Abstract: A compressor wheel for a compressor of a turbocharger has a hub (16) and a multiplicity of blades (12) on the hub (16). In intermediate spaces of the multiplicity of blades (12), a channel is in each case formed between a suction side (24) and a pressure side (26). The channel guides fluid that flows in axially in relation to a rotation axis (22) radially or radially-axially outward. The hub (16) in relation to the rotation axis (22) in at least one channel is contoured with a rotationally symmetrical portion (18?) and a non-rotationally symmetrical portion (18). The non-rotationally symmetrical portion (18) is formed by radii that are variable in the flow direction, and a transition region (28) between the hub (16) and the blade (12) adjoins the non-rotationally symmetrical portion (18).

Abstract: A blade damping device for damping vibrations during standstill of a wind turbine blade, wherein the blade damping device is adapted to be detachably attached to the pressure side and/or the suction side of the airfoil region of the wind turbine blade, the blade damping device comprising a base plate adapted to conform to the exterior shape of the wind turbine blade when the blade damping device is attached to the wind turbine blade, and a spoiler protruding from the base plate to a spoiler height along a height direction and having a spoiler length along a length direction, the height direction being adapted to extend outwardly from the wind turbine blade, wherein the spoiler height is adapted to be at least 20% of a chord line located at two thirds of the blade length along the longitudinal axis from the root end of the wind turbine blade.

Abstract: A vortex generator for wind turbine blade includes: a platform; and at least one fin disposed projecting from an upper surface of the platform, and including a leading edge and a trailing edge. A rear end surface of the at least one fin, including the trailing edge, has a shape inclined backward as a distance from a bottom surface of the platform increases in a height direction of the fin.

Abstract: A system includes a gas turbine having a turbine shaft disposed along a rotational axis, a turbine casing disposed circumferentially about the turbine shaft, a combustion gas path disposed between the turbine shaft and the turbine casing, and a turbine stage disposed in the combustion gas path. The turbine stage includes a plurality of turbine vanes disposed upstream from a plurality of turbine blades. The gas turbine includes an isothermal expansion system coupled to the turbine stage, wherein the isothermal expansion system includes a plurality of flame stabilizers configured to vary axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion. The flame stabilizers are disposed in different axial positions over an axial length between leading and trailing edges of the turbine blades, wherein at least one flame stabilizer is coupled to each of the turbine blades.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes a platform section and an airfoil section extending in a spanwise direction from the platform section to a tip portion establishing a tip. The airfoil section has an external wall defining pressure and suction sides extending in a chordwise direction between a leading edge and a trailing edge, and the pressure and suction sides are spaced apart in a thickness direction between the leading edge and the trailing edge. The tip portion includes a tip pocket and a tip shelf extending inwardly from the tip. The tip pocket and tip shelf are on opposite sides of a shelf wall.

Abstract: A paddle for propelling a watercraft through water. The paddle includes an elongated shaft having a handle at one end and a paddle portion at the other end. The paddle portion includes a substantially flat member having opposite first and second sides, a central portion and a peripheral edge. A plurality of convolutions are formed on the peripheral edge of the paddle portion, with each convolution consisting of a finger positioned between a pair of notches, the notches extending from the peripheral edge towards the central portion. The shape and size of the notches and fingers can be selected to control the optimal performance of the paddle.

Abstract: A strut provided in an exhaust diffuser and having an airfoil-shaped cross-section is provided. The strut may include a cut portion configured to be formed in a trailing edge in a span direction. The cut portion is configured to provide a stepped portion in at least a portion of the trailing edge.

Abstract: A rotor blade for a wind turbine, comprising a rotor blade root for fixing the rotor blade to the hub of a wind turbine, an inner blade portion which extends from the rotor blade root in the direction of a longitudinal extension of the rotor blade, and a rear edge segment for increasing the depth of the rotor blade in the profile depth direction in the region of the inner blade portion, wherein the rear edge segment is fixed to the inner blade portion and has an edge facing the inner blade portion. A cover lip is proposed which overlaps with the edge and is arranged in a transition region from the inner blade portion to the edge of the rear edge segment.

Abstract: A rotor blade of a wind turbine, having a rotor blade length, a rotor blade depth extending over the rotor blade length, a rotor blade thickness extending over the rotor blade length, and a thickness of a trailing edge of the rotor blade extending over the rotor blade length, wherein, in a region of the rotor blade length, the rotor blade simultaneously has a splitter plate that has a predetermined length and a Gurney flap that has a predetermined height, wherein a ratio of the predetermined height of the Gurney flap to the predetermined length of the splitter plate at a particular position in the direction of the rotor blade length is selected in such a manner that a threshold value that decreases with a relative profile thickness, which is defined as a ratio of the rotor blade thickness to the rotor blade depth, is not reached.

