Abstract: A blade outer air seal (BOAS) casting core has first and second end portions and a plurality of legs. Of these legs, first legs each have: a first end joining the first end portion; a main body portion; and a second end. Second legs each have: a second end joining the second end portion; a main body portion; and a first portion. At least one of the second legs may have its first end joining the core first end portion and a plurality of apertures in the main body portion. Alternatively, at least one of the first legs may have its second end joining the core second end portion and a plurality of apertures in its main body portion.

Abstract: A portable electronic device includes a casing, an electronic component disposed in the casing, and a thermal module for dissipating heat of the electronic component. The thermal module includes a heat pipe, a fin unit, and a transverse fan. The heat pipe includes an evaporating section thermally attached to the electronic component, and a condensing section thermally attached to the fin unit. The transverse fan is arranged in the casing for generating an airflow through the electronic component and the fin unit. The transverse fan includes a rotor, and a sidewall on a floor of the casing and surrounding the rotor. The sidewall defines an air inlet and an air outlet therein. The air outlet faces to the fin unit. The air inlet faces to the electronic component.

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 cooling fan of the present invention includes: a bottomed cylindrical boss portion; and a plurality of blades provided on an outer circumferential surface of the boss portion, the blades radiating in a radial direction, in which a ring member for connecting the blades with each other is provided on a side radially inner from tips of the blades. According to the present invention, it is possible to provide a cooling fan capable of preventing the worsening of the noise characteristic and also of enhancing the versatility even if the blades are made thinner.

Abstract: A method for machining a blank includes machining a first pocket in the blank having a first sidewall, machining a second pocket in the blank, machining a groove within material located between the first and second pockets to expose a second sidewall opposite the first sidewall, machining the first and second sidewalls, and alternately repeating machining the grove and the sidewalls to step mill the groove deeper in the blank and form a third pocket along which the second sidewall extends.

Abstract: The fan impeller (10) comprises a hub (14) and blades (12) extending radially outward from the hub, the blades having a flattened airfoil profile cross section with a leading edge (24) and a trailing edge (26) between which a chord is defined. The blade (12) has a relative thickness that reached its maximum value (Emax) in the first quarter of the length of the chord measured from the leading edge (24), the relative thickness being defined by the ratio between the thickness of the blade and the length of the chord. The invention finds an application particularly in motor vehicle engine cooling fan impellers.

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 aerodynamic shroud positionable surrounding a hub to which blades are attached is disclosed. The shroud has a textured outer surface that is configured so as to create a turbulent boundary layer for fluid flowing over the surface. The turbulent boundary layer delays flow separation from the shroud and reduces drag. The shroud may be formed from a domed shell mounted on the hub and have skirts that surround the hub. The textured surface is provided by dimples in the surface or projections from the surface. The shroud is intended to reduce main and tail rotor hub drag on helicopters but is also useful on marine propellers, aircraft propellers and jet engine fans.

Abstract: A turbine blade 10a which is a stop blade is provided with a cutout portion 50 which is formed in one circumferential side surface 22a of a shank portion 22 at the center in the axial direction of a turbine rotor 100, a cutout portion 60 which is formed in one circumferential side surface 22a of the shank portion 22 from one end portion 22b to the cutout portion 50 in the axial direction of the turbine rotor 100, and a through passage 70 which is formed to pass from the cutout portion 50 to an effective blade part and in which a moving member 170, which moves a stopper member 160 to the effective blade part in the cutout portion 50, is inserted.

Abstract: A rotor hub fairing system includes an upper hub fairing, a lower hub fairing and a shaft fairing therebetween. The rotor hub fairing system is attached to the counter-rotating, coaxial rotor system through a bearing arrangement such that the shaft fairing may be positioned at an azimuthal position about the main rotor axis of rotation relative the airframe by a de-rotation system. The de-rotation system controls the position of the shaft fairing about the axis of rotation such that the shaft fairing is prevented from rotating freely in unison with either shaft as may otherwise result during some flight regimes.

Abstract: Plural saddle shape patches are formed on a blank material for forming a blade using a manufacturing apparatus provided with a punch support having punches each with a holder attached to be opposite with one another at a predetermined interval corresponding to a thickness of the blank material. The punch support is mounted to a second ram via a second rotational mechanism which is rotatable in a direction in which the ram moves. The die is attached to the first ram via the first rotational mechanism. The actuator controls the rotating angles of both the rotational mechanisms.

Abstract: A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth.

