Abstract: An exemplary aerofoil blade for an axial flow turbomachine has a radially inner platform region, a radially outer tip region, an axially forward leading edge, and an axially rearward trailing edge. The aerofoil blade has a pressure surface which is convex in a radial direction, and a suction surface which is concave in the radial direction. The axial width (W) of the aerofoil blade can vary parabolically between maximum axial widths (Wmax) at the platform and tip regions, respectively and a minimum axial width (Wmin) at a position between the platform region and the tip region.

Abstract: An air conditioner includes an outdoor unit that includes a compressor configured to compress a refrigerant, a condenser configured to condense the compressed refrigerant, and a blowing fan configured to blow outdoor air into a room, an indoor unit that discharges air heat-exchanged with the refrigerant flowing-in from the outdoor unit to the room, and a connection piping that connects the outdoor unit and the indoor unit. Here, a plurality of protrusions may be formed at least one side of the blowing fan, and a convex portion and a concave portion may be formed on a surface of the blowing fan so that the surface of the blowing fan is indented.

Abstract: A rotor according to a preferred embodiment of the invention has at least one blade arranged at a hub of the rotor, wherein the blade has a curvature between its leading edge and its trailing edge which curvature has a first convex surface and an opposite second concave surface, wherein the first surface is to be arranged against the direction of the wind striking the blades. The convex profile of the first surface and the concave profile of the opposite second surface are spaced by the thickness of the blade which is preferably constant. The hub is arranged at the rotational axis.

Abstract: A centrifugal multiblade fan includes a rotatable shaft, blades, a side shroud, and a main shroud. A front edge has a shape inclined radially outward in a direction from the main shroud toward the side shroud. When viewed from an axial direction, a corner part on a positive pressure surface-side is located on a tangential line of a positive pressure surface reference curve at a positive pressure surface side reference corner part, and when viewed from the axial direction, a curvature radius of a negative pressure surface becomes larger in a direction from the side shroud toward the main shroud.

Abstract: The present invention relates to an airfoil for a fluid flow machine (100), having a suction side (5), a pressure side (7) and an airfoil trailing edge (200). The airfoil (100), at least in portions thereof, has a profile (9) in the region of the airfoil trailing edge (200), which profile extends over the suction side (5) and the pressure side (7) of the airfoil trailing edge (200). The present invention also relates to a blade and an integrally bladed rotor.

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: Provided are a wind turbine blade that can reduce the thickness of a turbulent-flow boundary layer generated on the blade surface of a blade tip portion to prevent noise generated at a trailing edge portion effectively, as well as a wind power generator using the same. Provided is a wind turbine blade, which is a wind turbine blade having an airfoil shape in cross section, wherein an angle-of-attack decreasing portion that decreases an angle of attack during rotation at at least a predetermined rotational speed is provided over a predetermined range from a blade tip to a blade root side.

Abstract: A wind blade is provided that includes a primary blade body defining a leading edge and a trailing edge and further defining a pressure side and a suction side joining along the trailing edge. The wind blade also includes a secondary blade having an aerodynamic contour defining a first surface and a second surface and coupled with the primary blade body for the purpose of shielding noise. The secondary blade body is disposed proximate to at least a portion of the trailing edge on at least one of the pressure side and the suction side of the primary blade body and may also improve overall performance of the wind blade.

Abstract: Spacers interposed between blades attached to the disk of a rotor having slots and bottoms of the slots are disclosed. Each spacer is made of an elastically deformable material and at least one longitudinal segment of the spacer presents a transverse profile of arcuate shape to define two lateral contact zones.

Abstract: A wind turbine blade is described having noise reduction features. The blade has a plurality of projecting serrations provided at the blade trailing edge to reduce the scattering noise produced during operation of the blade, wherein the serrations have a plurality of through-going apertures defined in the serration body. The apertures act to provide a pressure equalisation effect at the serrations between the suction and pressure sides. This pressure equalisation provides for improved noise reduction performance, as well as a reduction in mechanical stresses and strains which may be experienced by the serrations, increasing serration lifetime.

