Abstract: A turbomachine blade having features arranged to initiate bending of the leading edge towards the pressure surface upon impact of a foreign object on the leading edge. The features may be features weaker than the material of the leading edge located on the pressure surface side of a mid-thickness line. By causing the leading edge to bend towards the pressure surface on impact the volume of the foreign object, typically a bird, that passes over the suction surface is reduced.

Abstract: An impeller of a centrifugal fan includes a hub and a plurality of blades arranged on and around the hub. Each of the blades includes a root portion and a tip portion. The tip portion of each of the blades has a concave surface and a convex surface in rear and front sides thereof respectively. In a rotational direction of the impeller, the tip portion of a rear blade protrudes towards a front blade.

Abstract: In a transonic region with a Reynolds number not more than a critical Reynolds number, a flow velocity distribution on an extrados of an airfoil has a single supersonic maximum value within a range of up to 6% from a leading edge on a chord, or a shape factor has a maximum value in a region of 6 to 15% from the leading edge on the chord, the value being nearly constant in a region of 30 to 60% and gradually can increase up to 2.5 in a region downstream of 60% of chord. A pressure loss in a low Reynolds number region can be drastically reduced, while conventionally keeping low the pressure loss in a high Reynolds number region. Moreover, this pressure-loss reduction effect in the low Reynolds number region is exerted even if an inflow angle is changed in a wide range.

Abstract: The present device is a vertically oriented wind turbine blade having a rectangular curvilinear shaped blade which includes a top edge, a bottom edge, an outer edge, a helical inner edge, an inner surface and an outer surface. The blade's top edge is curved and defines a radius R and the helical inner edge defines an angle theta relative to a vertical reference line.

Abstract: A bucket for a turbine is described. The bucket includes a dovetail portion configured to couple the bucket to a turbine wheel, the dovetail portion having a lower surface. The bucket also includes a shank portion that extends from the dovetail portion and an airfoil having a root and a tip portion, an airfoil shape, and a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table I. The bucket also includes a plurality of cooling passages. The plurality includes no more than five cooling passages that extend between the root and the tip portion of the airfoil. Each of the cooling passages exits the airfoil at the tip portion, the plurality of cooling passages are positioned in a camber line pattern.

Abstract: An electricity-generating Savonius-type wind turbine apparatus has a pair of blades configured helically around a central axis. The wind turbine apparatus is modular and sectional such that each section includes a pair of blades useful for being pushed by wind to generate electricity via an attached electrical generator. Further, a series of modular wind turbine sections generates electrically via an attached electrical generator. The wind turbine apparatus further includes one or more airfoils attached to an axis of rotation for aiding in the rotation of the central axis for generating electricity.

Abstract: The special circumstances of working with hydroelectric turbines in pipes require innovations in blade shapes and systems that are presented here. An example is streamlining of the blades greater than that found in traditional hydroelectric turbines.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the TABLE. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Abstract: The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, is disclosed. The blade includes an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ; and a connection zone between the airfoil and the airfoil end face. The connection zone forms a fattening of the airfoil. The connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil upstream of the suction face neck and a point P3 situated on the pressure face of the airfoil upstream of the pressure face neck.

Abstract: A vertical-axis wind turbine for use with an electrical generator for producing power by converting the energy of wind currents into mechanical rotational energy which is then used to operate the electrical generator. In an embodiment, a rotor is responsive to wind currents by imparting rotation upon a central vertical shaft. Preferably, the rotor is designed with functional curved surfaces for efficient operation.

Abstract: A camber line in a radial section of a runner vane has a curved part extending near the tip of the runner vane is convex toward the front surface of the runner vane. The runner vane is formed in a shape meeting a condition expressed by: ?s<?p, where ?s is the radius of curvature of the back surface of the runner vane and ?p is the radius of curvature of the front surface of the runner vane. The runner vane of this shape suppresses flows toward the tip thereof to moderate the variation of flow velocity in the turning direction. Consequently, loss can be reduced without impeding the recover of pressure in a draft tube.

Abstract: An impeller for use in conjunction with a percutaneously-insertable blood pump or other rotatable equipment includes a blade that is segmented into a plurality of overlapping or abutting bladelets. In some embodiments, the bladelets are foldable and one side of each bladelet is concave.

Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: An improved rotor blade used in combination with a submersible electrical generator comprises a rotor base with width BW, a leading edge, a tip, and a trailing edge. The leading edge and the trailing edge are defined as elliptical curves having a radius of 8.0 BW. The rotor has a surface area profile substantially in accordance with the Cartesian coordinate values X and Y set forth in Table I. The rotor blade can be functionally connected to a rotor shaft through a pivotal support axial which allows the pitch of the blade to be set and maintained. The pitch is set to harness the kinetic energy of flowing water for generating electricity.

Abstract: A mixed flow turbine or radial turbine suppresses a rapid increase in load applied on a leading edge of a blade, and can reduce incidence loss. The mixed flow turbine or radial turbine includes a hub, and a plurality of blades provided on an outer circumference surface of the hub at substantially equal intervals. The camber line of the blade section is convex-curved to the rotational direction side as seen entirely from a leading edge side toward trailing edge side. On a leading edge section of the blade, there is provided an inflected section that is inflected so that a camber line in a sectional surface along the outer circumference surface is concave-curved to the rotational direction side.

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

Abstract: A fan includes a frame, a motor and an impeller. The motor is disposed on the frame and coupled to the impeller to drive the impeller to rotate. The impeller includes a hub, a plurality of blades and an air exhausting structure. The hub has an opening formed on a top portion of the hub. The blades are disposed around the hub. The air exhausting structure is disposed in the opening for discharging hot airs generated by the motor out of the hub.

Abstract: A vertical axis wind turbine that utilizes a unique semi-circular, angled, scoop design and frame to fully harness wind energy. The shape of the scoops maximizes wind collection while minimizing wind resistance. The angle of the scoops allows the wind turbine to catch wind, including updrafts, to produce a rotational and balanced lifting force on the scoop system. This balanced lift is possible due to a stable frame which maintains a fixed position of the vertical axis.

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

Abstract: An article of manufacture includes an object having an airfoil core shape. The airfoil core shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1 where X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil core shape.

Abstract: A large capacity wind power generator is provided, which includes an outer rotor including an upper partitioning plate having a plurality of spokes formed along a circular circumference of the upper partitioning plate at equal intervals and a side partitioning plate formed on one side surface of the outer rotor, the outer rotor having a lower surface and the other side surface which are open; and a windmill formed inside the outer rotor to be rotated by wind flowing through the outer rotor. The side partitioning plate is formed to have an area that is smaller than a half of the entire circumferential area of the outer rotor, and spaces between the respective spokes are open so as to facilitate an inflow of the wind through the side surface of the outer rotor.

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

Abstract: A fan and a fan wheel thereof are provided. The fan comprises the fan wheel and a fan cowl. The fan wheel comprises a hub and a plurality of blades. The hub can define an axial direction and a radial direction, and each of the blades has an axial length and a radial length. The portion of each of the blades that extends along the axial direction over a top edge of a side wall of the hub accounts for the axial length in a ratio between one third and two thirds. A connection portion connecting a central portion to the side wall of the hub, and a tip and a tail of each of the blades, as well as a flow conducting portion connecting a top wall to a central hole of the fan cowl, are all rounded. Thereby, the fan and the fan wheel thereof can strengthen the flow rate and reduce the noise generated by the fan.

Abstract: A turbomachine has at least one rotor blade row designed for extremely high work coefficients (high-load), which—in its center section and/or averaged over the blade height—provides for an essentially swirl-free relative outflow. The respective rotor in its trailing edge area is essentially orientated in meridional direction, with the mean or averaged exit metal angle of the rotor blade ranging from ?10 to +5 degrees.

Abstract: A turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 1. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z arc joined smoothly to one another to form a complete airfoil shape.

Abstract: When cold and in the uncoated state, the aerodynamic airfoil is substantially identical to a nominal airfoil determined by the Cartesian coordinates X, Y, Z? given in Table 1, in which the coordinate Z? is the ratio D/H where D is the distance from the point in question to a reference plane P0, located at the base of the nominal airfoil, and H is the height of this airfoil, measured from said reference plane up to the tip of the blade. The D and H measurements being taken radially with respect to the axis of the turbine whereas the X coordinate is measured in the axial direction of the turbine.

Abstract: A centrifugal pump having a turbine impeller having a plurality of curved vanes. The vanes curve from the inlet end to the outlet end in the direction of pumping rotation of the impeller, such that the leading wall of each vane re-directs a portion of the radial velocity of the fluid flowing through the passage to increase the total tangential velocity provided by the impeller. Each vane includes a cavity which entrains fluid which slides back from a spinward passage and redirects the entrained fluid back in the direction of rotation.

