Abstract: A coupling system for coupling a curved object to a central shaft, the curved object includes an inner surface facing the central shaft and an outer surface. The system includes a coupling member for coupling the curved object to the central shaft; at least one pocket integrally formed on a curved surface of the curved object and defined as a depression with respect to at least one of the inner and outer surfaces. The pocket includes: a flat portion having an aperture for holding the coupling member; and a flange portion which merges continuously from the flat portion to the curved object and is shaped such that the flat portion is disposed perpendicularly to the coupling member; a fastening member for fastening the coupling member to the flat portion. The thickness of the flat portion and flange portion is the thickness of the curved object.

Abstract: A savonius wind turbine including a rotational shaft and a compound blade operatively coupled to the rotational shaft is provided. The compound blade includes a primary blade portion and a secondary blade portion. The primary blade portion extends between a first end and a second end and defines a primary concave surface therebetween. The secondary blade portion is coupled to the primary blade portion between the first end and the second end. The secondary blade portion defines a secondary concave surface configured to generate a torque about the rotational shaft.

Abstract: A device includes a hub and a blade. The hub has a cylindrical geometry. The blade extends radially from the hub. The blade has a helical structure. The blade includes a leading edge, a winglet, a trailing edge, and a trough. The leading edge is formed on the blade and has an arcuate geometry. The winglet of the blade is distal relative to the hub. The winglet angles away from a surface of the blade. The trailing edge is formed on the blade to be opposite the leading edge. At least a portion of the trailing edge forms a pitch-line cup that is angled with respect to the surface of the blade. The trough is formed in a transition between the pitch-line cup of the trailing edge and the winglet. The trough forms a recess that is relatively closer to the surface of the blade.

Abstract: A rotor blade for a wind power installation, which extends in a longitudinal direction with a profile course from a blade connector to a blade tip, wherein the profile course contains at least one profile, comprising: a suction side and a pressure side, a relative profile thickness of greater than 25%, a profile chord, which extends between a leading edge and a trailing edge of the profile and has a length which defines the profile depth, a mean line which extends at least partially below the profile chord, a convex region which extends on the suction side from the trailing edge, and a convex region which extends on the pressure side from the trailing edge, wherein the convex region on the pressure side defines a rounded transition region of the pressure side to the trailing edge.

Abstract: A blower includes: an outside/inside air box into which outside air and inside air are introduced; an impeller to suck and blow out air introduced into the air box; a casing having a bell mouth that forms an air suction port to the impeller, the casing forming a ventilation passage on an outer side of the impeller in a radial direction; and a plate-shaped member provided with a predetermined gap relative to the casing and the bell mouth. A gap passage is defined between the casing and the plate-shaped member. A guide rib is provided at a part of the gap passage opposite to an opening through which air flows into the gap passage. The guide rib guides air flowing through the gap passage in a circumferential direction of the bell mouth.

Abstract: A propeller fan includes a hub, and a plurality of wings provided at an outer circumference of the hub. Each of the wings includes a protrusion tapered and positioned on a rotation direction rear side in a radially outer portion of the wing, the protrusion includes a top positioned at a rearmost end in the rotation direction, an outer circumferential rear edge positioned radially outside the top, and an inner circumferential rear edge positioned radially inside the top, the outer circumferential rear edge includes a first serration having a first serration shape, and the inner circumferential rear edge includes a second serration having a second serration shape.

Abstract: A turbocharger includes: a mixed flow turbine including a turbine wheel; a turbine housing configured to house the turbine wheel, including a gas passage extending toward a leading edge of a blade of the turbine wheel; and nozzle vanes arranged in the gas passage in the circumferential direction of the turbine wheel, mutually adjacent two of the nozzle vanes forming a throat therebetween. Each nozzle vane is twisted with respect to a trailing edge of the nozzle vane as a twist center such that a width of the throat becomes narrower on the shroud side than on the hub side.