Abstract: A rotor blade assembly for a wind turbine and a method for increasing a loading capability of a rotor blade within a maximum load limit for a wind turbine are disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade assembly further includes an extension connected to a surface of the rotor blade, the extension having at least one design characteristic configured for increasing a loading capability of the rotor blade within a maximum load limit for the wind turbine. The design characteristic is one of extension length, extension width, extension curvature, span-wise extension location, chord-wise extension location, or extension angle with respect to a chord line of the rotor blade.

Abstract: A fan assembly according to an exemplary embodiment of the present invention includes: a hub; and a plurality of blades including a leading edge corresponding to a side hit by air and a trailing edge corresponding to an opposite side of the leading ledge, the plurality of blades configured to be extended radially from an outer peripheral surface of the hub, wherein each of the plurality of blades includes a first part extended radially from the outer peripheral surface of the hub, a bent part stepped on the end of the first part, and a second part further extended radially on the end of the bent part.

Abstract: An angled fan blade extension includes an attachment portion and an angled portion. The attachment portion is configured to facilitate securing the angled fan blade extension to the distal end of a fan blade. The angled portion is configured to extend from the distal end of the attachment portion, creating an angled extension relative to the fan blade. Adding angular fan blade extensions to fan blades may improve the airflow control, and thereby increase the utility and efficiencies of a fan.

Abstract: One or more protuberances are provided on a turbine blade on its suction side in a vicinity of its trailing edge. The protuberances serve to reduce a separation zone in a vicinity of a blade surface that is responsible for disturbances that affect efficiency of the turbine.

Abstract: A fluid flow modification apparatus (10) has a surface (15), the surface having an edge (65) of length Y over or past which a fluid can flow in use. The edge (65) has a virtual boundary (30) of length X where Y is greater than X. At least a first portion of the apparatus (10) within the virtual boundary (30) comprises an opening (55) and at least a second portion of the apparatus (10) comprises a projection (60) which extends beyond the virtual boundary (30) to provide the edge (65). The edge (65) is multi-scale.

Abstract: A compressor having a compressor blade with a blade tip portion configured to reduce stresses in the blade tip of the compressor blade is provided. The compressor blade includes a first and second faces extending to the blade tip portion. The blade tip portion includes a blade tip, a first recess extending between the first face and the blade tip, and a second recess extending between the second face and the blade tip.

Abstract: A centrifugal fan has a circular main plate driven and rotated by a motor rotary shaft, a plurality of blades fixed to an outer circumferential portion of the main plate and spaced apart at predetermined intervals in a circumferential direction of the main plate, and a side plate attached to ends of the blades opposite to the main plate. An air inlet port is formed at the center of the side plate. The side plate inclines outward in centrifugal directions from the air inlet port and has an arcuate cross section with a predetermined radius of curvature. A dead water region reducing space is formed between the blades and the side plate. The dead water region reducing space forms a smooth flow between the two surfaces of each blade, bringing about desirable blade performance.

Abstract: A rotor blade has a radially extending aerofoil body having pressure and suction sides. The rotor blade further has squealer tip. The squealer tip includes a peripheral wall surrounding a cavity which is open at the radially outward end of the blade and at the trailing edge of the aerofoil body. The peripheral wall has at least one first region which extends radially from the aerofoil surface which has a first outer surface. The peripheral wall further has, along at least part of at least one of the pressure and suction sides, at least one second region inclined outwardly of the cavity with respect to the radial direction of the blade which has a second outer surface which extends obliquely outwardly of the blade. A radially outer portion of the second outer surface turns towards the radial direction to truncate the outward extension of the second outer surface.

Abstract: The present invention relates to enhancing performance of fans and propellers using outsized Gurney flaps. Specifically, the current invention proposes the application of ‘outsized Gurney flaps’ (OGFs) to the trailing-edges of fan blades. According to an exemplary embodiment of the current invention, the Gurney flaps are larger than 10% of the fan blade chord length. Attaching OGFs is not only non-obvious; it seems counterintuitive, because it is akin to placing a large bluff body onto a flow. Preliminary experimental data acquired at Reynolds numbers typically exist during fan operation on idealized blade profiles showed a 100% increase in the generated lift and 40% to 60% increase in aerodynamic efficiency. This translates to significant improvements in fan performance at a given rpm, and/or significant saving in power and noise reduction for the same aerodynamic performance.

