Abstract: Devices and methods of manufacturing important parts of a Benkatina Turbine are described.

Abstract: Turbine blades and methods of forming modified turbine blades and turbine rotors for use in an engine are provided. In an embodiment, by way of example only, a turbine blade includes a platform and an airfoil. The platform includes a surface configured to define a portion of a flowpath, and the surface includes an initial contour configured to plastically deform into an intended final contour after an initial exposure of the blade to an operation of the engine. The airfoil extends from the platform.

Abstract: A turbine assembly comprising a blade assembly having a plurality of curved blades with an inner end of each of the curved blades terminating at a cavity. The cavity has an open side with a generator located within the cavity and coupled to the blade assembly. The turbine assembly is suitable for underwater use. Multiple turbine assemblies may be connected to form a power generation station.

Abstract: A turbine wheel for a gas operated medical handpiece includes a plurality of blades which extend in radial direction from a hub and extend in axial direction from a side ring web of the turbine wheel, and the front side of which is substantially concavely curved about an approximately radially running first axis of curvature. In order to increase the drive power or to better exploit the drive power at least one blade has at least in an axial end region an inclination surface which is inclined in the axial direction towards the front side.

Abstract: Wind turbine blade (1) comprising a first blade part (2) and a second blade part (3), said blade parts (2, 3) being bonded by bonding means forming a bond (4). To reduce peel stresses of the bond and reduce the risk of crack formation, an edge portion of the bond (4) is covered by a low elastic modulus adhesive joint (5) bridging a gap between the first blade part (2) and the second blade part (3).

Abstract: A vertical axis wind turbine which includes a rotor having three radially extending blades spaced at even intervals about a central axis. Each radially blade having an outer edge that lies on an imaginary circle of a first diameter. Each radially extending blade including a plurality of spaced airfoil sub-blades separated by gaps for the passage of air therethrough. Each of sub-blade having a leading vertical edge, and a trailing vertical edge and being positioned with the trailing vertical edge along a common radius line of the imaginary circle. Each sub-blade is skewed such that its cord line is rotated negative 45 degrees with respect the radius of the imaginary circle. The airfoil sub-blades maximize energy production by creating a secondary wind flow of a higher velocity for impingement upon blades of the rotor, and utilize backpressure during the second half of a rotation cycle to efficiently break the rotor against overspeed.

Abstract: A turbine blade is provided, comprising a stator-side end located toward a stationary stator cylinder of the turbine, a rotor-side end located toward an axial rotor of the turbine, a leading edge located between the stator-side end and the rotor-side end, a trailing edge located between the stator-side end and the rotor-side end and located down-stream of the leading edge with respect to a fluid flow direction, wherein the rotor-side and stator-side ends have a negative sweep angle as measured between the instantaneous tangent of the blade surface and the fluid flow direction.

Abstract: The invention relates to a blade of a rotor of a ninth phase of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, the blade having a profile which can be identified by having a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, the blade also comprising a thickening, substantially parallel to a base portion of the blade itself, fixable to said rotor, said thickening being substantially situated half-way up the blade and being suitable for shifting the natural resonance frequencies of the blade itself outside a functioning frequency range of said rotor.

Abstract: A Savonius vertical axis wind turbine rotor has first and second curved vanes having remote substantially vertical edges widely spaced form each other, and proximate substantially vertical edges more closely horizontally spaced from each other and horizontally overlapping are associated with a substantially vertical central shaft construction. The shaft construction is operatively connected to the vanes and mounts the vanes and adjacent the proximate edges. The central shaft construction may comprise a perforated shaft (e.g. a single perforated shaft), or multiple shafts. In any event, the shaft construction, and mounting of the rotor vanes, allow, during use, spillover of wind from the proximate edge of one vane to another vane during powered rotation of the vanes in response to wind. The rotor is preferably omni-directional. The rotor may have a third set of vanes, and different vertically spaced sets of vanes circumferentially offset with respect to each other.