Abstract: The invention relates to a rotor blade (100) for a wind turbine, having a rotor blade root (102), a rotor blade outer edge (104), a leading edge (106) and a trailing edge (108), The leading edge (106) and the trailing edge (108) define a chord (110), the length of which increases from the rotor blade root (102) to the rotor blade outer edge (104), Chord centre points (112) define a rotor wing centre line (114) running from the rotor blade root (0.102) to the rotor blade outer edge (104) and the rotor wing centre line (114) divides the rotor blade outer edge (104) into a leading edge portion (116) and a trailing edge portion (118), a winglet (120) that extends only along the trailing edge portion (118) being arranged on the rotor blade outer edge (104).

Abstract: A strut provided in an exhaust diffuser and having an airfoil-shaped cross-section is provided. The strut may include a cut portion configured to be formed in a trailing edge in a span direction. The cut portion is configured to provide a stepped portion in at least a portion of the trailing edge.

Abstract: A method of repairing a tip of an airfoil can comprise: removing a coating from the tip of the airfoil; preparing a repair area for bonding, the repair area including the tip and a portion of a concave side of the airfoil; applying an epoxy film and an abrasive component to the repair area; and bonding the epoxy film and the abrasive component to the repair area.

Abstract: A ceiling fan blade is provided. The ceiling fan blade is configured to be mounted on a rotating base, and includes a main body and a blade holder connected to the main body. The blade holder is configured to be mounted on the rotating base. The main body includes a windward part arranged adjacent to a side of the main body and a plurality of air guiding structures arranged adjacent to the windward part. Each of the air guiding structures and the side of the main body that is adjacent to the windward part is 0.2 to 0.4 times of a width of the main body.

Abstract: A method for improving performance in an aircraft having a winglet coupled to a wing, the winglet having a leading edge and a trailing edge continuously transitioning from a leading edge and trailing edge of the wing. The method includes coupling a wing tip to the winglet. The wing tip may include a curved leading edge from the winglet leading edge to a leading end point, a curved trailing edge from a winglet trailing edge to a trailing end point, and an end segment connecting the leading end point and the trailing end point. The end segment may be swept back from the trailing end point to the leading end point at an end segment angle.

Abstract: A turbine rotor blade includes: a root portion fixed to a rotor shaft; and an airfoil portion including a pressure surface, a suction surface, and a top surface connecting the pressure surface and the suction surface, with a cooling passage formed inside the airfoil portion. The top surface of the turbine rotor blade includes a leading edge region located on the leading edge side and formed parallel to the rotor shaft, and a trailing edge region adjacent to the leading edge region. The trailing edge region has an inclined surface inclined radially inward toward a trailing edge.

Abstract: An impeller for use in an aquarium filter pump includes a shaft and a plurality of impeller blades radially extending from the shaft. Each of the impeller blades includes opposite blade faces. A depression is in each of the blade faces and aids in pushing the water. The depression can be a variety of shapes and can have its deepest portion along one of the edges of the blade.

Abstract: There is provided a gas turbine engine comprising a low pressure shaft and a high pressure shaft; wherein the low pressure shaft connects a fan to a fan drive turbine, and the high pressure shaft connects a high pressure turbine to a compressor section. The low pressure shaft and the high pressure shaft are arranged such that when operating at idle the idle shaft speed ratio is greater than 6.05. The idle shaft speed ratio is the ratio of the speed of the high pressure shaft to the speed of the low pressure shaft at idle conditions.

Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. A fan section has an array of twenty-six or fewer fan blades. An airfoil includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with the leading edge angle of less than 40° at 100% span.

Abstract: A fan wheel has a hub cup and a plurality of blades extending radially outward from an outer wall of the hub cup, which is in particular at least substantially cylindrical. Each blade has a leading edge and a trailing edge, wherein for at least one blade, the progression of a relative position of the blade's leading edge and/or the progression of a relative position of the blade's trailing edge has an aperiodically wave-like shape. There is also described a radiator fan module with a fan wheel of the type described above, and a motor vehicle with such a radiator fan module.

Abstract: A heat dissipation fan including a hub and a plurality of metal fan blades disposed all around the hub. Each of the metal fan blades has a first end and a second end opposite to each other, wherein the first end is connected to the hub, and the metal fan blade has a flap wing at the second end. An angle is included between the flap wing and a surface of the metal fan blade.

Abstract: A blade/vane cascade segment of a blade/vane cascade for a turbomachine is disclosed, which comprises a stage with a stage surface as well as a first blade/vane element and a second blade/vane element. The stage surface comprises a first elevation reaching as far as the pressure side of the first blade/vane element and a second elevation reaching as far as the suction side of the second blade/vane element. A furthest downstream point of a boundary of the second elevation has an axial position which differs from the axial position of at least one highest point of the first elevation by a maximum of 10% of an axial cascade span. Furthermore, a blade/vane cascade, a blade/vane channel, a stage, a turbomachine and an aircraft engine are disclosed.

