Abstract: A portable blower, and a fan for such a blower, are disclosed in which a plurality of blades extend from one side of a generally flat fan disc. The blades are swept rearwardly relative to the intended direction of rotation of the fan disc. The blades extend from the disc and are tilted transversely and in the direction of rotation of the disc. The tilt arises either due to manufacture or rotation of the disc and constitutes an air scoop for the fan.

Abstract: A centrifugal fan and an air conditioner using the same are provided. A gurney flap having a rectangular plate or a S-shaped, twisted gurney flap may be formed in a tip of a blade provided in or on a hub of the centrifugal fan, so that noise may be effectively reduced, and efficiency increased. Further, the blade with the gurney flap may be easily formed integrally with the hub, enhancing productivity.

Abstract: A turbine blade has a root portion, a platform and an aerofoil, the aerofoil is mounted on the platform and is formed by a pressure side wall and a suction side wall and has an outer surface, the pressure side wall and the suction side wall meet at a leading edge and a trailing edge, the aerofoil has an axial chord length, the suction side wall defines part of the radially outward surface of the aerofoil, the suction side wall defines art overhang, the overhang has a maximum overhang length that is between 5% and 20% of the axial chord length of the blade and is located between 5% and 50% of the suction surface length from the leading edge.

Abstract: Some embodiments of a turbine system described herein provide a turbine that rotates in response to off-axis fluid flow, such as water flowing in a generally horizontal direction that is generally perpendicular to a vertical axis of rotation. The rotation of the turbine can drive a generator to output electrical energy.

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: An exhaust gas turbocharger, including either a variable turbine with rotatably mounted guide vanes or a compressor geometry with rotatably mounted guide vanes. At least one of the guide vanes has a profile center line with at least one of a jump and a kink.

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 airfoil comprises a suction sidewall, a pressure sidewall, a tip wall, and a tip leakage control channel. Each sidewall extends spanwise from an airfoil base and chordwise between a leading edge and a trailing edge. The tip wall extends chordwise from the leading edge to the trailing edge and joins respective outer spanwise ends of the suction and pressure sidewalls. The tip leakage control channel has an inlet and an outlet recessed into an outer surface of the tip wall. An inlet of the channel begins proximate a junction of the airfoil pressure sidewall and the tip wall. An outlet of the channel terminates at a recessed portion of the junction of the tip wall and the suction sidewall.

Abstract: A root attachment for a wind turbine rotor blade having a blade root is disclosed. The root attachment may include a wall panel configured to be coupled to the rotor blade at or adjacent to the blade root. The wall panel may define at least a portion of an airfoil shape and may include an inner side and an outer side. In addition, the wall panel may define a non-uniform cross-section between the inner and outer sides.

Abstract: A wind turbine rotor blade having a longitudinal axis, a blade root; a blade tip, a pressure side, a suction side and an aerodynamic profile which, in a longitudinal section of the rotor blade, has a profile chord and a thick trailing edge. The rotor blade includes a multiplicity of flow deflection elements which are arranged on the thick trailing edge and have respective inflow surfaces which are shaped and arranged such that a radial flow running in the direction from the blade root toward the blade tip is diverted by the inflow surface in the direction of the profile chord.

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 wind turbine rotor blade for a wind turbine having a length extending from a first end, a leading edge and a trailing edge, where a pressure side and a suction side extend between the leading edge and the trailing edge and thus define an airfoil shaped cross section. At least along a part of the length of the wind turbine rotor blade, the trailing edge comprises a trailing edge part having a first and a second installation flange, each of which has a width. The installation flanges are arranged in connection with a trailing edge extender, the first and second installation flanges both having an inner surface for installation on the pressure side and the suction side of the wind turbine blade. Also, method for fitting a wind turbine rotor blade with a trailing edge part is provided.

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 wind turbine blade having a longitudinal direction with a root end and a tip end as well as a chord extending in a transverse direction between a leading edge and a trailing edge is described. The blade comprises a flow control surface with a suction side and a pressure side. A number of boundary layer control means is formed in the flow control surface. The boundary layer control means include a channel submerged in the flow control surface with a first end facing towards the leading edge and a second end facing towards the trailing edge of the blade.

Abstract: Some embodiments of a turbine system described herein provide a turbine that rotates in response to off-axis fluid flow, such as water flowing in a generally horizontal direction that is generally perpendicular to a vertical axis of rotation. The rotation of the turbine can drive a generator to output electrical energy.

Abstract: Low flow centrifugal pump that develops more than 25 percent greater pressure than equivalent standard type spiral impellers with circular casings.