Abstract: Disclosed is a blade including a blade body including a leading edge and a trailing edge, and at least one trailing edge cavity defined by a blade area disposed in at least partial alignment with the trailing edge, the at least one cavity extending a desired depth into said blade body in a direction of the leading edge.

Abstract: A centrifugal multiblade fan according to the present invention sucks air from one end side of an axial direction of a rotation axis to a radial inside, and blows the air to a radial outside. The centrifugal multiblade fan includes a plurality of blades located around the rotation axis. Each blade has a leading edge positioned at the radial inside, and a trailing edge positioned at a radial outside. The leading edge of each blade has an edge shape with a radius of curvature of 0.2 mm or less, for example.

Abstract: A turbine includes a turbine wheel having a plurality of buckets, each of the buckets including a bucket airfoil, a bucket dovetail to connect the bucket to a turbine wheel and a shank shape to connect the airfoil to the bucket dovetail, the shank having an uncoated nominal profile including a concave, pressure side, substantially in accordance with Cartesian values of X, Y and Z? set forth in Table I wherein the Z? values are non-dimensional values in a range from 0 to 1 convertible to Z distances in inches by multiplying the Z? values by shank height in inches, and a convex, suction side, substantially in accordance with Cartesian values of X, Y and Z? set forth in Table II wherein the Z? values are non-dimensional values in a range from 0 to 1 convertible to Z distances in inches by multiplying the Z? values by the shank height in inches.

Abstract: A turbine bucket including a bucket airfoil having an airfoil shape is provided. The airfoil shape has a nominal profile according to the tables set forth in the specification. The X and Y coordinate are smoothly joined by an arc of radius R defining airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. The airfoil profile results in improved efficiency and airfoil loading capability.

Abstract: The suction surface blade angle of a transonic fan blade, subject in use to a shock wave, progressively reduces along part of the suction surface, beginning at a position upstream of the shock wave position. The increased area variation at the location of the shock results in the shock position becoming less sensitive to small geometric imperfections. The reduced shock sensitivity reduces the variation in aerodynamic load and hence reduces the untwist variation with respect to small geometric imperfections. This has the effect of stabilising the untwist deflections of the fan.

Abstract: A turbine bucket including a bucket airfoil having an airfoil shape is provided. The airfoil shape has a nominal profile according to the tables set forth in the specification. The X and Y coordinate are smoothly joined by an arc of radius R defining airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

Abstract: A Savonius vertical axis wind turbine rotor, that is effective yet relatively easy to manufacture, includes spokes, vanes, and fasteners. Each spoke has a hub having a central opening, three arcuate ribs extending radially outwardly from the hub with inner (concave) and outer (convex) surfaces, and channels defined in at least one of the inner and outer surfaces. The vanes of sheet material generally conform to an inner or outer surface of a rib and have openings aligned with the channels. First fasteners pass through the openings and cooperate with second fasteners in the channels. Two of the spoke pieces may be joined by a bridging piece, and two spoke pieces by a clamp. A Savonius or helical rotor includes a generator, and a drive connecting the generator and rotor. The drive automatically increases the effective gear ratio between the generator and rotor as the speed of rotation increases.

Abstract: A blade for a gas turbine engine includes an aerofoil portion and a root portion defined by concave and convex walls having opposing inner surfaces. A reinforcing member is located between the concave and convex walls and is bonded to the inner surfaces of the concave and convex walls, and the root portion includes an unbonded region in which the reinforcing member contacts an inner surface of one of the concave and convex walls but is not bonded to the concave and convex walls.

Abstract: A rotor airfoil having a leading edge extending from a root to a tip, an inner span region and an outer span region the leading edge having a sweep angle profile such that the sweep angle increases from the root a first height location at a first rate of change of sweep angle that is substantially constant and thereafter increases at a second rate of change of sweep angle that is substantially constant.

Abstract: A blade for a gas turbine engine includes a root portion, an aerofoil portion and a transition portion between the root portion and the aerofoil portion. The aerofoil portion and the transition portion are defined by first and second wall members, the first and second wall members being secured together in the transition portion and each having an outer surface. The outer surface of at least one of the first and second wall members is generally concave in the transition portion in a radial direction of the blade.