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: A marine surface propeller, and blade therefore, which is surface piercing and partially submerged, and includes a blade geometry that improves distribution of pressure and control to wetted and ventilated regions. Preferably, the feature has a positive step (ramp, cup, interceptor, indent or other geometric addition or intervention) between one fifth and four fifths chord length so as to create a high pressure peak or zone in what is now a low pressure zone on either the blade face or back or both and to create speed controllable wetted and ventilated regions.

Abstract: A turbine blade for a turbine engine having a tip with one or more vortex generators for reducing tip leakage during operation of the turbine engine. The vortex generators may extend radially outward from the radially outer surface of the tip wall. The vortex generator may be positioned between a rib extending radially outward from the radially outer surface of the tip wall and an intersection between the outer surface of the tip wall and an outer surface on the pressure side. The vortex generators may include a base and three sides forming a triangular point with a first side having a larger surface are than second and third sides. One or more film cooling holes may be formed in the tip wall to provide cooling air to the tip. In one embodiment, film cooling holes may be positioned in one or more vortex generators.

Abstract: Rotor blade assemblies for wind turbines and methods for reducing rotor blade noise are disclosed. A rotor blade assembly includes a rotor blade having external surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade further defines a span and a chord. The rotor blade assembly further includes a tab. The tab includes an inner surface, an outer surface, a forward end and an aft end. The inner surface is mounted to one of the pressure side or the suction side. The outer surface has a cross-sectional profile configured to modify an operational value of the rotor blade at the trailing edge. The forward end is disposed within the chord.

Abstract: A turbine rotor blade with a spar and shell construction, and a tip cap that includes a row of lugs extending from a bottom side that form dovetail grooves that engage with similar shaped lugs and grooves on a tip end of the spar to secure the tip cap to the spar against radial displacement. The lug on the trailing edge end of the tip cap is aligned perpendicular to a chordwise line of the blade in the trailing edge region in order to minimize stress due to the lugs wanting to bend under high centrifugal loads. A two piece tip cap with lugs at different angles will reduce the bending stress even more.

Abstract: A method for reducing tip rub loads in a rotor blade is described having the steps of selecting a location of contact between the rotor blade and a static structure; selecting a location on the blade for incorporating a tip-cutter; selecting a cutter-profile for the tip-cutter; and incorporating the tip-cutter on the selected location on the blade such that tip-cutter is capable of removing a portion of the static structure during a tip rub such that tip rub loads are facilitated to be reduced.

Abstract: The disclosed embodiments relate to turbulence inducing mechanisms applied to portions of wind turbine blades and methods for increased power production using turbulence inducing mechanisms. Embodiments provide methods and mechanisms for increasing the range of optimal wind performance for wind turbines and provide for increasing the maximum energy producing capacity of wind turbines at a given wind speed. Some embodiments have a rotor blade that includes a capture side and a drag side. The blade also includes a film disposed over at least a portion of only the drag side of the blade. The film comprises a conformable sheet material with a plurality of perforations therethrough which are configured to induce turbulence on a fluid flowing thereover. The turbulence inducing film reduces the drag of the blade and consequently increases the blade's rotational speed at a given wind speed, which increases the turbine's power production and optimal performance range.

Abstract: An airfoil for use in a rotor assembly is disclosed, the airfoil having a tip-cutter located on a sidewall near a tip portion, wherein the tip-cutter is capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-grinder located on the tip portion, wherein the tip-grinder capable of removing a portion of an abradable material during a tip rub. In another embodiment, an airfoil has a tip-rake that facilitates reducing loading induced to said airfoil during tip rubs.