Abstract: A Savonius vertical axis wind turbine rotor has at least three spokes, at least two vanes, and fasteners. Each spoke includes a hub with central opening and arcuate ribs integral with the hub and extending radially outwardly. Channels are defined in at least one surface of each rib. Vanes of sheet material generally conform to an inner or outer surface of the ribs and have openings aligned with the channels. First fasteners pass through the openings into the channels and cooperate with second fasteners provided within the channels. Each hub may define a clamp which cooperates with a shaft, the clamp including a radial slot in the hub communicating with the central opening and fastener receiving elements on opposite sides of the slot. The vanes may overlap the central opening so that there is spillover from one vane to the next when the rotor is rotated by the wind.

Abstract: New aerodynamically improved rotors for use in vertical axis wind turbine (VAWTs) are disclosed. In some examples, the VAWT rotors include one or more blades with an aerodynamic front shape with low drag coefficient and a blunt or concave back shape that effectively catches the wind. Example rotors can be used by themselves or in conjunction with vertically attached rotating airfoils. The new rotors add to the overall energy production while acting as supports for the vertical airfoils. Furthermore, the new rotors provide energy in low wind speed conditions where the vertical airfoils are ineffective and can act as jump starters for the vertical airfoils. Guy wire structures for stabilizing VAWTs are also disclosed. The structures allow for reduced construction costs for a given tower height compared to conventional HAWTs and allows for taller towers for a given construction cost.

Abstract: A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.

Abstract: The blades of a turbomachine comprise airfoils, which are bent such that the lean angle (?), defined as the angle which the stacking line of the airfoil includes with the radial direction, and measured in the direction of rotation (?), is variable along the width of the flow channel and decreases from the hub towards the housing.

Abstract: A process for adjusting a throat area (the flow capacity) between airfoils in an airfoil configuration such as a stator ring used in a small gas turbine engine. The airfoils are designed with an over-extending trailing edge forming a throat area sized such that a worst case tolerances design flow area would be achieved. A fluid with a flow rate representing the actual fluid for normal operation in the airfoil configuration is passed through the airfoil throats and the flow rate is measured. A specified portion of the leading edge of each airfoil is removed until the design flow rate through the airfoil configuration is achieved. A plurality of iterations of measuring flow rates and removing trailing edge material is performed until the design flow rate is achieved.

Abstract: An improved rotor blade used in combination with a submersible electrical generator comprises a rotor base with width W, 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(W). A straight line drawn from the front of the base to the lip forms a forty five degree angle with respect to the rotor base. The rotor blade is 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 thereby generating electricity.

Abstract: Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z? set forth Table I wherein X and Y values are in inches and the Z? values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z? values by the height of the airfoil in inches and adding the radius of the airfoil base. The X and Y values are distances which, when connected by smooth continuing arcs, 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. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelope of +/?0.0.060 inches in directions normal to the surface of the airfoil.

Abstract: The invention concerns a rotor blade of a wind power installation and a wind power installation. One advantage of the present invention is to provide a rotor blade having a rotor blade profile, and a wind power installation, which has better efficiency than hitherto. A rotor blade of a wind power installation, wherein the rotor blade has a thickness reserve approximately in the range of between 15% and 40%, preferably in the range of between about 23% and 28%, and wherein the greatest profile thickness is between about 20% and 45%, preferably between about 32% and 36%.

Abstract: A turbine includes a stack of substantially parallel disks, the rotation of which causes rotation of a shaft. The disks are separated by peripheral spacers, each peripheral spacer having the shape of an airfoil. Each peripheral spacer defines a chord which is angled radially inward, towards the axis of rotation of the disk. The peripheral spacers are located only in the vicinity of the periphery of the disk. Air, or other fluid, entering the turbine engages the airfoil shaped peripheral spacers, and the flow of air generates lift, and associated drag, causing the energy of the fluid to be more efficiently converted into mechanical, and ultimately, electrical power. The turbine is especially useful in harnessing wind energy for the generation of electric power.

Abstract: A high-lift airfoil embodying a combination of loading conventions in a single design specifically to reduce and control total pressure losses that occur in the flow channels between airfoils employed in turbomachinery applications is disclosed herein. The mixed-loading high-lift airfoil designs embody and exhibit the best total profile and secondary loss characteristics possessed by both aft-loaded airfoil and front-loaded airfoil conventions through controlling the development and interaction of boundary layers forming along the surfaces of the airfoils and the endwalls in such applications. The mixed-loading high-lift airfoil may be utilized in both rotating and non-rotating turbomachinery applications.