Abstract: A transonic compressor of a turbomachine comprising exactly two or exactly three annular rows of rotor blades and respectively exactly one or exactly two annular rows of intermediate stator vanes interposed between two respective rows of rotor blades, wherein the flow velocity relative to the rotor downstream of the intermediate stator vanes is less than or equal to a Mach number of 0.9 over a radial portion of the blades extending over the radially inner 40% of the blades, and less than or equal to a Mach number of 1 over a radial portion extending over the radially inner 80% of the blades, and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outer 20% of the blades.

Abstract: Fan assemblies are disclosed. Fan assemblies include an impeller with asymmetric design. For example, an impeller may include a first set of blades with one geometry and second set of fan blades with another geometry. This enables a dual-inlet centrifugal fan to generate different air flow performance characteristics for the air entering one fan inlet compared to the air entering the other fan inlet. The impeller, with different fan blade configurations, can better handle air flow entering the fan assembly through different inlets, particularly when the air flow conditions differ through the inlets due to impeding structures (e.g., motor, struts, etc.). As a result, air flow distribution from air leaving the impeller, including the locations associated with the different fan blade configurations, is relatively uniform. Beneficially, when air flow distribution uniformity increases, the fan assembly operates more efficiently, as air flow pressure losses due to flow separation are mitigated.

Abstract: A rotor blade of a wind turbine, wherein the rotor blade has in particular a splitter plate, which is arranged on the blunt trailing edge of the rotor blade. The splitter plate comprises: a root edge, wherein the root edge is arranged on, in particular along, the trailing edge below a transition from the suction side into the trailing edge, an end edge, wherein the end edge forms a free edge, and a surface between the root edge and the end edge, wherein the surface has at least one curved part between the root edge and the end edge, and at least one part of the surface lies in the shear layer generated by the suction side. A rotor blade of a wind turbine, wherein the rotor blade has in particular a splitter plate, which is arranged on the blunt trailing edge of the rotor blade.

Abstract: A fan frame with an improved heat dissipation performance includes a frame body, a plurality of stationary blades, and a central base. The frame body defines a flow channel, the central base is arranged within the flow channel and divides the flow channel into flowing zones. Each of the flowing zone includes a high-pressure zone and a low-pressure zone. The central base defines first slot, second slot and receiving groove between the first slot and the second slot, the first slot communicates the high-pressure zone and the receiving groove, the second slot communicates the low-pressure zone and the receiving groove.

Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in one of TABLE I or TABLE II. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at a base of the airfoil. The Cartesian coordinate values of X, Y, and Z are non-dimensional values that are convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

Abstract: A gas turbine engine generates noise during use, and one particularly important flight condition for noise generation is take-off. A gas turbine engine that has high efficiency provides low noise, in particular from the fan and the turbine that drives the fan. Values are defined for a noise parameter NP that results in a gas turbine engine having reduced combined fan and turbine noise.

Abstract: A directed thrust propulsion system has a central hub and at least three blades that extends outward at a rake angle between about 20 to 70 degrees. Each blade is shaped as a portion of a cylindrical surface, in which concave side forms the blade face and is facing in direction of thrust generated by rotating the hub. The convex side of the blades minimizes drag in the water that resists forward motion while the concave shape and tilted end portions directs the thrust inward toward the extension of the hub's principal axis rearward. The directed thrust propulsion system may be deployed on inboard and outboard motors for all manner of watercraft to increase efficiency above 10 knots speed.

Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location.

Abstract: Various embodiments of the disclosure include turbine blades and systems employing such blades. Various embodiments include a turbine blade having: an airfoil having an airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each distance Z along at least a portion of the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the nominal profile.

Abstract: A gas turbine engine generates noise during use, and one particularly important flight condition for noise generation is take-off. A gas turbine engine that has high efficiency provides low noise, in particular from the fan and the turbine that drives the fan. Values are defined for a noise parameter NP that results in a gas turbine engine having reduced combined fan and turbine noise.