Abstract: A rotor of a vacuum pump has a circular member that is driven rotatably, a cylindrical member joined to an outer circumference of the circular member, and a thread groove pump flow path formed between the cylindrical member and a stator member surrounding an outer circumference of the cylindrical member. The cylindrical member is made of a material having at least a feature of lower thermal expansivity or lower creep rate than that of a material of the circular member. A gap of a second region provided between a non-joint portion of the cylindrical member and the stator member is set to be smaller than a gap of a first region provided between a joint portion of the cylindrical member and the stator member.

Abstract: A blade for use in rotary machines such as a wind turbine blade has a plurality of dimples distributed over an area of a low pressure or suction surface of the blade which preferably extends from immediately adjacent to a leading edge of the blade at least partially towards a rear or trailing edge of the blade.

Abstract: A turbine blade extends radially between a blade root and a blade tip having an open cavity referred to as a bathtub formed therein, which cavity is defined by a closed end wall and a side rim. The side rim of the cavity carries at least one rib extending between a leading edge and a trailing edge of the blade.

Abstract: A marine propeller with reverse thrust cup includes a propeller hub, propeller blades each having a leading blade face and a trailing blade face provided on the propeller hub and a reverse thrust cup provided in the trailing blade face of each of the propeller blades.

Abstract: A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side.

Abstract: An impeller comprising: a top shroud; a bottom shroud, a plurality of vanes extending from the top shroud to the bottom shroud, each said vane including a top edge at a radially inner portion of the vane in contact with the top shroud and a bottom edge at a radially outer portion of the vane in contact with the bottom shroud, such that a radially inner portion of the vane at the bottom edge of each vane is not in contact with or adjacent the bottom shroud and a radially outer portion of the vane at the top edge of each vane is not in contact with or adjacent the top shroud.

Abstract: A squealer tip preform having a coating including an abrasive is disclosed. The squealer tip may be separately formed from a generally elongated blade to which the squealer tip preform is configured to be attached. The squealer tip may be configured such that an outer surface of the squealer tip preform is generally aligned with an outer side surface of the turbine blade defining a cross-sectional profile of the turbine blade. Forming the squealer tip preform with an abrasive coating separate from the turbine blade greatly reduces costs and improves efficiency as compared with conventional systems.

Abstract: A shroudless blade for use in a compressor or fan of an axial flow gas turbine engine includes a treatment to the tips of the blades to improve the surge margin of the compressor. A series of cross bleed holes are formed at the tip of the blade, which may be a stator or rotor component, extending between the pressure and suction sides of the blades. Notches are provided at the tip of the blades to provide initiation sites for any fatigue cracks such that the cracks propagate from the base of these slots or notches and radially inwards into the body of the blades. The present invention provides an arrangement, which by provision of the cross bleed holes the propagation of the cracks is arrested. A preferred placement and orientation for the holes for best mechanical and aerodynamic performance is described.

Abstract: A turbine blade adapted for mounting to a turbine rotor includes a root portion, and an airfoil portion extending outward from the root portion and defining a blade tip at an outermost end thereof. The airfoil portion having a pressure side and a suction side opposite the pressure side, and including a stiffening rib disposed at the blade tip. The stiffening rib projects from the pressure side of the airfoil portion of the turbine blade.

Abstract: A wing-tip device for the tip of a wing, or a blade of a wind generator, or a blade of a marine generator that makes it possible to reduce or even cancel what are known as wing-tip vortices. In the case or a wind generator, the result provides a start-up with less wind, control and energy efficiency that are highly productive throughout its use while at the same time significantly reducing the noise caused by the vortex.

Abstract: A blade for a compressor having a pressure surface and a suction surface. The suction surface includes a discontinuity in the chord-wise curvature of an intermediate portion of the suction surface between the blade leading edge and blade trailing edge, and a slot arranged along at least a portion of the blade in a substantially span-wise direction. The slot being disposed at or near the change in curvature, such that when in use lower momentum fluid near the suction surface is aspirated into the slot.