Abstract: A de-rotation system includes a first ring gear defined about an axis of rotation, a second ring gear defined about the axis of rotation and a gear set in meshing engagement with the first ring gear and the second ring gear to control a position of a housing about the axis of rotation.

Abstract: A turbine bucket that may include an airfoil having a tip shroud, the tip shroud having an edge; wherein the edge has a profile substantially in accordance with values of X and Y in a Cartesian coordinate system set forth in Table 1 at points 1-14, wherein X and Y represent distances that may be proportionally scaled by a common multiplier which, once scaled and connected, define the profile of the edge of the tip shroud.

Abstract: Turbine systems for extracting energy from water traveling relative to the turbine system can include a rotor assembly for extracting the energy, a turbine shroud having a turbine shroud inner volume within which at least a portion of the rotor assembly is disposed, and an ejector shroud having a ejector shroud inner volume within which at least a portion of the turbine shroud is disposed. The turbine shroud and the ejector shroud can each have a terminus comprising a plurality of turbine shroud mixer elements or ejector shroud mixer elements, respectively. One or more of the mixer elements and ejector shrouds comprise a mixer/ejector pump which increases the energy extraction potential of the turbine system. One or more of the turbine shroud mixer elements, ejector shroud mixer elements, and ejector shroud and turbine shroud inlets can be asymmetric about a plane passing through the axis of rotation of the rotor assembly.

Abstract: A turbine blade rotor assembly is disclosed for a gas turbine engine. The assembly includes a rotor having nickel alloy turbine blades secured thereto. Each of the blades includes a root and an airfoil. The roots are supported by the rotor. A ceramic matrix composite platform separate from the turbine blades is supported between each pair of the turbine blades adjacent to the airfoils. In another example, the airfoil includes a perimeter. A shroud having an aperture receives the airfoil with a single shroud substantially surrounding the airfoil at the perimeter. In one example, the turbine blade includes high and low pressure sides opposite one another that extend from a tip to a root. The airfoil is free from any protrusions extending from the high and low pressure sides on a portion of the blade axially outward from the root.

Abstract: An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler defines an airflow surface for air being drawn through the engine. The annulus filler has one or more primary connectors for connecting the annulus filler to the rotor disc, and for resisting, in use, centrifugal forces on the annulus filler. Each primary connector allows rotation of the annulus filler around the centre line of the engine relative to the rotor disc at that primary connector. The annulus filler also has a secondary connector for connecting the annulus filler to the rotor disc and for resisting, in use, motion of the annulus filler relative to the rotor disc in a first axial direction. The secondary connector allows rotation of the annulus filler around the centre line of the engine relative to the rotor disc at the secondary connector.

Abstract: A centrifugal pump (10) includes a pump casing (12) within which an impeller (14) is mounted for rotation, cantilever fashion, on a shaft (16). The casing (12) has an axial inlet (20), and a peripheral volute (22) around the impeller (14) leading to an outlet (24). The impeller (14) has axially spaced annular sides (26, 28) with radially outwardly arranged, rearwardly curved, vanes (30) between the sides. Outwardly of the sides, clearing corresponding sides of the casing (12), auxiliary vanes (32, 34) are provided to generate a pressure gradient to prevent or counteract leakage of working fluid. Leading faces of the auxiliary vanes slope relative to a perpendicular to the sides, i.e. the leading edges are at an obtuse angle to the sides (26, 28).

Abstract: The present invention provides an automotive engine-cooling fan assembly including a motor having a driveshaft defining a central axis, and a fan driven by the motor. The fan includes an inner hub portion coupled to the driveshaft, and an outer hub portion coupled to the inner hub portion. The outer hub portion is coupled to a plurality of radially-extending blades. The fan also includes a plurality of vibration isolation members interconnecting the inner hub portion and the outer hub portion.

Abstract: A centrifugal compressor assembly for compressing refrigerant in a 250-ton capacity or larger chiller system comprising a motor, preferably a compact, high energy density motor or permanent magnet motor, for driving a shaft at a range of sustained operating speeds under the control of a variable speed drive. Another embodiment of the centrifugal compressor assembly comprises a mixed flow impeller and a vaneless diffuser sized such that a final stage compressor operates with an optimal specific speed range for targeted combinations of head and capacity, while a non-final stage compressor operates above the optimum specific speed of the final stage compressor.

Abstract: An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler has a body portion which defines an airflow surface for air being drawn through the engine, and one or more hook portions which extend radially inwardly from the body portion. The hook portions are for connection to corresponding engagement portions on the radially outer face of the rotor disc. The or each hook portion is attached to the body portion by a joining arrangement in which a wedge part provided by one of the hook portion and the body portion is received in a complementary-shaped retention recess provided by the other of the hook portion and the body portion.

