Abstract: When cold and in the uncoated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X, Y, Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance from the point in question to a reference plane P0 situated at the base of the nominal profile and H is the height of this profile, measured from the reference plane to the tip of the blade. The measurements D and H are taken radially relative to the axis of the turbine, while the coordinate X is measured in the axial direction of the turbine.

Abstract: A method of manufacturing an aerofoil structure capable of being diffusion bonded and superplastically formed to create a substantially hollow cavity within the aerofoil structure, the method comprising: providing a metallic plate for forming the aerofoil structure; joining mounting elements to opposing end surfaces of said metallic plate; dividing said plate along a plane extending substantially in a span-wise direction so as to produce two metallic panels each with one of said mounting elements joined thereto; assembling the two metallic panels so that the surfaces of the panels opposite to the surfaces which have been divided are facing each other; and joining the two metallic panels to one another to form the aerofoil structure; wherein the mounting elements are joined to one another to form the root of the aerofoil.

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 fluid energy conversion device comprising a plurality of adjacent fluid catching modules that may be disposed about a central drive shaft, wherein the central drive shaft may be rotatably secured to a support frame. Each of the plurality of adjacent fluid catching modules may comprise two intake elements having a first fluid capturing aperture, an overlap portion, and a second fluid capturing aperture facing a direction opposite to that of the first fluid catching aperture. Adjacent fluid catching modules may be offset from each other by a predetermined angular position, thus allowing for at least one fluid catching aperture to be facing a directional fluid energy source at all times. The plurality of fluid catching modules may comprise different widths and form an overall conical configuration or the plurality of fluid catching modules may comprise equivalent widths and form an overall cylindrical configuration.

Abstract: A system including an airfoil portion of an unshrouded turbine bucket, which includes a pressure-side surface and suction-side surface each extending from a root surface to a tip surface and joined at a leading edge and a trailing edge, the pressure-side surface having a generally concave shape and the suction-side surface having a generally convex shape; the airfoil portion having an increasing stagger angle in a span-wise direction from the root surface to the tip surface and an increasingly loaded suction-side surface as the suction-side surface approaches the tip surface and the tip surface approaches the leading edge, the airfoil portion having a resultant lean in a direction of the suction-side surface as the leading edge approaches the tip surface, and the pressure-side surface and the suction-side surface each having a locally reduced or reversed curvature in a direction of the pressure-side surface at their intersection with the tip surface.

Abstract: A method of designing an airfoil for a gas turbine engine according to one embodiment of this disclosure can include localizing a sweep angle at a leading edge of a tip region of the airfoil, and localizing a dihedral angle at the tip region of the airfoil. The dihedral angle can be applied by translating the airfoil in direction normal to a chord of the airfoil.

Abstract: An all speed range propeller includes a propeller hub and plural propeller blades having their shafts symmetrically connected with the propeller hub. Each propeller blade is divided into a first region and a second region from the propeller hub to an outer end. The first region and the second region are different in wing structure, and the wing cross-sectional area of the second region is smaller than that of the first region. Thus, in speed ranges that common ships navigate most frequently, the all speed range propeller of this invention can lower the influence of cavitation produced because of different speed ranges, able to maintain high efficiency in use and prevent the efficiency of the propeller from lowered exceedingly.

Abstract: A windmill structure for converting wind energy to electrical energy comprises a thrust holding foundation having a plurality of holes for fixing the windmill structure on a ground surface. A tower consists of a bottom end and a top end. The bottom end of the tower is positioned at a middle portion of the foundation. A plurality of wind-engaging blades extended from the top end of the tower. A plurality of concave panels with larger surface area may be used as the plurality of wind-engaging blades. A plurality of supporting structures is utilized for attaching the plurality of wind-engaging blades on the top end of the tower and a power generator molded at one end of the tower. The arrangement of the plurality of wind-engaging blades facilitates to attain maximum rotation with minimal wind energy thereby increasing the overall efficiency of the windmill structure.

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: A fluid interface device, such as an airfoil assembly, can include a device structure and at least one moveable band oriented such that the band moves in a direction of fluid flow. The at least one moveable band can be supported on the device structure such that an outer surface of the moveable band is exposed along the device structure and is capable of movement relative thereto such that a relative velocity can be maintained between the outer surface and the device structure. The fluid interface device can have a cross section that includes first and second boundary layer collision points disposed along one side of the device structure with at least one of said first and second boundary layer collision points formed by the endless band. An airplane, a wind turbine and a method are also included.

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

Abstract: The disclosure provides blades, and the modification thereof, for stages 18-22 of an axial compressor wherein the blades have reduced susceptibility to tip cracking. The blades and blades manufactured by the provided method have a thickened profile that results in reduced stress in response to multi frequency impulses and can have increased frequency response of the chord wise bending mode.