Abstract: A process of designing a transonic airfoil that results in an exit deviation angle that is optimized to minimize downstream shock induced flowfield disturbances. Specifically, a design process of a transonic airfoil minimizes pitchwise variation in downstream static pressure that includes determining an airfoil exit deviation angle and downstream turning for reduced shock from a trailing edge of the transonic airfoil.

Abstract: A Francis pump-turbine includes a runner provided with runner blades arranged around in a circumferential direction of a main shaft of the runner, each of the runner blades being supported by a band at a bottom side thereof in a blade height direction and supported by a crown at a head side in the blade height direction, in which the runner blade is formed, at a trailing edge thereof, with a curved portion expanding to the main shaft when the turbine is in operation, the curved portion has a maximum point with respect to a straight line connecting a crown-side trailing edge connecting end at which the trailing edge and the crown are connected and a band-side trailing edge connecting end at which the trailing edge and the band are connected, and an angle ? formed by a straight line connecting the maximum point and the crown-side trailing edge connecting end and a straight line connecting the maximum point and the band-side trailing edge connecting end is set to be within a range of ??150°.

Abstract: The Dual Zone Amplifier Turbine Blade is for use on a vertical axis wind turbine. It is a 40 degree conic with a three sided opening at the base region for wind collection. The 40 degree conic turbine blade allows for amplification of collected wind and minimum air resistance to foreword movement. The curved, three sided opening at the base region allows for maximum collection of wind. When attached to a spoked hub in balanced plurality for the purpose of turning an electric generator or other device, an efficient collection, amplification and transfer of wind energy is attained.

Abstract: A turbo fan includes a plurality of blades positioned vertically in a radial direction between a main plate and a shroud. Each of the plurality of blades is formed with a slope at an outer periphery thereof to suppress generation of turbulence.

Abstract: A fan blade comprises a root portion and an aerofoil portion. The aerofoil portion has a leading edge, a trailing edge and a tip remote from the root portion. A concave pressure surface extends from the leading edge to the trailing edge and a convex suction surface extends from the leading edge to the trailing edge. A portion of the tip of the aerofoil portion between the leading edge and the trailing edge of the aerofoil portion is thinner than the remainder of the tip. The portion of the tip of the aerofoil portion is spaced from the leading edge and is spaced from the trailing edge. The portion of the tip of the aerofoil portion has a recess such that the portion of the tip of the aerofoil portion is thinner than the remainder of the tip. The recess is arranged on the concave pressure surface of the aerofoil portion. This reduces vibrations of the fan blade.

Abstract: A wind power engine including a stator having stator blades and a rotor having rotor blades. The rotor is positioned inside the hollow area of the stator and is rotationally movable with respect to the stator about an axis of rotation. The stator blades are positioned in such a way that an air flow coming from the outside of the stator is oriented towards the rotor and the rotor blades. The oriented airflow allows the rotor blades to drive the rotor about the axis of rotation. At least certain rotor blades have a concave-shaped profile on one of their faces.

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: The present invention provides an airfoil for a third stage blade having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract: Conventional large area fans generally create a cylinder of air having a diameter that is essentially equal to the diameter of the fan. Larger diameter fans require heavier-duty motors and gearboxes to drive the longer fan blades and are heavier, and thus are more difficult to mount, require heavier-duty mounting fixtures, and are more likely to fall. One large area fan according to this invention forms a cone of air. Some fan blades according to this invention have a relatively straight leading edge portion attached to the fan and a generally curved trailing portion extending downwardly from the relatively straight leading edge portion that interacts with the air to create a conical or cone-shaped flow of air from the fan. Other fan blades have a curved segment and are attached to the fan at theirs leading edges. In some such fan blades, one end is offset from the other end.

