor rotatable in use about an axis transverse to the direction of fluid flow. The rotor has a first part carrying a plurality of arcuate blades and a second part journalled in a base structure by means of two or more bearings. All the bearings are arranged on the same side of the blades so that the first part of the rotor is cantilever supported in the base structure.

Abstract: An airfoil of varying span-wise thickness comprising a suction side and a pressure side coupled together at a leading edge and a trailing edge, with the trailing edge comprising a plurality of spaced-apart wave-shaped projections. Exemplary embodiments provide airfoil geometry and/or trailing edge features to influence downstream wake flow. Methods of fabricating an airfoil for improved wake flow are also provided.

Abstract: A cooling fan includes an impeller which comprises a plurality of radially extending blades, each of which includes a blade hub, a blade tip and a blade midspan approximately midway between the hub and the tip. In addition, each blade includes a camber of between about 60° and 90° at the blade hub, between about 15° and 40° at the blade midspan and between about 15° and 40° at the blade tip.

Abstract: An impeller, a system for mixing a fluid, and a method of mixing a fluid in a tank are disclosed. For a sufficiently small impeller diameter and maximum blade tip velocity, the disclosed impeller, system, and method are capable of accelerating a near-zero intake velocity fluid, to generate a mixing zone that is collimated enough to have sufficient velocity vectors to suspend particles at a large distance away from the impeller, while minimizing the required power draw. An impeller may include a hub defining a longitudinal axis and plural blades spaced circumferentially about the hub. Each blade may include a root portion and a tip portion. Each blade may define a leading edge having an approximately circular raked helical geometry. A system for mixing a fluid may include a tank for containing the fluid, a drive shaft for extending into the tank, and the impeller.

Abstract: In one embodiment, a rotor blade includes a tip, a root, and a body extending between the tip and the root. The body has surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge. The body further defines an inboard portion, an outboard portion, and a bend therebetween. The bend is defined such that the outboard portion extends outwardly with respect to the inboard portion. The bend is stiffened to reduce opening of the bend during deflection of the rotor blade.

Abstract: A centrifugal fan includes a housing and an impeller rotatably received in the housing. The housing defines an air inlet in a top plate thereof and an air outlet in a sidewall thereof. The air inlet is perpendicular to the air outlet. The impeller includes a hub and a plurality of blades extending outwardly from a sidewall of the hub. Each of the blades includes an inner blade section connected with the sidewall of the hub and an outer blade section extending outwardly from the inner blade section. An upper portion of the inner blade section is curved upwardly and forwardly from a curved lower portion of the inner blade section towards an adjacent front blade. The curved lower portion has a curvature smaller than that of the upper portion.

Abstract: A blade of a hybrid type fan includes: a blade body 21 made of a synthetic resin; and a metallic insert 22 that is insert molded simultaneously with the blade body 21 and mounted to a mounting arm of a spider. At a corner on an outer side of a radial direction and a forward side of a rotary direction of the insert 22, a bulging portion 26 is provided to bulge toward the outer side of the radial direction and the forward side of the rotary direction. A bulging region 27 of the bulging portion 26 that the most prominently bulges toward the outer side of the radial direction is located to be forward in the rotary direction relative to a mounting center C of the insert 22 and the mounting arm along the radial direction.

Abstract: The present invention concerns a rotor blade for a wind power plant having an aerodynamic profile. The rotor blade has a main rotor body with an aerodynamic profile and a tip. The tip extends away from a plane of the rotor blade and in a direction of at least one of a low pressure side or a high pressure side of the main rotor body. The tip includes a tip upper edge, a tip leading edge, and a tip trailing edge. At least a portion of the tip leading edge is curved such that a width of the tip defined between the tip leading edge and the tip trailing edge is reduced towards the upper edge.

Abstract: A fan includes a hub and a plurality of blades formed on the hub with a rake angle. In an axial direction of the hub, no part of a trailing edge of any of the blades is disposed past an air outlet end of the hub at more than a distance approximately equal to 25% of a diameter of the hub.

Abstract: Provided is an axial fan apparatus including a housing and an axial-flow impeller. The axial-flow impeller is capable of rotating inside the housing and includes a plurality of axial-flow wings each having a negative pressure generation surface for generating a negative pressure, and an auxiliary vane standing on the negative pressure generation surface at an end portion of each of the plurality of axial-flow wings.

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 propeller has a hub 1 with a pair of blades 3 extending therefrom. Each blade 3 has a root, a tip, a first blade portion 10a extending between the root and tip and a second blade portion 10b extending between the root and tip adjacent and substantially parallel to said first blade portion 10a. The first and second blade portions 10a, 10b each have an arcuate concave face 11a, 11b, the radius of curvature of the concave face 11a of said first blade section 10a being greater than the radius of curvature of the concave face 11b of the second blade section 10b. The concave faces of said first and second portions 10a, 10b facing in substantially opposite directions such that, in use, said concave face 11a of said first blade portion 10a faces rearwards and said concave face 11b of the second blade portion 10b faces forwards.

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.