Abstract: In an axial flow fan, a line extending from a center axis and passing a corner where a following edge and a radially outer edge of a blade of an impeller meet is arranged forwardly in a rotational direction from an another corner where a leading edge of the blade and a radially outer surface of a hub meet. Furthermore, a camber ratio of the blade, which is minimum at a joint with the hub across the blade, monotonically increases to be maximum at the radially outer edge of the blade.

Abstract: The invention pertains to a rotor blade for a wind power system as well as a wind power system. The present invention is based on the objective of disclosing a rotor blade with a rotor blade profile and a corresponding wind power system that make it possible to improve the efficiency in comparison with arrangements known thus far. In the proposed rotor blade for a wind power system, the position of maximum thickness of the rotor blade lies approximately between 15% and 40%, preferably between 23% and 28%, and the maximum profile thickness lies approximately between 20% and 45%, preferably between 32% and 36%.

Abstract: An arrangement for turbine bucket or nozzle airfoils that accounts for the radial variation of inlet flow angle with the boundary layer of flow adjacent to the inner and outer sidewalls. Local chambering of the airfoil sections in the region of the sidewalls provides an airfoil and fillet with an optimum shape for accommodating the radial distribution of the inlet flow angle for the working fluid in the sidewall region.

Abstract: A blade for a device for generating energy from a fluid including a driving surface inside which a fluid is intended to flow in order to rotate the blade about a rotational axis {right arrow over (X)}0, {right arrow over (Y)}0 which defines with axes {right arrow over (Y)}0, {right arrow over (Z)}0 an orthogonal reference frame, {right arrow over (X)}0, {right arrow over (Y)}0, {right arrow over (Z)}0. Said blade being bounded by a leading edge and a trailing edge, narrowing between the leading edge and the trailing edge, running along a neutral fibre, where the projection of the neutral fibre onto the plane {right arrow over (X)}0, {right arrow over (Y)}0 has a first curvature. The plane {right arrow over (X)}0, {right arrow over (Y)}0 being defined so as to contain the neutral fibre at the leading edge. The blade is particularly applicable to wind generators.

Abstract: Scrolls made from one or more near-net shaped powder metal processes either wholly or fabricated together from sections. Both “conventional” press and sinter methods and metal injection molding methods will be described.

Abstract: A centrifugal pump having a turbine impeller having a plurality of curved vanes. The vanes curve from the inlet end to the outlet end in the direction of pumping rotation of the impeller, such that the leading wall of each vane re-directs a portion of the radial velocity of the fluid flowing through the passage to increase the total tangential velocity provided by the impeller. Each curved passage has cooperating inlet and outlet areas and a smooth curved shape to ensure that the radial velocity of the liquid does not decrease dramatically while flowing through the passage, while ensuring that any solid particulates and contaminants entering the impeller will pass therethrough.

Abstract: The present invention is a vertical wind turbine having a turbine with a plurality of blades or wind vanes. The blades are constructed and attached to the shaft of the turbine so as to allow them to twist open to present more surface area to wind currents when a threshold rotational velocity is reached. Also presented are a novel outer shell that is placed over at least part of the shaft and a novel turbine 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: A family of airfoils for a wind turbine blade. Each airfoil may include a blunt trailing edge, a substantially oval shaped suction side, and a substantially S-shaped pressure side.

Abstract: The instant invention deals with the solution to technical flaws of existing vertical axis windmills in which the wind strikes simultaneously on inward and outward facing sides of rotor blades which reduce efficiency. Hence, this invention, i.e., the vertical axis windmill with wind guiding device, includes vertical plates which are fixed from the bottom of a base structure to the top of a rotor in an annular array. In between any two vertical plates, inclined plates are fixed from the bottom of the base structure to the top of the base structure. These plates are tilted towards the concave side of the rotor blades. The vertical and inclined plates are fixed in angular and radial directions so that whenever the wind blows from any direction, it gets compressed and then is diverted towards the wind receiving blades. Also the vertical plates protect the convex side of the rotor blades from wind while diverting the wind towards the wind receiving blades.

Abstract: A single stage high pressure turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: A transonic turbine blade. Expansion waves are generated by a lifting surface on the blade. The expansion waves extend downstream, through a shock generated at the trailing edge of an adjacent blade. The invention increases the strength of the shock, thereby attenuating the expansion waves passing through the shock. One stratagem for increasing the shock is to reduce the aerodynamic load of the trailing edge generating the shock.