Abstract: A centrifugal fan and a dryer, where the centrifugal fan includes a shell, a driving mechanism, an impeller and a volute tongue arranged in the shell, the driving mechanism is connected with the tongue and can drive the tongue to rotate between a first limit position and a second limit position, the tongue includes a first volute tongue part and a second volute tongue part; when the tongue is located at the first limit position and the impeller rotates forwards, the first tongue part abuts against the inner wall of one side of the shell in a sealed mode, the second tongue part can cut the air blown by the impeller, and when the tongue is located at the second limit position and the impeller rotates reversely, the first tongue part can cut air blown by the impeller.

Abstract: A turbocharger turbine wheel can include a hub that includes a rotational axis, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system that includes a radial coordinate (r) and an azimuthal coordinate (?) in a direction of intended rotation about the rotational axis; and blades that extend outwardly from the hub, where each of the blades includes a hub profile, a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the hub profile includes a global maximum radius and a global minimum radius, and where, between the global maximum radius and the global minimum radius, in an axial direction from the backdisk to the nose, the hub profile includes a local minimum radius at a first axial coordinate position and a local maximum radius at a second axial coordinate position.

Abstract: A moving blade for a wheel of an aircraft turbine engine, including an aerodynamic aerofoil and an outer heel defining the aerofoil. The heel includes a platform and a first lip that projects from the platform. The first lip is inclined upstream and peripherally along an axis of elongation. The heel includes a row of ribs that are arranged at a distance from each other. The row of ribs extends along the axis of elongation and from the platform up to the first lip. The ribs are arranged upstream of the first lip in such a way as to generate turbulence upstream of first lip.

Abstract: A compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.

Abstract: A fan wheel (1) has a bottom disc (4), a cover disc (3) and impeller blades (2) arranged around a rotation axis (RA) of the fan wheel (1). The blades, in each case, extend over a blade length from a blade leading edge (5) to a blade trailing edge (6). The impeller blades (2) are divided into a front section (10), rear section (12) and transition section (11). The front section (10), extends proceeding from the blade leading edge (5) in the direction of the blade trailing edge (6). The rear section (12) extends proceeding from the blade trailing edge (6), in the direction of the blade leading edge (5). The transition section (11) forms a transition between the front section (10) and the rear section (12). The impeller blades (2) are formed with opposite curvature in the course from the bottom disc (4) to the cover disc (3) in the front section (10) and the rear section (12).

Abstract: Assemblies and inserts are provided for evenly heating a smokable substance. A hookah bowl insert is provided for heating a smokable substance. The insert has a central core having at least one passageway extending therethrough. The insert further has a plurality of radial extensions extending in a radial direction from the central core. The radial extensions may be for gripping the smokable substance therebetween, and each radial extension has a vertical extension extending in a direction perpendicular to the radial direction. The insert is formed from a heat conductive material, such that heat is distributed across the insert, and within the individual radial and vertical extensions. Each vertical extension has a thickness larger than a thickness of the insert at the central core. As such, the vertical extensions can maintain stable temperatures and transfer heat to and from the smokable substance located therebetween.

Abstract: A heat dissipation fan including a housing, a hub, and a plurality of blades is provided. The hub is rotatably disposed in the housing. The blades are disposed at a surrounding edge of the hub to be rotated with the hub. When the heat dissipation fan is operated, at least one flow path is formed by two adjacent blades, and the flow path has a reduction section away from the hub.

Abstract: Systems can be used to harness energy from winds. For example, this document describes scalable systems having multiple wing-like blades that can efficiently convert wind power into electricity and other types of energy.

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a seal segment and an attachment unit. The seal segment includes an arcuate shroud wall that extends circumferentially partway around an axis and a mount post that extends radially outward away from the shroud wall. The attachment unit includes a first carrier and a second carrier that cooperate to define a channel that receives at least a portion of the mount post.

