Abstract: A turbine engine with a tip shroud and method for shaping the tip shroud where at least one pair of airfoils including a first and second airfoil each having an outer wall bounding an interior. Each airfoil extending between a pressure side and a suction side to define a circumferential direction and extending between a leading edge and a trailing edge to define an axial direction. Each airfoil extending between a root and a tip to define a radial direction. The first and second airfoils are circumferentially spaced to define an inlet between the leading edges and an outlet between the trailing edges where each airfoil is coupled to an inner platform at the root. A tip shroud circumscribing the airfoil operably coupled to the tip extending in the axial direction between axially spaced first and second planes where the tip shroud includes at least one scalloped portion.

Abstract: A heat dissipation fan blade structure and a heat dissipation fan thereof. The heat dissipation fan blade structure includes a main fan blade and a subsidiary fan blade. The main fan blade has a root section and a free end section. The root section is connected with a hub. The free end section radially extends in a direction away from the hub. A main body section is formed between the root section and the free end section. The subsidiary fan blade extends from the free end section of the main fan blade toward the root section of the main fan blade to the main body section. The subsidiary fan blade and the main fan blade together form a loop structure defining a flow way between the main fan blade and the subsidiary fan blade.

Abstract: A fan includes a frame, rotor supported by this frame and having a central hub and a number of blades and a drive mechanism for rotatably driving the rotor, in addition to a ring to which the end zones of the blades are connected. The ring is assembled from two part-rings of the same form which each include a circular strip of sheet material, the free ends of which are mutually connected to form the outer surface of a truncated cone, and a third part-ring which mutually connects the inner edges of the first two part-rings. The end zones of the blades are connected to the third part-ring. The ring has a diameter of more than about 1.50 m. The number of blades amounts to at least eight. The blades are hollow and include a framework structure which is provided with a skin connected thereto.

Abstract: Low-pressure turbine rotors for a thermoelectric power station include an interconnection of slender blades. The rotor includes blades bearing caps being roughly in the shape of a chevron.

Abstract: A wind turbine for generating electrical power, the turbine having a rotor assembly comprising a hub, an annular rim and a plurality of blade members extending between the hub and rim, a pulley transfer box apparatus and a looped member extending circumferentially about the annular rim and through the pulley box transfer apparatus, the pulley box transfer apparatus having a pair of drum pulleys each having a plurality of annular grooves receiving the looped member.

Abstract: A high output bent fin type of fan wheel for use in appliances such as but not limited to microwave ovens. The fan wheel is made by single 90-degree bends for each fan blade relative to the flat mounting plate. Unique to fan wheel is the large fan blade surface area in relation to the total area of the metal used in wheel.

Abstract: A cover of an airfoil having opposing pressure and suction sides of a rotatable turbine stage to prevent fluid from crossover-flowing from a pressure side of a leading airfoil to a suction side of a trailing airfoil is provided. The cover includes pressure and suction side edge portions, one of which having a shape that is discontinuous relative to that of a complementary one of suction and pressure side edge portions of an aft cover of a corresponding one of a trailing and a leading airfoil, respectively.

Abstract: A rotating screen, for use with a centrifugal fan of an engine, includes a hub having a rotational axis and a plurality of blades extending radially outwardly from the hub. Each of the blades includes a root adjacent the hub, a tip, a leading edge extending between the root and the tip, and a trailing edge extending between the root and the tip. The blades also include an airfoil shape. The rotating screen also includes a band concentric with the hub and interconnecting the tips of the respective blades.

Abstract: A blade is disclosed for a gas turbine including an airfoil, which extends along a longitudinal axis from a blade root to a blade tip, and has a shroud segment at the blade tip. The shroud segment abuts with first and second edges against shroud segments of adjacent blades to form a ring-like shroud. The first and second edges are each provided with a respective side rail on the upper side of the shroud segment. Each of the side rails is subdivided into sections of different height and/or width.

Abstract: The invention relates to a gas turbine blade (10), in particular a compressor blade and/or turbine blade for a turbomachine, wherein the gas turbine blade (10) comprises at least one receptacle (18) for the form-fitting arrangement of a connecting element, by means of which a mechanical load can be introduced into gas turbine blade (10). The invention further relates to a shrouding band segment (16) for arrangement on a gas turbine blade (10), a connection system having a gas turbine blade (10) and having a connecting element, a method for connecting a gas turbine blade (10) to a connecting element, and a rotor for a turbomachine having a rotor disk (12) joined to a blade ring or having a rotor ring joined to a blade ring.