Abstract: A centrifugal impeller includes a hub and a plurality of impeller blades extending from the hub. Each impeller blade extends over a chord length between a leading end and a trailing end, over a span from a root at the hub to a tip end and over a thickness between a convex side and a concave side. The blades collectively or individually have profiles that define a circumferential pitch (CP) with regard to a spacing distance between the leading ends of neighboring ones of the blades and blade angles at positions along the convex side of each blade between the leading end and the trailing end. The blades have a solidity value (S) defined as CD/CP that is less or equal to 1.0 and the blade angles (?) of each blade increase from the respective leading end to the corresponding trailing end.

Abstract: A free end of a blade of a fluid flow machine has a skeleton line camber distribution having an excessive value to a relative skeleton line camber of at least ?*=0.35 for a related running length of s*=0.1 in a blade profile flow line section between the free end and a blade section at 30% of a main flow path width from the free end. S* is a local running length relative to a total running length of the profile skeleton line and ?* is an angular change of the skeleton line relative to a total camber of the skeleton line from a leading edge to a related running length s*. The skeleton line camber distribution runs between leading edge point V (s*=0, ?*=0) and trailing edge point H (s*=1, ?*=1).

Abstract: It is intended to provide a wind turbine blade with superior aerodynamic characteristics and rigidity, a wind turbine generator equipped with the wind turbine blade, and a method of designing the wind turbine blade. The wind turbine blade 1 is provided with a blade tip part 2, a blade root part 4 connected to a hub 112, and an airfoil part 6 disposed between the blade tip part 2 and the blade root part 4. The airfoil part 6 includes a flatback airfoil 10 with a blunt trailing edge 8 at least in an area in a longitudinal direction of the wind turbine blade 1 where a blade thickness ratio X is 40% to 50%. X indicates a ratio of a maximum thickness tMAX to a chord length LC. In the area where the blade thickness ratio X is 40% to 50%, the flatback airfoil has a trailing edge thickness ratio Y which is 5% to YH%, Y indicating a ratio of a trailing edge thickness tTE to the maximum thickness tMAX and YH has a relationship of YH=1.5X?30 with the blade thickness ratio X.

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 marine propulsion assembly comprises or consists of a marine engine, a pair of parallel laterally spaced propeller shafts and a pair of marine propellers with one of the propeller fixed to each of the shafts for rotation. Each of the propellers includes a hub and four equally spaced blades and wherein the hub has a forward portion having the shape of a frustum of a cone with a decreasing radius from a forward edge thereof to the middle of the hub and a rear or second continuous portion having the shape of a frustum of a cone with an increasing radius from the middle of the hub to the rear of the hub. The bases or larger ends of the frustums are of equal size as are the tops of the frustums. In addition, each of the blades has a complex concave shape.

Abstract: An airfoil is provided and includes a pressure surface and a suction surface. Radially corresponding surface characteristics of the pressure and suction surfaces at a spanwise local portion of the airfoil are formed to cooperatively define at least one of a camber line and a thickness distribution plot of the airfoil as having a radius of curvature with at least two sign changes. The number of sign changes decreases along a radial dimension of the airfoil measured from the spanwise local portion.

Abstract: A blade for an axial-flow turbomachine with a gap-side blade area I which transits into a free blade end and with a hub-side or casing-side blade area II, respectively. Blade 3 forms a flow line profile section with leading edge VK and trailing edge HK which establish forward end point V and rearward end point H, respectively, by a tangent normal to and intersecting with the profile chord, with the distance between these end points being profile depth L. Blade 3 includes an enlargement of profile depth L at a tip of the free blade end which is at least +10 percent and decreases to zero in the blade central section, with the values being non-negative throughout, with the profile enlargement at trailing edge HK being larger than zero at the tip in the gap-side peripheral section.

Abstract: A propeller blade includes a body configured to extend radially from the hub of a propeller. The body can include a front surface, a back surface, a leading edge, and a trailing edge. The top of the body can form a tippet that generally transitions the front and back surfaces from extending in a generally radial direction to a generally axial direction. The tippet can reduce radial flow and force losses, redirect the radial flow in an axial direction, reduce the exit flow area of the propeller, and increase the inlet flow area of the propeller. The front surface of the blade can have a planar configuration that prevents or reduces the creation of low or negative pressure across the front surface of the blade and associated cavitation.

Abstract: A turbine bucket including an airfoil, the airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 as contained herein wherein the Z values are non-dimensional values from approximately 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by substantially smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined substantially smoothly with one another to form a complete airfoil shape.

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 novel airfoil design comprising a reactionary front face that pushes into the flow of air with a high angle of attack and a vacuum-producing face which forces the early separation of the flow of air from the top side of the airfoil, creating an area of high negative pressure which pulls upward, contributing to lift.