Abstract: A cross flow fan blade includes an inner edge disposed on an inner circumferential side of a cross flow fan, an outer edge disposed on an outer circumferential side of the cross flow fan, and a base part formed between the inner edge and the outer edge. The base part has a pressure face and a negative pressure face. A thickness of the inner edge is larger than 1.5 times a thickness of the outer edge. An interval between the pressure face and the negative pressure face in a direction perpendicular to the pressure face is a thickness of the base part. A maximum thickness position of the base part is closer to the inner edge than to the outer edge. When a blade chord length is L and a maximum thickness of the base part is tmax, tmax/L?0.094, and a range of tmax/L?0.08 is excluded.

Abstract: A turbine blade for a rotary machine includes an airfoil that extends from a root to a tip along a radial span. The airfoil further includes a first sidewall and a second sidewall that are coupled together at a leading edge of the airfoil and that extend aftward to a trailing edge of the airfoil. One of the first sidewall or the second sidewall includes a tip region having an increased stagger angle that produces a non-linear, over-hanging trailing edge.

Abstract: An outlet guide vane for an axial compressor extending along a rotor axis, includes an airfoil extending in a span direction from a radially inner end at 0% height to a radially outer end at 0% height. The airfoil has a suction side and an opposite pressure side, both sides extending in a chord direction from a leading edge to a trailing edge, wherein for each profile of the airfoil a stagger angle between the chord and the rotor axis is defined. A more favorable air flow profile behind the outlet guide vane is achieved by a new shape of the outlet guide vane, wherein a stagger angle distribution in the span direction has a curved course having a minimum located between 40% and 60% in the span direction, a first maximum at 0% and a second maximum at 100% in the span direction.

Abstract: A rotor blade includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

Abstract: A method for operating a wind turbine power system connected to an electrical grid includes collecting data relating to one or more parameters of one or more electrical components of the wind turbine power system. The method may also include performing a statistical analysis of the data relating to one or more parameters of the one or more electrical components. Further, the method includes predicting future behavior of the electrical component(s) based on the statistical analysis. Moreover, the method includes determining set points for the electrical component(s) using the predicted future behavior. In addition, the method includes operating the wind turbine power system at the determined set points for the electrical component(s) so as to optimize at least one characteristic of the electrical component(s).

Abstract: A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section has an array of twenty-six or fewer fan blades. The low pressure compressor is downstream from the fan section. An airfoil is provided in the compressor section outside the high pressure compressor section and includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with the stagger angle greater than 35° from 0% span to at least 50% span. The stagger angle has a positive slope from 20% span to 100% span.

Abstract: A cantilevered vane, for use with a rotary disc of a gas turbine, includes a root supported in a dovetail slot formed in a circumferential surface of the rotary disc; and an airfoil protruding a predetermined height from the root and having a J-shaped cross-section throughout a front-wing portion and a rear-wing portion of the airfoil. The airfoil includes a straight portion vertically extending upward from the root by a predetermined height; and a curved portion integrally formed with an upper end of the straight portion to cantilever toward one side of the airfoil, the curved portion being inclined at a predetermined angle with respect to the straight portion. Cooling fluid flows through a first channel formed in the straight portion and a second channel formed in the curved portion. The first channel includes front-wing and rear-wing channels for guiding the cooling fluid to the front-wing and rear-wing portions.

Abstract: A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

Abstract: Suction surfaces of blades of this radial turbine each have: a leading edge side of blade tip including a leading edge and the boundary between the suction surface and the tip; and a trailing edge side of blade tip including a trailing edge and the boundary between the suction surface and the tip. The leading edge side of blade tip forms a concave curved surface which is recessed towards the side opposite to the rotation side in a radial view. The trailing edge side of blade tip forms a convex curved surface which protrudes towards the rotation side in a radial view.