Abstract: There may be provided a wind power system that may include a turbine that comprises multiple curved blades that rotate about a vertical axis; wind collectors that surround the turbine; wherein each wind collector comprises a set of facets that define an outlet and an opening that is bigger than the outlet; wherein the outlet faces the turbine; and a ventilation mechanism.

Abstract: A method for applying a serrated rear edge to a blade rear edge of a rotor blade of a wind turbine that has a pressure side and a suction side.

Abstract: A mountable wing tip device (102) for mounting on a rotor blade of a wind turbine is disclosed which comprises a forward extremity (106) and at least two rearward extremities (108A, 108B, 112), wherein the forward extremity (106) and the at least two rearward extremities (108A, 108B, 112) are triangularly arranged, a leading edge region extending between the forward extremity (106) and the at least two rearward extremities (108A, 108B, 112), and a trailing edge region extending between the rearward extremities (108A, 108B, 112), a root region (113) at which the wing tip device (102) is mountable on an end of the rotor blade, wherein the root region (113) is positioned between the leading edge region and the trailing edge region.

Abstract: An agitator for mixing solutions in a bottle is described. The agitator is comprised of a handle portion and a whisk portion. The agitator may have a helical-shape to encourage spinning of the agitator as liquid flows past the agitator. The whisk may be flat-bottomed and formed of a flexible material, such that when the whisk portion comes into contact with the bottom of the bottle, the whisking members splay outwardly.

Abstract: An airfoil blade assembly including a blade which includes a lift generating section with a first profiled body defined between a pressure surface and a suction surface. The first profiled body extends from a first leading edge to a first trailing edge with a first chord extending form the first leading edge to the first trailing edge and being perpendicular to the radial direction. At least one flow deflector extends along either the pressure surface or the suction surface within the lift generating section of the blade. The at least one flow deflector defines a second profiled body extending between a second leading edge and a second trailing edge with a second chord extending between the second leading edge and the second trailing edge. The second profiled body defines an outer surface facing away from respective pressure surface or suction surface along which the flow deflector extends.

Abstract: A blade assembly including a blade which includes a lift generating section with a first profiled body defined between a pressure surface and a suction surface. The first profile body extends from a first leading edge to a first trailing edge with a first chord extending form the first leading edge to the first trailing edge and being perpendicular to the radial direction. A plurality of flow deflectors extend along either the pressure surface or the suction surface within the lift generating section of the blade. The plurality of flow deflectors define a second profile body extending between a second leading edge and a second trailing edge with a second chord extending between the second leading edge and the second trailing edge.

Abstract: An airfoil for a rotor blade or a stator vane of a gas turbine engine having a tip extension extending one or both of the suction and pressure side surfaces adjacent the tip. The tip extension defines a thickness at the tip larger than the true thickness of the airfoil. The tip extension includes a side transitional surface substantially defined along a curve extending tangentially from the corresponding side surface. The tip extension defines a gradual increase in the thickness over a portion of the airfoil having a radial dimension corresponding to at least 2 times the true thickness.

Abstract: The present invention relates to a method for modelling a part (1), the method being characterized in that it comprises implementing, using data processing means (11) of a piece of equipment (10), steps of: (a) parameterizing a curve of class C1 representing the value of a physical quantity characterizing said part (1) as a function of a position along at least one portion of the part (1), the curve being defined by: a. two end points (PCU0, PCUK) defining the extent of said portion of the part (1); b. at least one intermediate point PCUi, i?[[1,K?1]]) located between the two end points (PCU0, PCUK); c. at least two Bezier curves connected to said intermediate point; the parameterization being carried out using one or more parameters defining said intermediate point; (b) determining optimized values for said parameters of said curve; and (c) returning the determined values to an interface (13) of said piece of equipment (10).

Abstract: A blower wheel comprises a hub, a guide and blades extending radially between the hub and the guide, each blade comprising a root at its junction with the hub and a head at the junction with the guide, each blade having a leading edge and a trailing edge between which, at each flattened cross section, a chord is defined. For each blade, between the root and the head, the length of the chord varies and the variation in the length of chord between the root and the head has a point of inflexion between two levels.

Abstract: A blade of a turbomachine is disclosed. A contour variation is provided on the suction side of the blade, where the contour variation has a negative step as viewed in a direction of flow. The step has a stepped surface extending perpendicularly to a contour of the suction side and the contour variation has a tangential surface which leads upstream tangentially on the contour of the suction side starting from a step edge.

Abstract: A dishwasher having a washing container, a sorption dryer device connected to the washing container in an air-conducting fashion, and at least one flow-conditioning device to homogenize a flow cross-section profile of an airflow as the airflow flows through the sorption dryer device. The flow-conditioning device is provided for the sorption unit between at least one heating element and the sorption unit of the sorption dryer device when viewed in the direction of the airflow such that essentially every point of an intake cross-section area of the sorption unit of the sorption dryer device is permeated by a volumetric airflow with essentially the same intake temperature.