Abstract: In a multi-blade fan for an air-cooled engine, by defining the inlet angle ?1 and the angle ??2 to make the sum thereof less than 80° (preferably defining ?1 as 32° and ??2 as 36°), the multi-blade fan achieves greater air volume than in the case where the sum is made 80° or greater, where ?1 is the angle between the relative velocity direction and the peripheral direction on the inlet side of the blades, ?2 is the angle between the relative velocity direction and the peripheral direction on the outlet side of the blades, and ??2 is the difference obtained by subtracting ?2 from 180°. The number of blades can therefore be reduced to realize lower noise level while still maintaining the same air volume as the prior art multi-blade fan.

Abstract: The present invention provides an airfoil for a first stage nozzle guide vane having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract: A blade is disclosed for use in a wind turbine, with the blade having a longitudinal axis for extending radially outwardly from a center of rotation of the blade on the wind turbine. The blade has a front side with a front surface for orienting in a windward direction and a rear side with a rear surface for orienting in a leeward direction. The blade has a profile taken in a plane oriented substantially perpendicular to the longitudinal axis of the blade. The profile of the blade has a leading edge and a trailing edge. The profile is characterized by a camber ratio, and the camber ratio of the profile is greater than or equal to approximately 4%.

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 blade is disclosed for use in a wind turbine, with the blade having a longitudinal axis for extending radially outwardly from a center of rotation of the blade on the wind turbine. The blade has a front side with a front surface for orienting in a windward direction and a rear side with a rear surface for orienting in a leeward direction. The blade has a profile taken in a plane oriented substantially perpendicular to the longitudinal axis of the blade. The profile of the blade has a leading edge and a trailing edge. The profile is characterized by a camber ratio, and the camber ratio of the profile is greater than or equal to approximately 4%.

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: A rotor that consists of a central hub or shaft and a plurality of boot shaped integral blade/vane units that combine a pronounced elongated vane tip extending substantially toward the incoming flow and also the direction of rotation forming a helix or pitch angle to the rotation axis centerline, preferably normal to and joined to the outer frontward extremity of a slightly rearward tilted blade/wing section that is connected by its inner end to the central hub or shaft. The rotor revolves about the rotation axis by incoming gas/fluid flow as most of the fluid flow is encouraged to move substantially outward and rearward as it travels into and past the forwardly projecting vane tips located a substantial distance radially from the axis of rotation. This maximizes the torque developed and transferred to the hub/shaft in a manner that does not greatly inhibit total through flow.

Abstract: A first bent portion bent toward an intrados and a second bent portion located in the rear of the first bent portion and bent toward an extrados are provided on a camber line on a trailing edge in the rear of 90% of a chord length of a turbine blade having an extremely low aspect ratio for an axial-flow turbine. The inclination of the camber line immediately in the rear of the second bent portion on the side of a blade root is substantially equal to the inclination of the camber line immediately in front of the first bent portion, and the curvature of the second bent portion is decreased from the side of the blade root toward a blade tip. As a result, a higher-pressure portion on the intrados which is a pressure surface of the turbine blade is displaced toward the trailing edge, and thus a secondary flow from the side of the blade tip toward the blade root can be suppressed, whereby a pressure loss particularly in the vicinity of the blade root can be suppressed to the minimum.

Abstract: A wind turbine is provided which comprises a plurality of blades and a single venturi disposed at a central area of the plurality of blades. The single venturi redirects the wind from a concave side of an active blade to the concave sides of the other blades. Also, the single venturi reduces turbulent flow of air out of the venturi and redirects the flow of air against the adjacent blades.

Abstract: A rotor for a wind power plant for mounting on a building, especially with a vertical rotational axis, comprising a rotor hub and at least one rotor blade, with the rotor blade being arranged to cover the whole surface area and having a substantially rectangular shape, comprising a radially inwardly disposed edge, a radially outwardly disposed edge, a radially extending bottom edge and a radially extending upper edge, with said rotor blade being provided with a twisted arrangement in a spiral fashion about the rotor hub, starting from its bottom edge in the direction of its upper edge. Furthermore, a wind power plant with such a rotor.