Abstract: A diffuser augmented wind turbine assembly comprising an inlet wind suppressor and a shroud disposed within said inlet wind suppressor. The assembly contains a wind turbine; the wind turbine is disposed within the shroud; and the shroud is connected to a diffuser.

Abstract: A method for dimensionally restoring a stationary shroud segment, the method comprising removing at least a portion of a damaged flowpath of the stationary shroud segment to provide an exposed surface, casting a replacement flowpath, positioning the replacement flowpath on the exposed surface, and diffusion bonding the replacement flowpath to the stationary shroud segment.

Abstract: A fan-turbine rotor assembly for a tip turbine engine includes a fan hub with an outer periphery scalloped by a multitude of elongated openings which extend into a fan hub web. Each elongated opening defines an inducer section and a blade receipt section to retain a hollow fan blade section. The blade receipt section retains each of the hollow fan blade sections adjacent each inducer section. The inducer sections are cast directly into the fan hub which minimizes leakage between each fan blade section and each of the respective inducer sections to minimize airflow leakage and increase engine efficiency.

Abstract: A cooling fan includes a fan ring to be attached to an end surface of a rotor core near the outer circumference thereof, and a plurality of fins connected to the fan ring. The fan ring has positioning leg portions provided on an end surface thereof facing a thrust direction. The fan ring is positioned in relation to the rotor core through insertion of the positioning leg portions into core slots of the rotor core. The fan ring has wire accommodation recesses which are formed on the end surface of the fan ring facing the thrust direction and communicate with the core slots.

Abstract: A fan module is provided. The fan module is configured to dissipate heat from, e.g., a compressor and a condenser disposed in a machine room of the refrigerator. The fan module includes a fan, a shroud having a receiving hole positioned around the fan, a fan mounting portion coupled to a rear surface of the shroud on which the fan is mounted, the rear surface facing a downstream airflow direction of the fan, and a concave recess provided on a rear surface of the shroud and circling the receiving hole. The fan module prevents noise caused by air passing through the receiving hole and prevents flow loss.

Abstract: The present invention discloses a dust collector blade structure. In the present invention, the blades are uniformly and radiately arranged on a rotation disc. The blades are vertical to the rotation disc and form an air entrance at the center of the rotation disc. One end of each blade is exactly at the border of the rotation disc, and the other end of each blade has a wind-guiding bevel. The rotation disc is arranged inside a blower housing. The blower housing has an air outlet and a cover. The cover has an air inlet corresponding to the air entrance. The air outlet is arranged in the tangential direction of the rotation disc. The shape of the blades can reduce the air friction on the blades and thus can promote the blower performance and reduce the energy consumption.

Abstract: A turbine bucket including a bucket airfoil having a hollow tip shroud, the hollow tip shroud having a hollow core having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, in inches, wherein the shape of the core is defined by the cloud of points listed which are distributed around each surface of the shroud, and the complete hollow portion of the tip shroud could be constructed by defining smooth sheet surfaces through the listed points.

Abstract: A turbine rotor has a row of turbine blades associated with a circumferential groove in a disk, each turbine blade having foot received in the groove, a blade profile above the foot, and a shroud plate above the profile. Each blade foot and each shroud plate have end surfaces and side surfaces which form a rhomboid, the end surfaces of each shroud plate tapering toward each other along respective radii and abutting the end surfaces of adjacent shroud plates to form a closed ring. The blade profiles are torsionally stressed by applying a force to each plate in a direction parallel to the axis of the disk, thereby twisting the cover plates through an angle alpha so that the side surfaces of adjacent cover plates are circumferentially aligned in a plane perpendicular to the longitudinal axis. This force is maintained by clamping devices applied to the combs of adjacent blades.

Abstract: A method of fabricating a shrouded impeller is disclosed. The method includes providing an open faced impeller, the open faced impeller including a plurality of blades extending at least partially radially from a hub. The method also includes performing a first powder metallurgical process to form a first material over at least part of the open faced impeller. The method further includes forming a shroud circumferentially disposed about the hub and connected to one of more of the blades. Forming the shroud includes performing a second powder metallurgical process to metallurgically bond the shroud to at least some of the blades.

Abstract: A rotor blade may include a tip shroud having at least one seal tooth disposed at an angle that may be relative to the engine centerline when in an assembled condition, the leading edge of the tip shroud and/or the trailing edge of the tip shroud.