Abstract: A vertical axis turbine and method of making same is disclosed. The device and method comprise a plurality of blades rotatably disposed around an axis of rotation at a plurality of blade locations, each blade being twisted at a first angle about its longitudinal axis, each blade having its distal ends located a predetermined distance from the axis of rotation, each blade being bent at one or more central locations along the longitudinal axis so the one or more central locations are the same predetermined distance from the axis of rotation as the distal ends, each blade having a foil cross section perpendicular to the axis of rotation for maintaining unidirectional rotation of that blade about the axis of rotation in a fluid flow, and each blade having its longitudinal axis tilted at a second angle with respect to the axis of rotation.

Abstract: A blower wheel comprises a hub, a guide and blades extending radially between the hub and the guide, each blade comprising a root at its junction with the hub and a head at the junction with the guide, each blade having a leading edge and a trailing edge between which, at each flattened cross section, a chord is defined. For each blade, in the radial direction from the root to the head, the pitch angle between the chord and the rotation axis of the wheel varies and the variation in the pitch angle between the root and the head has a point of inflexion between a first level and a second level.

Abstract: A wind turbine is disclosed. Various embodiments of the wind turbine have a turbine rotator assembly that, when rotated by the wind, provides a rotational input motion to a power generation unit. The turbine rotator assembly may include a central rotator bearing and an outer ring. A plurality of flexible fins are mounted in tension between the outer ring and the central rotator bearing such that the fins are able to flex when contacted by wind at certain wind speeds. The fins may be mounted at an angle and at a twisted configuration to facilitate flexing of the turbine rotator assembly in a direction that is opposite to the direction in which the wind is blowing. Various embodiments employ electrical generator units and other embodiments employ hydraulic pump and motor arrangements that are coupled to an electrical generator.

Abstract: A banded turbine configuration has an integral outer band support structure capable of providing two point simple support for a multiplicity of blades. A large scale vertical array has a set of twelve 23 m-diameter banded turbines with up to nine blades and resting on an Open Web Steel Joist (OWSJ) platform. The banded turbine configuration is supported off of a main shaft hub assembly, which is supported by forward and aft pillow block bearing assemblies. The banded turbine allows for a protective screen for bird- and bat-kill prevention. Each banded turbine employs DC alternators to provide a switchable output which is subsequently fed to a dedicated set of high efficiency grid-compatible solid state invertors or, alternatively, to energy storage.

Abstract: An exemplary fan includes a hub and an impeller. The hub is made of metal, and includes a flange. The impeller is made of plastic. The impeller is formed around the hub and has the flange embedded therein. A method for manufacturing the fan is also provided.

Abstract: A steam turbine rotor blade has a profile and a cover integrally formed on and at an end of the profile, the leading edge of the cover formed on the profile and the trailing edge of a cover formed on an adjacent preceding profile being in contact and connected with each other by the torsional return force produced during rotation. The cover formed on the profile is provided with a radially-formed stepped portion at the trailing edge, the stepped portion having a height large than the thickness of the cover.

Abstract: An impeller in a centrifugal fan includes a support portion having a cylindrical outer circumferential surface coaxial or substantially coaxial with a center axis and a plurality of moving blades arranged on the outer circumferential surface of the support portion independently of one another and configured to draw an air along the center axis and expel the air radially outwards when rotated about the center axis together with the support portion. At least one of the moving blades includes a first blade portion connected to, and extending radially outwards from, the outer circumferential surface of the support portion, at least one second blade portion having a radial inner end portion radially spaced apart from the outer circumferential surface of the support portion and a connecting member arranged to interconnect the first blade portion and the second blade portion.

Abstract: A turbine diaphragm includes an annulus of static blades and an outer diaphragm ring surrounding the annulus of static blades and welded to the outer platforms. Each static blade has an inner platform, an aerofoil, and an outer platform. The inner platforms serve the function of an inner diaphragm ring, thereby reducing material and manufacturing costs. Furthermore, confronting edges of the inner platforms have an interference fit with each other and the aerofoils are in a state of torsional stress between the inner and outer platforms. The latter two features improve the dynamic characteristics of the diaphragm.