Abstract: An axial fan assembly including a casing wall with a forward facing step formed therein and a fan rotor with blade tips, each having an aft facing step which radially overlaps the casing step so as to reduce the clearance backflow loss in the assembly. A vane is attached to the suction side of each of the blade tips with the vane having an aft facing step which radially overlaps the casing forward facing step to promote further reduction of clearance backflow. Variations on the invention include the option of an additional inlet bellmouth piece that further restricts the clearance flow and wedges integral to the casing step to improved flow stability.

Abstract: A wind turbine blade having a longitudinal direction with a root end and a tip end as well as a chord extending in a transverse direction between a leading edge and a trailing edge is described. The blade comprises a flow control surface with a suction side and a pressure side. A number of boundary layer control structures are formed in the flow control surface. The boundary layer control structures include a channel submerged in the flow control surface with a first end facing towards the leading edge and a second end facing towards the trailing edge of the blade. The channel further comprises a bottom surface extending from the first end to the second end. The channel at the first end comprises a first channel zone comprising a first sub-channel having a first cross-sectional area and a second sub-channel having a second cross-sectional area, the first sub-channel and the second sub-channel crossing each other at a point of crossing.

Abstract: A cooling fan with partial ring members attached to the blade tips. The fan preferably is a one-piece molded fan with a central hub and a plurality of blade members. Partial ring members on the blade tips reduce weight and minimize potential failures caused by knit lines and operations at high rotational speeds.

Abstract: An aerodynamic slat (30F) having a flatback trailing edge (44F) extending along and spaced proximate an inboard portion of a wind turbine blade (22). At least the leading edge (42F) of the slat may be disposed within a zone (48) of airflow that is generally parallel to the suction side (40) of the wind turbine blade over a range of air inflow angles. A splitter plate (52) may extend aft from the flatback trailing edge to reduce vortex shedding and extend the effective chord length of the slat. Vortex generators (60) may be attached to the slat. Flatback slats may be retrofitted to a wind turbine rotor (20) by attaching them to the spar caps (56) of the blades or to the hub spinner (28). The flatback slat provides lift on low-lift inboard portions of the wind turbine blade over a range of angles of attack of the inboard portion.

Abstract: An airfoil is provided that has an arrangement that improves the lift of an airfoil and that include surface features that change the performance of the airfoil. Protrusions are provided on the top surface of the airfoil such that channels are formed between adjacent protrusions that affect the flow of air there through. In an additional respect, indentations can be provided on the bottom surface of the airfoil that affect the flow of air there through.

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 rotary blade is provided that includes a root, an airfoil, and a tip insert. The airfoil is attached to the root, and has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip. The slot extends in a chordwise direction between the leading edge and trailing edge. The tip insert has a base end and a rub end. The base end of the tip insert is disposed within the slot. The rub end of the tip insert extends radially outward from the airfoil tip.

Abstract: In a vehicle heat-exchange module in which a fan unit is provided at the downstream side of a rectangular heat exchanger, and the fan unit is provided with a shroud having a bell-mouth and an annular opening, a propeller fan that is disposed in the annular opening, and a fan motor that rotationally drives the propeller fan, the fan unit is a unit having a single-fan configuration in which motor input power is at a predetermined level or less, and the propeller fan is provided with two sets of winglets that are respectively constructed upright, with a prescribed gap therebetween in the radial direction, along the circumferential direction on both a pressure surface and a suction surface of the root side of the blades.

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: An axial flow fan comprises a central hub (2) and a plurality of blades (3), each fixed to the central hub (2) and extending from a respective first end (3a) proximal to the hub (2) to a respective second end (3b) distal from the hub (2); the blades (3) are inclined at a keying angle (?) to a rotation plane (R) of the fan which also comprises a plurality of aerodynamic protrusions (11), each extending from a first lateral edge (6) of a corresponding blade (3) in the vicinity of its second end (3b); each protrusion (11) lies in a plane (PP) perpendicular to an axis (A) of fan rotation.

Abstract: A wind turbine blade includes a root region. A first extension (LEX) is attached to the leading edge side of the root region while a trailing edge strake (TES) is attached to the trailing edge side of the root region. The LEX and TES each include an outer profile that becomes more pronounced relative to their respective locations in the root region as the root region of the wind turbine blade morphs from a substantially cylindrical shape to a substantially airfoil shape. The LEX provides both optimal angle of attack and lift generation in the root region, while the TES mitigates airflow separation and enhances airfoil lift in the root region.

Abstract: A winglet for a blade of a wind turbine is disclosed. The winglet contains a core with a predetermined water absorption-rate to reduce or even avoid the absorption of water in the core. This may be achieved via different variations on the core material and/or core cover material including composition, density and thickness.