Abstract: The present invention relates to a device for transducing and/or converting of wind power into another power, for example electric power, comprising a rotor which is rotary in a tunnel tube which is mounted on the upper end of a tower the rotor having an outer ring, an inner ring and a number of blades or vanes, which extend between the rings, the outer ring having a depression extending between the edges for a belt or the like which extends to a shaft on the underside of the tunnel tube for rotation thereof on rotation of the rotor.

Abstract: A turbine ring made up of an assembly of a plurality of sectors forming the outer shroud of the rotor of said turbine. The sectors are united end to end with interposed sealing systems comprising tongues housed in slots, said tongues being rectilinear and engaged in respective rectilinear slots in the radial faces of said sectors.

Abstract: A centrifugal fan includes a fan frame (20) and an impeller (40) received in the fan frame. The impeller includes a hub (41) having a circular top wall (410) and a cylindrical side wall (412) extending downwardly from a rim of the circular top wall, a plurality of blades (42) extending radially from the side wall of the hub and a blade ring (44). The blade ring includes an annular top plate (441), a cylindrical sidewall (442) extending downwardly from an outer periphery of the top plate, and a flange (443) extending outwardly from a bottom of the cylindrical sidewall. The blade ring is arranged on top surfaces of the blades received in an air inlet (24a) defined in a top surface of the fan frame, and the top plate of the blade ring and the top surface of the fan frame are coplanar with each other.

Abstract: A row of moving blades for a steam turbine has moving blades elongated radially which are arranged peripherally around and secured to a turbine rotor 9. The row also has an intermediate support structure for holding the blades each other at a radially intermediate position. The support structure has a shape of streamline cross section. The support structure may include a tie wire secured to the blades, or lugs protruding from the blades and combined to each other. The support structure may include lugs protruding from the blades to each other, and a sleeve combining the lugs. The shape of streamline cross section may have an obtuse-angle or acute-angle upstream part.

Abstract: A novel three-vaned, drag-type wind turbine, wherein air, when it exits a first vane, is split into two flow paths. A first path is directed to a second vane, while a second path is directed to a third vane. The air, then, impinges on a plurality of vanes wherein the momentum of the air is altered, thus providing the force needed to drive the wind turbine. In a first embodiment, a wind shield is used to deflect a portion of the wind from entering the wind turbine, this portion being in a region where the vanes are rotating into the wind. In second embodiment, the wind shield is not used.

Abstract: Fluid movers produce at least predominantly laminar flow internally in an axial or a radial direction in a rotor. A fluid mover rotor comprises a matrix of passages of appropriate size to produce at least predominantly laminar flow spaced circumferentially around the rotor. The passages may provide axial, radial or mixed flow. “Appropriate” dimensions may be selected for a specified volume flow rate. In a radial embodiment, a matrix of radially extending passages could comprise walls having an axial height projecting from an annular disk. The passages may be offset with respect to the radial direction to provide an angle of attack that minimizes incidence losses. The matrix structure allows the use of thin-walled passages to minimize blockage of entering air.

Abstract: An object is to provide a centrifugal blower with reduced noise. The centrifugal blower is provided with: an impeller; a casing that houses the impeller and forms a spiral flow passage that surrounds a radial direction outside of the impeller; and a driving device that rotates the impeller about an axis. The impeller has: a bottom plate; a plurality of blades provided on a same circumference of the bottom plate; and a substantially annular plate shape shroud that has the blades interposed between it and the bottom plate, and that is disposed concentric with the bottom plate, and that connects end sections of the respective blades. The shroud has: an inclined section that comes closer to the bottom plate moving from a radial direction inside to a radial direction outside; and a shroud side barrier that rises from a position on the radial direction outside of the inclined section towards a side opposite to the bottom plate.

Abstract: An impeller used in a fan is provided. The impeller includes a hub and a plurality of blades disposed around the hub. The hub has at least one curve-shape surface. A fan comprises a fan frame, an impeller, and a motor. The impeller disposed in the fan frame comprises a hub and a plurality of blades disposed around the hub, wherein the hub has at least one curve-shape surface and an airflow guiding structure disposed on an outer circumference of the hub. The motor is disposed in the impeller for driving the impeller.

Abstract: In a rotatable duct type shrouded rotating wing, permanent magnets are arranged in the outer periphery of a rotatable duct, rotor blades are connected to the inner periphery of the rotatable duct, the rotor blades having a rotatable support portion at about every 2.5 m to prevent deflection or distortion. The shroud and the rotatable duct are constantly in vertical contact with each other, and an appropriate horizontal spacing is provided between the inner periphery of the shroud and the outer periphery of the rotatable duct to permit expansion and contraction of the rotatable duct and the rotor blades. Accordingly, even if the shrouded rotating wing is of a large radius, is used in a horizontal orientation and undergoes a rapid change of direction mounted to a turntable, it always rotates stably to generate lift and thrust.