Abstract: A lift-type turbine comprising at least three blades at circumferentially spaced positions is supported for rotation about a vertical axis. Each blade has an airfoil shape to generate a torque about the axis responsive to wind across the blades. A support comprising cables under tension is connected between adjacent ones of the blades to extend generally circumferentially about the turbine. Accordingly a minimum number of parts form the structure of the blades while minimizing the drag produced during rotation thereof due to the support members lying in a common circumferential path. The tension of the support members can support the blades in a pre-stressed condition to optimize the shape and performance thereof.

Abstract: A shroud of adjacent turbine moving blades has the primary contact face portion, which has opposing flat faces forming an acute angle from a turbine rotating direction and has the secondary contact face portion which has opposing flat faces forming an obtuse angle from the turbine rotating direction. In a process of increasing the rotor speed of a turbine, the secondary contact face portion shifts from a contacting state to a separated state, and thereafter, the primary contact face portion shifts from the separated state to the contacting state. According to such arrangement, vibration in a turbine higher speed range can be suppressed in addition to the suppression of the contact reaction force between coupling members of adjacent turbine moving blade from increasing too high, thereby improving the reliability of the turbine moving blades.

Abstract: A turbine disk includes a rotor and a plurality of turbine blades, each comprising a root at a proximal end secured to the rotor and a tip having a shroud at a distal end. The shroud includes a inner diameter surface, an outer diameter surface and a segmented sidewall surface separating the inner and outer diameter surfaces. The shrouds of adjacent turbine blades are separated by a tip shroud damper, and which includes a retention rail that cooperates with the outer diameter surface to maintain a positional relationship of the damper, a inner flange that engages the segmented sidewall surface, and a web that separates the retention rail and the inner flange. The tip shroud damper reduces the vibratory responses of modes involving axial and radial shroud motion to prevent high cycle fatigue (HCT).

Abstract: A turbine blade including a root section at an end of the turbine blade, a first airfoil section adjacent to the root section, and a tip section adjacent to the airfoil section and including a material block that is incongruous with the airfoil section. A midspan section may also include a material block. Each material block can be selectively machined to customize the length of the turbine blade and the position of a tip shroud connection or midspan connection. The turbine blade can be sized for retrofitting last stage blades of older turbines. A radial position of the root mounts for the turbine blade may also be adjusted to provide further customization.

Abstract: An apparatus and method for harvesting fluid energy including a wave turbine consisting of a long shaft having pairs of buckets positioned at intervals along the shaft and rotated 90 degrees from each adjacent pair. Each bucket is connected at an offset angle with respect to a plane that is normal to the shaft. When adapted for harnessing wave energy, the shaft is elevated above water surface and positioned at an oblique angle to the prevailing wave fronts. Each bucket is positively buoyant, so that buckets capture both potential and kinetic wave energy.

Abstract: A fluid turbine for generating electrical power, the turbine having a rotor assembly comprising a hub, a rim and a plurality of blade members joining them together, the blade members being rigid, flat panel, multi-ply, composite blade members having a plurality of parallel, longitudinally-oriented, reinforcing cords composed of non-braided aramid synthetic strands, the cords being disposed between at least two cloth layers impregnated with a cured polymer resin.

Abstract: A wind turbine is disclosed. Various embodiments of the wind turbine have a turbine rotator assembly that, when rotated by the wind, provides a rotational input motion to a power generation unit. The turbine rotator assembly may include a central rotator bearing and an outer ring. A plurality of flexible fins are mounted in tension between the outer ring and the central rotator bearing such that the fins are able to flex when contacted by wind at certain wind speeds. The fins may be mounted at an angle and at a twisted configuration to facilitate flexing of the turbine rotator assembly in a direction that is opposite to the direction in which the wind is blowing. Various embodiments employ electrical generator units and other embodiments employ hydraulic pump and motor arrangements that are coupled to an electrical generator.

Abstract: A fan comprises an impeller and a motor. The impeller has a hub, a plurality of blades and a plurality of reinforced elements. The blades are disposed around the hub. At least one reinforced element is disposed on the active surfaces of two adjacent blades. The blades and the reinforced elements are integrally formed as a single piece. The motor connects to the impeller for driving it to rotate.