Abstract: The present invention relates to a mixing impeller for an agitator. The impeller has a body that may be disc-shape. The impeller has a plurality of radially spaced-apart, longitudinally curved, channel-shaped outer vanes connected to and extending outwards from the body in a plurality of different directions. A first one of the outer vanes has a distal end at least partially facing above the body. A second one of the outer vanes has a distal end at least partially facing below the body. A third one of the outer vanes has a distal end at least partially facing tangential to the body.

Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades.

Abstract: A blade of a gas turbine engine is provided having an airfoil, a platform, a shank, a dovetail, and a skirt. The airfoil may extend distally from the platform, and the shank may extend proximally from the platform. The dovetail may also be provided to extend proximally from the shank. The skirt may be disposed on an aft side of the shank and may extend from the shank in a direction at least partially axially aft from the shank.

Abstract: A wind turbine blade is provided. The wind turbine blade has multiple vortex generators, each projecting from a surface of the blade and having a predetermined length. The vortex generators are arranged on a strip. The width of the strip is several times larger than the length of a vortex generator.

Abstract: A gas turbine airfoil blade comprises an airfoil having a leading edge and a trailing edge defining fore and aft points of an airfoil chord relative to a flowpath direction. The airfoil extends generally radially from a root to a tip, the root of the airfoil intersecting a platform of the blade. A body of the airfoil is composed of a plurality of airfoil sections stacked along a stacking line extending radially from the platform. A root airfoil section being the one of said airfoil sections intersecting the platform, the trailing edge at the root airfoil section extending to intersect the platform chordwise aft of the trailing edge of the airfoil section immediately radially outwardly adjacent to the root airfoil section.

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 turbomachine component includes a main body having a gas path surface configured to be exposed to gases passing along a turbomachine gas path, a non gas path surface configured to be arranged in a turbomachine wheelspace outside the turbomachine gas path, and a non-axisymetric flow contour feature extending from the gas path surface to the non gas path surface.

Abstract: Provided is a quiet propeller including a propeller blade having such a pitch angle not at its root portion but at its blade end edge portion with respect to a relative flow in the rotational direction, as to raise the internal pressure of a liquid thereby to eliminate a cavity, a water bubble or a cavitation at the blade root portion at the time of a high-speed rotation so that the propeller is rotated at a high speed by a small prime mover and by a prime mover capable of moving much fluid backward. In the quiet propeller, a propeller blade is curved backward at its leading end portion to form a slope portion, and a rotational front side end portion in the slope portion is formed into an arcuate shape in the side view whereas a rotational rear side end portion is so gradually extended backward from the rotational front side end portion as to become straight from the blade root to the blade end, thereby to form a deflecting slope face.

Abstract: A blade of a turbomachine or a flying machine includes a blade airfoil extending in a radial direction from a blade root to a blade tip. The blade airfoil has an inflow-side leading edge, an outflow-side trailing edge, a pressure side and a suction side. A surface of each of the pressure side and the suction side extends between the inflow-side leading edge and the outflow-side trailing edge. The blade tip has an end face with a camber line that extends from the inflow-side leading edge to the outflow-side trailing edge. At least one tip-side recess forms a depression from the end face into the blade airfoil, the depression extending continuously from the pressure side to the suction side and having a partial length of the camber line.

Abstract: A wind power unit comprising a mast, a rotor with several blades, a nacelle and optionally further components around which there is a flow, is disclosed. The surfaces of the mast and/or the rotor blades and/or the nacelle and/or the further components at least partly comprise recesses for improvement of the flow.

Abstract: A wind turbine blade has a leading edge and a trailing edge and includes an upper shell member and a lower shell member. The shell members include transversely spaced attachment edge that are spaced rearward of the leading edge. A preformed bond cap having opposite legs with rearward edges is mounted to the attachment edges of the upper and lower shell members. The bond cap is preformed into an aerodynamic parabolic shape and size so as to define the leading edge of said blade and lie essentially flush with the upper and lower shell members. The bond cap defines a primary external bonding bridge between the upper and lower shell members and defines at least a portion of the leading edge of the blade.

Abstract: A spoiler for a rotor blade of a wind turbine includes a spoiler body and at least one mounting band arranged along a longitudinal edge of the spoiler body for mounting the spoiler onto a surface of the rotor blade. The at least one mounting band adapts to a curvature of the rotor blade surface. The spoiler body and the at least one mounting band are formed as a single entity. Further, a rotor blade for a wind turbine includes such a spoiler mounted onto a surface of the rotor blade. Further, a wind turbine includes a number of rotor blades attached to a hub, wherein at least one rotor blade includes such a spoiler mounted onto a surface of the rotor blade.