Abstract: A guide blade of a turbomachine, in particular of a compressor, a blade of the guide blade without an inner shroud having a flow inlet edge, a flow outlet edge, a suction side, and a pressure side. The blade is formed by a plurality of blade sections stacked one on top of the other in the radial direction, and the centers of gravity of the blade sections extend along a stacking axis. The blade sections are stacked one on top of the other in the radial direction in such a way that, in a radially inner section of the blade adjacent to a radially outer section of the blade, the stacking axis has its single inflection point in its radial curvature, namely, between a first, radially inner subsection of the radially inner section in which the stacking axis has a concave curvature toward the pressure side, and a second, radially outer subsection of the radially inner section in which the stacking axis has a concave curvature toward the suction side.

Abstract: A generally spherical turbine configured to rotate transversely within a cylindrical pipe under the power of fluid flowing either direction therethrough is operatively coupled with a rotating machine or generator to produce electricity. In one embodiment, the blades of the spherical turbine curve in an approximately 180 degree arc in a plane that is at an inclined angle relative to the rotational axis of a central shaft. In another embodiment, a deflector is provided upstream of the spherical turbine and within the cylindrical pipe to control flow through the spherical turbine by shielding a part thereof. The blades of the spherical turbine are airfoil in cross section to optimize hydrodynamic flow, to minimize cavitation, and to maximize conversion from axial to rotating energy.

Abstract: An enhanced pump assembly includes an impeller and volute casing designed to provide high operating pressures (“P”) and flow rates (“Q”) with low energy usage. The impeller has a central shaft carrying radially projecting curved primary vanes, and each primary vane also has a twist in the radial direction. Secondary impeller vanes define triangular connecting fillet-like wall segments connecting each primary vane to the impeller shaft. The casing of the pump has a slight spiral deviation so that the pump chamber's radial sidewall flares away from the swept area of the impeller's vanes to define a fluid outlet that contributes to higher P-Q performance, especially when pumping colder fluids.

Abstract: A centrifugal fan includes a plurality of fan blades arranged spaced apart from each other in a circumferential direction. The fan blade has an inner edge portion disposed on an inner peripheral side and an outer edge portion disposed on an outer peripheral side. The fan blade has a blade surface including a pressure surface and a suction surface. When cut along a plane orthogonal to a rotation axis of the fan, the fan blade has a blade cross section having concave portions formed at the pressure surface and the suction surface. A plurality of fan blades include fan blades having blade cross sections of different shapes. With such a configuration, the fan has an excellent air-blowing capacity while preventing noise. A molding die for use in production of the fan and a fluid feeder including the fan are also provided.

Abstract: A method of operating an axial turbine, having a stage including stationary blades and moving blades, each stationary blade having a radial height of an outlet thereof higher than the radial height of an inlet thereof, each moving blade being located downstream of a corresponding one of the stationary blades along a flow direction of a working fluid, the moving blades being constructed such that a moving blade front-end peripheral velocity Mach number exceeds 1.0, the method including restraining a radial velocity component of a working fluid flowing through an outer peripheral portion of the stationary blade from the stationary blade inlet to the stationary blade outlet, whereby the working fluid having passed through the stationary blade flows substantially parallel to the central axis of the turbine from the stationary blade outlet to the moving blade inlet.

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: An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vane root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The blade has a blade airfoil profile shape in an envelope within a range of .+?.2.0 mm in a direction normal to any surface location of an airfoil profile portion. The airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates wherein Z is a distance representing a sectional height from a root of the airfoil profile portion. The contours represented by X and Y at each section Z are joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion.

Abstract: An airfoil for a compressor is described. The airfoil has a root, an airfoil tip, a leading edge, a trailing edge, airfoil pressure and suction sides extending between the leading edge and the trailing edge. The airfoil has an inner span region and an outer span region and the trailing edge has a dihedral profile such that the trailing edge dihedral angle decreases in at least a portion of the inner span region and the outer span region.

Abstract: The invention describes a propeller-less turbine for the conversion of linear flow energy to rotary power. The turbine is based on a plurality of hollow elements, with at least one element having a tapered helical structure. Inlet and outlet define a chamber through which air or water may flow, energy from the flow being delivered to the body of the turbine and thus allowing for highly efficient conversion of linear to rotary energy.

Abstract: The present invention relates to a concave blade for a wind generator, formed by a body (1) determined by a surface defining a concavity (3), with a flattened part (2) at one end for being fixed by means of said flattened part (2) in a radial position on a support disc.