Abstract: A turbomachine (1), in particular a turbine or compressor, includes a rotor (2) which has at least one moving blade row (4) with a plurality of moving blades (5), and a stator (3) which has at least one guide vane row (6) with a plurality of guide vanes (7), at least in one of the blade or vane rows (4, 6) all the blades or vanes (5, 7) each having a shroud plate (10). In order to simplify the maintenance of the turbo-machine (1), the shroud plates (10) are separate components with respect to the respective blade or vane (5, 7) and are mounted on the respective blade or vane (5, 7), shroud plates (10) adjacent in the circumferential direction (9) being coupled to one another for the transmission of tensile forces in the circumferential direction (9).

Abstract: A wind driven energy source is providing integrated a series of radially extending masts from a central hub. The masts are supported by a series of cables. A mast-to-mast tension cable spans between distal ends of adjacent masts. A mast-to-axle tension cable spans between the distal end of each mast and each axial end of the central hub. A turbine blade is supported by each mast. The turbine blades can be of a rigid or pliant material. An angle of incidence of the rigid blades can be adjusted by rotating the mast. An angle of incidence of the pliant blades can be adjusted by applying tension to a blade control cable. Pliant blades can be retracted into the mast via a retracting mechanism to reduce the exposed surface area when subjected to excessive wind speeds.

Abstract: Injection molded ring fan embodiments and methods for making them. The methods influence material flow during the injection molding process such that a major portion of the materials flowing in opposite directions in the outer rings preferably flow past one another, intermix in a swirling relationship, and/or collide at an angle relative to one another. This results in better material mixing or integration of the flow fronts. In one embodiment, the thickness of the outer ring varies in different portions between adjacent fan blades.

Abstract: A wind power extraction device has a rotor with a hub and a rim coupled to the hub through a plurality of blades. The blades rotate the rotor about an axis of rotation passing through the hub in response to a wind moving generally parallel to the axis of rotation. A mount coupled to the rotor extends and retracts the rotor between a first configuration aligning the rotor axis of rotation substantially horizontally, and a second configuration aligning the rotor axis of rotation substantially vertically. The device may have components of an electric generator mounted in or near the rim.

Abstract: A fan has a plurality of blades extending in a radial direction with respect to a rotation axis and a ring portion disposed on radial outside edges of the blades. Further, the fan has a first connecting wall and a second connecting wall. The first connecting wall extending from the ring portion to a portion of the radial outside edge of each blade, the portion protruding from the ring portion toward an upstream position with respect to an air flow direction. The second connecting wall has a generally triangular shape. The second connecting wall continuously extends from the first connecting wall and connects to the ring portion on a leading side of the first connecting wall with respect to a rotation direction of the blade. The fan is for example housed in a shroud, thereby to construct a blower unit.

Abstract: An integrally bladed rotor is constructed from a plurality of layers of organic matrix composite material wound together in a spiral fashion to form the disc portion of the rotor, and at each rotor blade position at least the outermost one of the layers is turned substantially radially outwards from the periphery of the rotor disc to form a blade. Each blade is finished with further pieces of organic matrix composite material bonded into position on the. An encircling blade tip shroud may be formed by further layers of material wound around the tips of the blades in conjunction with closed loop inserts in the spaces between blades.

Abstract: A rotor (10) that enables an aircraft to become passively stable in hover. The inner part of the rotor blades (11) have a pitch angle fixed relative to a reference plane perpendicular to the rotor shaft (18) axis, and the tip of the rotor blades being connected to a ring (12) encircling the rotor. Each blade is connected to the rotor shaft by a separate hinge having a hinge axis perpendicular to both the rotor shaft axis and to the blade. Because the rotor blades can also easily twist the rotor can tilt freely in any direction. The rotor blades may be disconnected from the ring and folded up for easy transport.

Abstract: A centrifugal fan assembly including a housing having a lower surface and a parallel inlet wall that defines an inlet opening. A shaft is supported by the housing for rotating about an axis. A plurality of fan blades are disposed about the shaft and extend radially from the axis for drawing air axially into the fan blades and blowing air radially outwardly. The housing defines a scroll wall that spirals about the axis and defines an outlet air passage that extends substantially tangentially to the axis. The fan blades include extensions that extend through the inlet opening and outside of the inlet wall.