Abstract: A rotor blade assembly for a wind turbine is disclosed. In one embodiment, the rotor blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade further defines a span and a chord. The rotor blade assembly further includes a noise reducer configured on an exterior surface of the rotor blade. The noise reducer includes a plurality of noise reduction features. Each of the plurality of noise reduction features defines a centerline. In a planform view, the centerline of each of the plurality of noise reduction features is approximately parallel to a local flow streamline for that noise reduction feature at the trailing edge of the rotor blade.

Abstract: The present invention relates to a reinforcing tip cap for an aerofoil blade. The tip cap comprises a body for attaching to the tip of an aerofoil blade and a plurality of abrading elements fixed in the body for abrading a surface against which the tip cap rubs in use.

Abstract: In one aspect, a winglet for a rotor blade is disclosed. The winglet may generally include a winglet body extending at least partially between a winglet origin and a blade tip. The winglet body may define a sweep and a pre-bend. The sweep defined between the winglet origin and the blade tip may range from about 0.5% to about 4.0% of a span of the rotor blade. The pre-bend defined between the winglet origin and the blade tip may range from about 1.5% to about 4.

Abstract: The present invention relates to an actuatable seal (14) for an aerofoil blade tip, for providing a seal between the blade tip (12) and an adjacent surface (10) over which the blade tip passes in use. The seal comprises a flexible member that is arranged in use to be mounted on the tip of a rotating aerofoil blade and to flex towards the surface under the action of centrifugal force when the blade rotates. The seal further comprises an actuator means provided on the flexible member and operably arranged in use to deflect at least a portion of the flexible member away from the surface.

Abstract: A turbine/compressor comprises at least one magneto-electric device and a drive train coupled to the magneto-electric device. At least one rotor blade is coupled to the drive train. The rotor blade has a shaped leading edge with a series of spaced tubercles formed therealong.

Abstract: A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade further includes a noise reducer configured on a surface of the rotor blade, the noise reducer comprising a plurality of serrations, each of the plurality of serrations defining a centerline. The centerline of each of the plurality of serrations defines a individual tailored angle dependent on at least one of span-wise location, local chord, width, length, bend angle, and thickness.

Abstract: A wind turbine blade having a suction side and a pressure side, which sides are connected at a leading edge and a trailing edge, wherein one or more shape modifiable air foil sections are defined in the area of the trailing edge of the blade, and wherein said one or more shape modifiable air foil sections are attached to a blade body, each of the one or more modifiable air foil sections having an upper skin and a lower skin, a first one of the upper and lower skin being secured to the blade body, and a second one of the upper and lower skin being slidably movable with respect to the blade body, so that a force is applied to one of said skins cause said second skin to slide with respect to the blade body, so as to thereby modify the air foil shape of the trailing edge.

Abstract: A turbine blade includes first and second tip ribs extending from a tip floor to define a tip cavity. An exit ramp bridges the ribs and rises in elevation aft from the floor.

Abstract: A propeller fan has a gap between a bellmouth and each blade tip. A leakage flow is thus produced from a positive pressure surface of a blade toward a negative pressure surface of the blade via the gap. The leakage flow develops while flowing from the leading edge of each blade toward the trailing edge, thus forming a blade tip vortex. This increases blowing noise and raises the input of the fan motor. In order to suppress the blade tip vortex caused by the leakage flow, the present invention includes recessed portions and projected portions, which are alternately formed in a portion of a blade surface of each blade corresponding to the blade tip.

Abstract: A wind turbine rotor blade assembly includes a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. An edge extension is attached along the trailing edge and includes a first strip member having a span-wise attachment section attached to pressure side, and a second strip member having a span-wise attachment section attached to the suction side. Each of the first and second strip members has an outboard edge and an extension section that projects chord-wise beyond the trailing edge. The extension sections are adhesively attached to each other outboard of the trailing edge along a span-wise length of the first and second strip members and define an adhesively bonded closure edge of the edge extension. A method is also provided for forming an edge extension on a wind turbine rotor blade.

Abstract: A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.

Abstract: A propeller (10,110) has a hub (20,120) with blades (40,140). A safety member (50,150) is provided along at least a portion of the leading edge (43,143) of each blade (40,140); and the blades (140) may incorporate anti-cavitation slots (160).