Abstract: Noise produced by the blades of a wind turbine electric generator is reduced by creating randomly varied serrations on the trailing edge of the blade, thereby creating vortices of varying size, energy, and distance from the trailing edge. This configuration creates vortices that tend to cancel one another while avoiding the creation of adjacent, mutually reinforcing vortices.

Abstract: A wind turbine blade includes a root portion, a tip and a body extending between the root portion and the tip. The body has a pressure side and a suction side. The body further has at least one winglet. Each winglet has a spanwise extension towards the root portion of the rotor blade and that ends at the tip to form a winglet having a substantially C-shaped or substantially open P-shaped geometry.

Abstract: By means of a simple structure, lightning resistance is improved without increasing the level of fluid noise due to a lightning discharge member provided on a surface of a wind turbine blade. A wind turbine rotor blade lightning discharger, in which a diverter strip serving as a lightning discharge member protrudes from a surface of a wind turbine blade that extends in a radial direction from a rotor head supported in a freely rotatable manner, includes a noise suppressing structure that suppresses the generation of a Karman vortex, which causes noise, on the downstream side of the diverter strip with respect to an airflow that flows at the surface of the wind turbine blade during rotation of the wind turbine rotor blade.

Abstract: The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.

Abstract: Provided is a wind turbine for generating electric energy using wind power, and more specifically, a wind turbine having a nacelle fence for improving aerodynamic performance by mounting a fence structure on the nacelle of a horizontal axis wind turbine. The wind turbine having a nacelle fence decreases the vortex that is generated at the downstream ends of rotating blades so as to improve the aerodynamic performance of the blades, and increases the power coefficient of the wind turbine.

Abstract: Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.

Abstract: An integrally bladed disk includes a rotor disk and circumferentially spaced first and second blades. The rotor disk has a rim the periphery of which forms a flow surface. The first and second blades extend integrally outward from the rim. The rim defines a trench in the flow surface between the first and second blades aft of a leading edge of the rim. The trench extends axially forward and rearward of a leading edge of the first blade.

Abstract: A torque converter impeller is provided. The torque converter impeller includes an impeller shell and an impeller hub. The impeller shell and impeller hub are autogenously welded together such that the weld has a concave shape. A method of forming a torque converter impeller is also provided.

Abstract: A particular arrangement of vortex generators for an airfoil is described. The vortex generators are provided in pairs, preferably on a wind turbine blade, wherein by arranging the vortex generators according to specified characteristics, a surprising improvement in blade performance is provided over the prior art systems.

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: An apparatus for attracting fish is disclosed. The apparatus has a motor with rotating driveshaft that defines a rotational axis substantially parallel to a surface of a body of water. A housing encloses the motor, and the driveshaft extends therefrom. There is an impeller with a hub axially aligned with and coupled to the driveshaft. The impeller has one or more flat planar blades, each defined by a trailing edge and a leading edge and extending radially from the hub in an orthogonal relationship to the rotational axis of the driveshaft without pitch. A proximate end of the blades is fixed to the hub an opposed distal end includes a cupped paddle projecting therefrom with a paddle leading surface and a paddle trailing surface. Turbulence and cavitation is generated by the impeller, and the visual and audible side effects thereof are simulative of fish feeding activity.

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: An axial flow fan includes a blade having a curved portion formed in the vicinity of a radially outer end portion positioned opposite to the base portion in the radial direction of the peripheral wall portion of the hub. The curved portion is convex in the rotation direction, concave in the direction opposite to the rotation direction, and extends along the radially outer end portion of the blade. The curved portion extends from a rear end edge of the blade, positioned on a side where one end of the base portion of the blade is positioned, and extends in the radial direction of the hub to the vicinity of a front end edge of the blade, positioned on a side where the other end of the base portion of the blade is positioned and extending in the radial direction.

Abstract: A turbocharger assembly including a turbine housing defining an exhaust inlet opening and an exhaust outlet opening and a turbine wheel housed in the turbine housing. The turbocharger assembly also includes a compressor housing defining an air inlet opening and an air outlet opening and a compressor wheel housed in the compressor housing. The turbocharger assembly also includes a shaft coupling the turbine wheel to the compressor wheel. The turbine housing, the turbine wheel, the compressor housing, and/or the compressor wheel includes a surface having a series of protrusions or depressions configured to increase the efficiency of the turbocharger assembly.

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 fan blade comprises a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. Material is deposited within the channels, with one type of material being selected to provide additional stiffness to the fan blade, and a second type of material being selected for having good damping characteristics. A method and gas turbine engine are is also disclosed.

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.