Abstract: A method to influence material flow during the injection molding of thermoplastic, polymeric ring type fans such that a major portion of the materials flowing in opposite directions preferably flow past one another, or collide at an angle relative to one another, rather than colliding at an 180 degree angle relative to each other to form weld lines. This flow bypassing results in better material mixing or integrating than merely allowing flow fronts to collide and cool. In one embodiment, a portion of the fan's ring is thickened in the weld line area to minimize the amount of material colliding at a 180-degree angle relative to each. Alternatively, at least one appendage could be added to the ring fan that will influence the material flow during molding conditions. Each appendage will be removed prior to introducing the ring fan to a cooling system.

Abstract: An unshrouded rotor blade 24 comprising an aerofoil 28, said aerofoil 28 having a leading edge 34, a trailing edge 36, a pressure surface 30 and a suction surface 32, there being provided at a radially outer extremity of the aerofoil 28 a gutter 40 which is wider than the aerofoil 28 adjacent the trailing edge 36 thereof, wherein at least a part of the gutter 40 is offset towards the aerofoil pressure surface 30.

Abstract: A bucket for use on a steam turbine rotor wheel, the bucket comprising a shank portion and an airfoil portion, the airfoil portion having a radially outer tip with a tip cover adapted to be engaged, in use, by a similar tip cover on an adjacent bucket, wherein a radial step is formed in the tip cover and the airfoil portion along a leading edge of the airfoil portion.

Abstract: An axial flow fan. The axial flow fan includes an impeller, an annular structure, and a plurality of connecting elements. The impeller has a plurality of blades, arranged radially. Each blade has an outer periphery. The outer periphery has a top portion. The annular structure is attached to the top portion of the outer periphery of each blade. Each connecting element respectively connects each blade to the annular structure.

Abstract: An inducer rotor rotatably mountable in an inducer for pressurizing fluid traveling through the inducer. The inducer rotor includes a hub. The hub has a central axis and a plurality of blades extending radially outward from the hub. Each blade extends from a root portion that is next to the hub, to a tip portion that is opposite the root. The rotor further includes a shroud extending circumferentially between each pair of adjacent blades within the plurality of blades. The shroud has an inner surface facing the central axis and an outer surface that is opposite the inner surface. Between the inner and outer surface of the shroud is defined a thickness. The shroud thickness varies circumferentially around the shroud.

Abstract: Whereas for each propeller blade of a radiator fan, an attachment angle ?1 at a propeller blade base portion, projected onto a plane parallel to an attachment surface of the propeller blades with respect to the boss is set in a range of 35 to 45°, an attachment angle ?2 of a propeller blade tip portion is set in a range of 15 to 22°. Seven propeller blades and a chord length Ct of the propeller blade tip portion, and an outer circumference length ?×Df of the propeller blades are set to satisfy a relationship 0.65<7Ct/(?×Df)<0.85. A tip broadening ratio of the propeller blades is set to within a range Ct/Cb=1.5 to 2.1, based on the chord length Ct at the propeller blade tip portion, and a chord length Cb at the propeller blade base portion. A fan sweep angle ?3 is set in a range of 15 to 25°.

Abstract: A fan 10 includes a central hub 14, an outer ring structure 18, and a plurality of fan blades 12. Each blade is of generally Y-shaped configuration having first and second separate branches 12a, 12b, respectively, coupled to the hub 14 and merging with a third branch 12c. The third branch 12c is coupled to the ring structure 18 at a tip 16 of the blade 18.

Abstract: A method is provided for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and a vane. The replacement casting includes an airfoil stub. The airfoil stub is received in a recess formed in the inner band. Joining is completed by joining the airfoil stub to the inner band. The replacement casting may be modified from a newly manufactured singlet casting.

Abstract: A centrifugal blower impeller includes a central hub and a plurality of impeller blades. The central hub includes a conical section and an outer edge. The conical section is centered with respect to a center axis and extends from the center axis towards the outer edge. The plurality of impeller blades includes first and second ends. The conical section is coupled to the first ends of the impeller blades which extend axially upward from the first ends towards the second ends. The centrifugal blower impeller also includes a rim which has a generally circular shape and is connected to the second ends of the impeller blades.