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 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 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: An exemplary aerofoil blade for an axial flow turbomachine has a radially inner platform region, a radially outer tip region, an axially forward leading edge, and an axially rearward trailing edge. The aerofoil blade has a pressure surface which is convex in a radial direction, and a suction surface which is concave in the radial direction. The axial width (W) of the aerofoil blade can vary parabolically between maximum axial widths (Wmax) at the platform and tip regions, respectively and a minimum axial width (Wmin) at a position between the platform region and the tip region.

Abstract: A blade of a turbomachine, especially of a steam turbine, is characterized in that the chord length (sm) in the middle region of the blade airfoil is shorter than the chord lengths (s0, S1) in the tip-side region or root-side region of the blade airfoil. As a result of this, a distribution of a Zweifel parameter over the longitudinal extent of the blade airfoil is achieved which minimizes the losses of a blade cascade of the blades.

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 axial flow fan includes a plurality of blades disposed around and rotating together with the rotation shaft, the blades each including a leading edge, a trailing edge, a leading edge portion proximate the leading edge, a trailing edge portion proximate the trailing edge, a suction surface, a pressure surface, the suction surface having a curved shape; wherein the blade trailing edge portion has a constant thickness; and the trailing edge is formed in a semi-circle which is bi-sected by a mean camber line of the air foil.

Abstract: A gas turbine engine airfoil shaped component is disclosed including in one form a compressor blade or vane having a tip portion capable of producing a relatively low pressure near the leading edge of the tip to induce a local jet of stream-wise momentum flow. In one form the tip portion includes a camber angle distribution that produces relatively large change in camber angle near the leading edge but relatively flat distribution for remainder of blade. In one form the tip portion includes relatively large change in camber angle near trailing edge.

Abstract: Thick airfoil families with desirable aerodynamic performance with minimal airfoil induced noise. The airfoil families are suitable for a variety of wind turbine designs and are particularly well-suited for use with horizontal axis wind turbines (HAWTs) with constant or variable speed using pitch and/or stall control. In exemplary embodiments, a first family of three thick airfoils is provided for use with small wind turbines and second family of three thick airfoils is provided for use with very large machines, e.g., an airfoil defined for each of three blade radial stations or blade portions defined along the length of a blade. Each of the families is designed to provide a high maximum lift coefficient or high lift, to exhibit docile stalls, to be relatively insensitive to roughness, and to achieve a low profile drag.

Abstract: A circumferential row of aerofoil members span an annular duct for carrying a flow of compressible fluid. The duct is centered on the axis of a turbomachine. Pressure and suction surfaces of neighboring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid. The row of aerofoil members includes at least one radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal. Each aerofoil member has reverse compound lean. Each aerofoil member further has a leading edge which has a position at the endwall which is upstream of its position at midspan. The endwall at each sectoral passage has a non-axisymmetrical cross-section formed by a region that, in meridional section, is convexly profiled immediately adjacent the pressure surface and a region that, in meridional section, is concavely profiled immediately adjacent the suction surface.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. 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 can be joined smoothly with one another to form a complete airfoil shape.

Abstract: A wind turbine blade having an aerodynamic profile (5) with a leading edge (11), a trailing edge (13) and suction and pressure sides (17, 19) between the leading edge (11) and the trailing edge (13) which has, on at least one part of the wind turbine blade, a Trailing Edge Region (TER), the transversal section of which increases in the direction of the trailing edge (13). Said trailing edge region (TER) preferably has a divergent form with a curved concave surface on its lower part.

Abstract: Provided is an impeller of a centrifugal compressor including: a hub; a plurality of blades protruding from a surface of the hub, wherein a passage is formed by the hub and a blade being adjacent with the hub, so that a fluid, flowing in along an axial direction at an inner circumferential side in a radial direction, is flowed out toward an outer circumferential side in a radial direction; each of the plurality of blades includes a main body part and a leading edge, the main body part including a pressure side and a suction side; an angle between a component central line of the main body part and the axial direction increases from an inner end toward an outer end; and a radius of curvature at a central position, intersecting with the component central line of the leading edge, decreases from the inner end toward the outer end.

Abstract: A fan structure is provided, including a hub and a plurality of blades surrounding the hub. Each blade has a first segment connected to the hub and a second segment extended outwardly from the first segment. A first surface is formed between the first segment and the hub, and a second surface is formed between the first and second segments. The first and second surfaces respectively have a first and second setting angle relative to a base plane of the fan structure, wherein the first setting angle exceeds the second setting angle.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE A. 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 can be joined smoothly with one another to form a complete airfoil shape.

Abstract: A rotor blade for a gas turbine engine includes an airfoil that extends in span between a root and a tip region. A leading edge and a trailing edge of the airfoil section extend between a chord line of the airfoil. A sweep angle is defined at the leading edge of the airfoil section, and a dihedral angle is defined relative to the chord line of the airfoil section. The sweep angle and the dihedral angle are localized at the tip region of the airfoil section.

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.