Abstract: A turbine blade system including a blade airfoil having an airfoil shape with the blade airfoil having a nominal profile substantially in accordance with normalized Cartesian coordinate values Z set forth in a table 1 below and which values are dimensionless values that are convertible to corresponding absolute distance values that define nominal airfoil profile sections and which, when joined smoothly with adjacent ones thereof, form a complete nominal airfoil shape that is substantially matched by the airfoil shape of the blade airfoil. This blade airfoil can be supported on a ring platform having a support surface with a support surface shape in the vicinity of the location at which that blade airfoil is supported thereon formed in a similar manner.

Abstract: The invention relates to a method and apparatus for gradually converting marine wave energy into electricity. The energy reserve provided by wind power holds enough energy for the needs of the entire mankind. The invention provides an efficient means of putting this energy reserve to practical use. Mounted on a rotating power shaft is a pair of form parts, the convex and concave shape, especially the round-pointed open V-shape of which reverses its orientation by 180 degrees, i.e. turns from convex to concave, whenever the power shaft makes a rotation of 180 degrees. The circular motion of water occurring in a wave drives such a turbine effectively while the wave dies out. The pair of convex and concave form parts extends helically around the power shaft, whereby water currents in all directions, which come to contact with the pair of form parts, produce a rotative moment.

Abstract: An impeller rotatable in a direction of rotation in a centrifugal compressor including an intake ring. The impeller includes a back plate having a shaft portion and a plurality of blades. Each blade extends from the back plate and includes an inducer portion adapted to draw fluid into the impeller and including a leading edge and an exducer portion adapted to discharge the fluid from the impeller and including a trailing edge. A blade pressure side is defined between the leading edge, the trailing edge, the back plate, and a blade tip. The pressure side is convex from the back plate to the blade tip. A blade suction side opposite the pressure side is defined between the leading edge, the trailing edge, the back plate, and the blade tip. The suction side being concave from the back plate to the blade tip.

Abstract: A fan with supercharging device has a hub and fan blades. A hub has a shape similar to a cone with a tip end and a circumferential side. The fan blades extend radially from the circumferential side of the hub. Each of the fan blades has a joining end being attached to the circumferential side, a free end extending outward the hub and a front edge and a rear edge being between the joining end and the free end respectively. The rear edge of the respective fan blade is shielded by the front edge of another fan blade next to it. The unshielded portion of the respective fan blade has an area gradually increases from the joining end to the free end. A projection is disposed at the free end along a direction of fluid flow. Hence, fluid pressure is capable of increasing significantly while the fan is in operation.

Abstract: A blade is disclosed for use in a wind turbine, with the blade having a longitudinal axis for extending radially outwardly from a center of rotation of the blade on the wind turbine. The blade has a front side with a front surface for orienting in a windward direction and a rear side with a rear surface for orienting in a leeward direction. The blade has a profile taken in a plane oriented substantially perpendicular to the longitudinal axis of the blade. The profile of the blade has a leading edge and a trailing edge. The profile is characterized by a camber ratio, and the camber ratio of the profile is greater than or equal to approximately 4%.

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 1. 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: 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 1. 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: An undershot waterwheel is described. The waterwheel has a rotational axis and paddles rotatable about the rotational axis. At least one paddle comprises a blade that is curved when viewed parallel to the rotational axis. Optionally, the waterwheel may be mounted on a watercraft.

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 1. 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: 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 1. 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: Blade (1) of a rotor for a first phase of a gas turbine having a profile identified by means of a series of closed intersection curves (20) between the profile itself and planes (X,Y) lying at distances (Z) from the central axis, each closed curve (20) has a first rounded end (21) and a second rounded end (22), which connect the trace of the first surface (3) with the trace of the second surface (5) in depression, the first end (21) first meets a gas flow of the turbine, each closed curve (20) has an axial chord (40) defined as the maximum distance of the first end (21) from the second end (22) along the axis (X), each closed curve (20) has a thickness (30) of the first end (21) defined as the maximum diameter of the circle inscribed in the first end (21); said dimensionless thickness (30), i.e. divided by the axial chord (40), has a quadric distribution according to a curve of the fourth order along the axis (Z).

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 1. 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.