Abstract: A method and apparatus for fabricating a rotor assembly for a turbine is provided. The method includes forming a cover on each bucket radial tip wherein the cover includes a leading edge side in a direction of rotation, and a trailing edge side in the direction of rotation wherein the leading edge and trailing edges are parallel with respect to each other, and wherein the leading edge and trailing edges are skewed with respect to the axis of rotation. The method includes forming an extension in the cover leading edge side, forming a groove in the cover trailing edge side, and attaching each bucket to the radially outer rim, such that the extension in the cover leading edge side of one cover is in mating engagement with the groove in the cover trailing edge side of an adjoining cover.

Abstract: A high-performance propeller has one hub and a plurality of blades, characterized in that a double-side or a single-side arc brim is provided at the tip of each blade. The propeller of the invention can provide a small induced drag and convert the centrifugal force to the effective force so as is to increase the differential pressure near the tip of blades and thereby increase the acting force on blades. Under the condition of same power consumption, it has been tested for the large propeller in the type of lateral inclination that the amount of flow is increased about 12%˜17%, which is equivalent to save energy 40%˜70%. Since the fluid dynamic performance presents the aspect ratio approaching infinity, the width of the blades can be increased whereas the induced drag is not increased. Applying the method of increasing the area of the blades and decreasing the velocity of outflow fluid, the effect on saving of energy can be further improved greatly on the present basis.

Abstract: In the embodiments described in the specification, an impeller is manufactured by providing a mold for one angular segment containing one vane of an impeller and corresponding hub and rim portions, injection-molding fiber-reinforced polymer composite resin material into the mold to produce a plurality of substantially identical segments, and assembling the segments into an impeller by bonding corresponding mating end surfaces of the hub and rim portions of the segments. A veil cloth is applied to the outer surface of the rim portion and impregnated with resin material to complete the impeller structure.

Abstract: A turbine bucket and cover assembly includes a bucket having a shank portion and an airfoil portion separated by a platform portion; and a bucket cover arranged on a sloped radially outer tip of the airfoil portion, the bucket cover having a radially inner surface matching the sloped edge and a radially outer surface lying in a plane parallel to a longitudinal axis of a rotor on which the bucket is adapted to be mounted. A related method includes the steps of a) providing a bucket cover having substantially parallel radially inner and outer surface; b) removing material from the bucket cover so as to form a new radially outer surface defining an acute angle relative to the radially inner surface; and c) securing the bucket cover on the sloped airfoil tip of the turbine bucket such that the radially outer surface is substantially parallel to the turbine rotor axis.

Abstract: The moving blades are configured so as to meet a condition: (L+3D)×f≧14,500 or L×(L+D)×f2≧1.55×107, where L is an effective length of the moving blade measured in inches, D is a blade root circle diameter of the moving blades measured in inches, and f is the rated operating speed of the turbine measured in Hz. The moving blades are formed of a titanium alloy. The dovetail has an Christmas-tree shape, and is a curved-axial-entry. The moving blades are configured and arranged so as to meet a condition: 3.5≦P/W≦7.0 or 0.8≦P/C≦1.0, where W is a width of a section of a tip of the moving blade measured along an axis of the rotor wheel, P is pitch of the moving blades, and C is a chord length of the tip section of the moving blade. Adjacent moving blades are connected to each other in such a manner that the adjacent moving blades being capable of relative movement while the adjacent moving blades being connected to each other.

Abstract: A turbofan and a mold used to manufacture the same, which enables the turbofan to be integrally molded by a single molding process. The turbofan has a rotating plate coupled to a shaft of a driving motor at its center, a plurality of blades radially disposed at and integrally formed with a periphery of the rotating plate, and a ring-shaped shroud integrally formed with front ends of the blades to face the rotating plate.

Abstract: A vehicle regenerative-type fuel pump which reduces the possible accumulation and effects of contamination relative to impellers with outer ring members. The impellers for the pump have outer ring members with non-uniform configurations (slanted, curved, grooved, etc.) which reduce the affects of contamination which can cause wear and roughing of the outer surface resulting in higher torque and reduced pump efficiencies.