Abstract: A modified J-type cantilevered vane reduces rubbing of an airfoil and enhances the vibration stability of a vane hub and the fluidity of fluid. The cantilevered vane includes a root attachment inserted into a slot formed in an inner circumferential surface of a casing of a gas turbine, and an airfoil vertically extending from the root attachment to a predetermined height. The airfoil includes a linear part extending in a radial direction from the inner circumferential surface of the casing toward a rotating shaft of the gas turbine, and a curved part integrally formed with the linear part, the curved part including a bend beginning from one end of the linear part and curving in a circumferential direction of the rotating shaft. Overall, the linear part and the curved part are biased in the circumferential direction, since the airfoil has a J-shaped X-axis profile and a C-shaped Y-axis profile.

Abstract: A turbine nozzle having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: Disclosed is a blade/vane cascade segment of a blade/vane cascade of a turbomachine, which comprises at least two blade/vane elements defining an axial cascade width, and a stage with a stage surface, as well as a stage edge on the inflow side. The stage surface has an elevation extending up to the pressure side of a first blade/vane element and a depression extending up to the suction side of the other blade/vane. At least one highest point of the elevation and at least one lowest point of the depression each lie at least 30% and at most 60% of the axial cascade width downstream of the inflow edges of the blade/vane elements. In this case, the elevation and the depression each come close to the stage edge on the inflow side.

Abstract: A floating wind turbine assembly, configured to self-stabilize in water without a fixed anchor. The floating wind turbine assembly has a wind turbine, joined to a turbine shaft. A beam anchor is joined to the turbine shaft. A hollow moving mass, arranged around the beam anchor, such that the hollow moving mass can be moved up or down the beam anchor. The hollow moving mass includes a pump, having a pump first end connected to the water with a first pump hose and a pump second end arranged within the hollow moving mass with a second pump hose.

Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Abstract: A continuously variable transmission cooling fan includes a moveable sheave cover attached to a drive clutch assembly of a continuously variable transmission, with a plurality of fan blades molded into the moveable sheave cover and arranged around the perimeter of the moveable sheave cover. Each fan blade may have a different length, curvature and angle of position than the adjacent fan blades. The continuously variable transmission cooling fan also may include a plurality of openings in the moveable sheave cover located radially inwardly from the fan blades.

Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.

Abstract: A turbine engine blade having a plurality of blade sections stacked along a radial axis between a root and a tip. Each section extends along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between a pressure-side face and a suction-side face. Each section presents a camber line, a deviation defined for each section as the difference between an angle between the tangent to the camber line at the leading edge and the longitudinal axis, and an angle between the tangent to the camber line at the trailing edge and the longitudinal axis. The minimum deviation is at the root of the blade, and the maximum deviation is present at sections situated in the range 0.3H to 0.8H, where H is the height of the blade measured from its root to its tip.

Abstract: A radial compressor has at least one compressor stage. The compressor stage includes: an impeller having moving blades on a rotor side arranged in a flow channel of the compressor stage. The flow channel is bounded by a hub contour and a housing contour or cover disc contour. Each moving blade has a flow inlet edge and a flow outlet edge. In the region of the compressor stage on the hub contour of the flow channel, initially a curvature change from a first concave curvature into a convex curvature and following this a curvature change from the convex curvature into a second concave curvature is formed; and/or on the housing contour or cover disc contour of the flow channel, initially a curvature change from a first convex curvature into a concave curvature and following this a curvature change from the concave curvature into a second convex curvature is formed.

Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.

Abstract: A turbomachine blade with a localized dihedral feature has a high order polynomial shaped curve region.

Abstract: A blade (1) for a tail anti-torque device of a helicopter, said device comprising a ducted rotor (13). The blade (1) has an assembly of sections, a leading edge (2) and a trailing edge (3); a stacking line (4) of the profiles extending at a distance lying in the range 25% to 50% of the chord (C). The stacking line (4) presents a shape that is curved having successively from the root (5) to the end (6) of the blade a back sweep, a forward sweep, and a last back sweep; and a chord (C) that becomes larger going towards the end (6) of the blade (1) over at least the end profile (1a).