Abstract: A rotor, such as a fan of a gas turbine engine, comprises blades 2 and annulus fillers 4 which extend between adjacent blades 2. Gaps 22 between each blade 2 and the adjacent annulus fillers 4 are sealed by sealing elements 8. The sealing elements 8 fit closely around the profile of the blade 2 and have annulus filler sealing surfaces 18 for sealing contact with the annulus fillers 4. The sealing elements 8 have low-friction blade sealing surfaces 12 so that, when the fan is rotating, centrifugal loading displaces the sealing elements 8 radially outwardly so that the annulus filler sealing surface 18 make sealing contact with the annulus fillers 4.

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 assembly further includes a noise reducer configured on a surface of the rotor blade. The noise reducer includes a plurality of noise reduction features and a plurality of auxiliary noise reduction features. Each of the plurality of auxiliary noise reduction features is configured on one of the plurality of noise reduction features.

Abstract: A turbomachine component includes a basic component including a first outer wall having a first joint face. An additional part includes a second outer wall having a second joint face, wherein the first and the second wall enclose an internal cavity, and wherein the first and the second joint faces are joined together between the basic component and the additional part. At least one wall-like intermediate piece is disposed in at least one of the basic component and the additional part and extends from the respective outer wall into the internal cavity, the at least one wall-like intermediate piece including a cutout having a transition contour that deviates from a straight line and is disposed at at least one transition between the at least one wall-like intermediate piece and the outer wall so as to relieve at least one of a mechanical and a thermal stress.

Abstract: The invention relates to a gas turbine blade (10), in particular a compressor blade and/or turbine blade for a turbomachine, wherein the gas turbine blade (10) comprises at least one receptacle (18) for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into gas turbine blade (10). The invention further relates to a shrouding band segment (16) for arrangement on a gas turbine blade (10), a connection system having a gas turbine blade (10) and having a connecting element, a method for connecting a gas turbine blade (10) to a connecting element, and a rotor for a turbomachine having a rotor disk (12) joined to a blade ring or having a rotor ring joined to a blade ring.

Abstract: A rotor blade includes a blade main body having a proximal end connected to the blade root, and a tip shroud connected to a tip end of the blade main body so as to constitute a part of an annular shroud, a tip end side of a leading edge of the blade main body is made continuous to an outside surface of the tip shroud via a curved portion curved toward a trailing edge, fillets are provided between the tip end of the blade main body and an inside surface of the tip shroud, and the curved portion is located closer to the leading edge than the fillets, whereby the turbine rotor blade and the turbo machine can realize weight reduction and suppress performance degradation.

Abstract: Provided is a wind turbine blade realizing enhancement of performance by a winglet provided at a blade tip. The wind turbine blade includes the winglet formed by bending a tip side thereof toward a pressure side of the blade relative to an adjacent portion adjacent on a blade root side, and a CANT angle defined by a blade axial line of the winglet relative to a radial extrapolation line of a blade axial line of the adjacent portion is set to be 15° or more and 55° or less. The winglet includes a tip end located on a tip side thereof, having a substantially linear blade axial line, and a bent portion located on a base end side of the winglet and bent relative to the adjacent portion. This bent portion is bent gradually so as to satisfy the predetermined CANT angle.

Abstract: An impeller is provided for a pump unit, in particular for a waste water pump unit, having two cover plates (2, 4), which are spaced apart from one another in the axial direction (X) and are connected to one another by at least one connecting element (8). The impeller has at least one blade (12, 14) which is arranged between the two cover plates (2, 4) and extends from an inner diameter of the impeller to an outer diameter of the impeller. The blade (12, 14) has a continuous slot (16), which extends from the edge (22, 24) of the blade (12, 14) which is situated at the inner diameter to the edge (26, 28) of the blade (12, 14) which is situated at the outer diameter. A pump unit is also provided having an impeller of this type.

Abstract: A cooling fan includes a fan housing and a stator and an impeller received in the fan housing. The fan housing includes a frame and a mounting portion located in the frame. The stator is received in the frame and mounted to the mounting portion. The impeller is mounted to the stator and rotatable with respect to the stator. The impeller includes a hub and a plurality of blades extending radially and outwardly from the hub. Each of the blades includes an inner end connected with the hub and an outer end distant from the hub. Each of the blades forms a tab on the outer end at the end surface.

Abstract: A blade for a rotor, such as a turbine rotor of a gas turbine engine, has a squealer tip comprising a peripheral wall which defines a cavity. A first region of the peripheral wall extends radially, with its outer surface forming a continuation of the adjacent aerofoil surface of the blade. A second region extends obliquely with respect to the radial direction and the adjacent part of the aerofoil surface. The second region defines a winglet, and serves to increase the width of the chamber towards the trailing edge of the blade.

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.