Abstract: A ceramic seal segment for a shroud ring of a rotor of a gas turbine engine, the ceramic seal segment positioned radially adjacent the rotor and characterized by being a hollow section that defines an inlet and an outlet for the passage of coolant therethrough.

Abstract: A subject of the present invention is to prevent the reduction of rigidity caused by the increased length of a steam turbine rotor blade and the degradation of vibration characteristics. A steam turbine rotor blade according to the present invention comprises 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, and wherein 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: A fan includes a main plate and at least one or more blades connected to the main plate. At least a portion of a boundary portion between the main plate and a pressure surface of the blade is provided as a curved boundary portion such that the blade and the main plate are connected to each other at a curvature.

Abstract: The invention relates to a rotor for a non-positive-displacement machine provided with a hollow shaft, which is arranged coaxial to the rotation axis, is supported, on both sides and on the face, on two axially opposed sections of the rotor, and which encloses an inner hollow space. In order to provide a rotor for a non-positive-displacement machine, which has a higher serviceable life and is less susceptible to mechanical defects, the invention provides that the hollow shaft, in the axial direction of the rotor, is formed from a number of adjoining rings, and the rings are outwardly sealed against one another an with regard to the sections of the hollow space. Each ring has an I-shaped cross-section and the web of the I shape extends in the radial direction of the rotor.

Abstract: A wind-powered electricity generator has a body, an axle, a rotor, a stator and a fan assembly. The rotor is mounted inside the body. The stator is connected to the axle inside of the body. The fan assembly is connected to the body and has a wind-ladle device, a blade device and at least one covering device. The wind-ladle device is attached to the body with multiple wind ladles. The blade device is connected to the body and has a lower mounting plate, multiple blades and a middle mounting plate. The lower mounting plate is connected to the body. The blades are mounted annular between the mounting plates. The at least one covering device is connected to the blade device between the mounting plates and each has an inner coverings, an outer coverings and a spring.

Abstract: A centrifugal fan includes a space in which the dimension between a shroud-facing wall and a shroud, from the outer peripheral side to the inner peripheral side of the shroud, is substantially uniform, wherein the shroud-facing wall includes a recess extending in the circumferential direction, the recess being disposed at the inner peripheral side of the outer peripheral end of the shroud-facing wall forming the space having the uniform dimension so that the recess forms a space larger than the other part.

Abstract: A blade outer air seal (BOAS) has a body having an inner (ID) face and an outer (OD) face, first and second circumferential ends, and fore and aft longitudinal ends. The BOAS has one or more mounting hooks extending from the body. The OD face comprises a plurality of transversely elongate protuberances. The protuberances include rearwardly divergent first protuberances and forwardly divergent second protuberances.

Abstract: A fan (16) draws air through a core (14) of a radiator (10) to which coolant from coolant passages in an engine (12) rejects heat. A shroud (28) having first and second parts (30, 32) in axial succession channels air that has been drawn through the core toward the fan. The first part (30) is a non-elastomeric ring, and the second part (32) has an elastomeric ring (34) having opposite axial ends, one of which telescopically fits to the non-elastomeric ring of the first part (30) and the other of which joins with a second non-elastomeric ring (36).

Abstract: A vehicle has an engine movably mounted on a frame, a fan mounted on an engine driven shaft, a radiator fixedly mounted on the frame, and a hollow shroud assembly which extends from the fan to the radiator. The shroud assembly includes an inner shroud member, an outer shroud member and a flexible annular seal member which interconnects the inner and outer shrouds. The inner shroud member is mounted to the engine and fixed with respect to the engine and the fan. The inner shroud member integrally forms an aspirator port. The outer shroud member is fixed with respect to the frame. The flexible seal member sealingly engages the inner and outer shroud members. The seal member has an annular gripping part and an annular lip which projects away from the gripping part. The gripping part grippingly engages an end of the outer shroud member. The lip engages an outer surface of the inner shroud member.

Abstract: In order to couple coolant air flow presented through a coolant gallery 4, 24 through an opening 7, 27 into a passage 8, 28 a flow deflector 6, 26 is provided. The flow deflector 6, 26 progressively deflects the coolant air flow 5, 25 through the opening 7, 27 such that there is reduced loss in coolant flow 5, 25 pressure.