Abstract: A turbine vane for a gas turbine engine with an airfoil portion including a perimeter wall having first, second, and third sets of cooling holes defined therethrough, including the holes numbered HA-1 to HA-13, HB-1 to HB-13 and PA-1 to PA-9, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.

Abstract: A universal spherical reaction turbine for any flowing fluid at any depths or elevation that is capable of unidirectional rotation under reversible flow conditions. The turbine includes a rotatable shaft that is adapted to rotate about an axis of rotation; turbine blade support members that are fixedly attached to the rotatable shaft and a plurality of meridian turbine blades. The meridian turbine blades are fixedly attached to diametrically-opposite points that define a geometrical north-south meridian axis that is oriented at a skew angle to the axis of rotation of the rotatable shaft. The skew angle is greater than zero and less than 180 degrees, and, more preferably, between 25 and 35 degrees. The skewing ensures that those turbine blades that are attached to the diametrically-opposite points move on a helical trajectory with respect to the axis of 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: The impeller wheel is rotatably supported about a central axis and has a hub on which vanes are arranged. The vane has across its radial length at least similar profiled sections, viewed in cylindrical section through the vane. The radial outermost profiled section which is positioned on a cylindrical enveloping surface of the impeller wheel has a greater displacement relative to the neighboring profiled section than this neighboring profiled section to its neighboring profiled section. The impeller wheel can also be provided on the radial outer edge with at least one projecting flow element whose axial height has a maximum in the area of the leading edge and of the trailing edge of the vane. The impeller wheels, while having a simple constructive configuration, provide a great noise reduction in operation of the ventilator.

Abstract: A compressor blade for an axially permeated compressor, preferably of a stationary gas turbine is provided. The camber line of the blade tip side profile of the blade of the compressor blade includes at least two inflection points for reducing radial gap losses. By means of two inflection points, there is a concavely designed suction side contour segment in a segment from 35% to 50% for the suction side contour, and a convexly implemented pressure side contour segment for the pressure side contour. It is possible by means of the geometry to generate low-loss gap vortices, in order to increase the overall efficiency of an axial compressor including the compressor blades.

Abstract: A wind turbine comprising a drive shaft; at least one vane connected to the drive shaft; and a torque converter attached to the vane, the torque converter comprising an airfoil, the torque converter being adapted to capture air for use in aiding the vane to rotate. Certain embodiments include the vane comprising a first surface and a second surface positioned opposite to the first surface, the first surface comprising a plurality of wind disrupters. Certain embodiments include a plurality of vanes rotatably connected to the drive shaft, the plurality of vanes comprising a plurality of strakes adapted to capture air and direct air to the drive shaft. Yet certain embodiments include a first air scoop connected to the vane, the first air scoop comprising a first air scoop portion at an angle relative to the vane.

Abstract: A wind/water turbine has a basic configuration in which both ends of blades which are in rotational symmetry are fixed to support plates, the blades have vanes, one of the vertical sides of the vanes is attached to a vane rotating shaft, and the free opposite sides each rotate freely in a sector extending as far as the adjacent vane rotating shafts on either side. The vanes are arranged such that when the blades of the wind/water turbine are convex, moving against the water flow/airflow, the vanes are pressed by the water flow/airflow and are opened, thereby reducing the rotational resistance, and when the blades have pivoted further and are concave, the spaces between the vane rotating shafts are closed, the water/air pressure is received over the entire surface of the blade, and thus a pivoting force that is increased corresponding to the reduction in rotation resistance is obtained.

Abstract: A blade row for a turbomachine is disclosed. The blade row has an inner lateral wall and an outer lateral wall for bordering a hot gas channel in the turbomachine through which hot gas passes. At least one of the lateral walls has a rounded lateral wall front edge, which is provided with a circumferentially asymmetrical edge contouring that is elliptical or is comprised of one or more segments of a circle.

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

Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.