Abstract: A turbine blade includes a blade body in which a suction side (51) facing one side in a circumferential direction and a pressure side (52) facing the other side in the circumferential direction are connected at a leading edge and a trailing edge; and a shroud provided at a tip which is a radially outer end portion of the blade body. The shroud includes a shroud body having an outer circumferential surface facing radially outward, a front end surface extending to both sides in the circumferential direction with a leading edge side of the blade body as a reference point (P1), a rear end surface extending to both sides in the circumferential direction with a trailing edge side of the blade body as a reference point (P2), and a contact surface provided on both sides in the circumferential direction, and a reinforcing portion which protrudes from the outer circumferential surface.

Abstract: Disclosed is an air conditioner that suppresses generation of leakage vortices between a fan and a shroud. An air conditioner according to an embodiment of the present invention includes: an axial fan for blowing air; a shroud partially surrounding a circumference of the axial fan to guide air blown by the axial fan; and a fence ring provided in an inner surface of the shroud and protruding in a radial direction from the inner surface of the shroud. In addition, the fence ring is disposed between a downstream end of the axial fan and a downstream end of the shroud.

Abstract: A turbine rotor blade assembly in which values A, CF, T, and L are set to satisfy the following expression in two-dimensional coordinates, 1.2×105?(A×CF)/(T×L)?17×105, where (A×CF)/(T×L) is an expression (1), A is an arm length [mm] of each of turbine rotor blades, CF is centrifugal force [kgf] occurring on each of the turbine rotor blades, T is a thickness [mm] of each of shrouds, and L is a lap amount [mm] of the shrouds adjacent to each other.

Abstract: A method of manufacturing a turbo-machine impeller, which includes a hub and a plurality of blades, using powder material in an additive-manufacturing process. The method includes: applying energy to the powder material by way of a high energy source, and solidifying the powder material. At least one bulky portion of the hub is irradiated such that the powder material solidifies in a lattice structure surrounded by an outer solid skin structure enclosing the lattice structure.

Abstract: In one aspect, a fan assembly is provided that includes a plurality of elongated metallic fan blades, a first metallic end ring, a second metallic end ring, and a metallic hub support connected to the fan blades intermediate the first and second end rings. The fan blades include straight inlet edges radially inward from first and second radially inner edges of the first and second metallic end rings so that inlet portions of the blades extend radially inward from the first and second metallic end rings. In another aspect, a fan assembly is provided that includes a hub support having a hub strip and a hub ring. The hub strip has an elongate configuration with an attachment portion connected to the hub ring at one end of the hub strip and another attachment portion connected to the hub ring at an opposite end of the hub strip.

Abstract: An axial fan comprises an impeller. The impeller comprises a hub and a plurality of blades disposed on an outer circumference of the hub. A pressure surface of each of the blades is at least partially a convex surface bulging from a suction surface side to a pressure surface side. The convex surface is provided within a predetermined region of the pressure surface of the blade on a hub side. The predetermined region is arranged as part of a radial width of the blade.

Abstract: An impeller shroud for a mechanical system has a hyperboloid shape with a rim at the air-inlet end. The face of the inlet rim is perpendicular to the flow direction. A plurality of slots through which air is allowed to pass is disposed symmetrically about the rim. A plurality of solid areas extends along the circumference of the rim between the adjacent slots. The ratio of the sum of the plurality of slots in degrees and the sum of the solid areas in degrees disposed about the rim is between 3:1 and 11:1.

Abstract: An impeller in which a plurality of vanes are provided so as to overlap each other back and forth as viewed in the direction of axis has a first impeller part on a front side and a second impeller part on a rear side. A method for manufacturing impeller includes a step of molding a first impeller part, a step of molding a second impeller part and a step of combining together the first impeller part and the second impeller part.

Abstract: A centrifugal fan introducing air via an inlet port in a direction of a rotation axis and discharging the air via an outlet port in the a direction of a centrifugal force produced by rotation includes: an impeller having a plurality of vanes around the rotation axis; and a housing including the inlet port and supporting the impeller such that the impeller is allowed to freely rotate in the housing. An inclined portion is formed at least at a part of edge portion of the inlet port, the inclined portion widening to the side that the impeller is disposed.

Abstract: A fan includes a motor and an impeller. The motor includes a stationary portion and a rotating portion rotatably supported by the stationary portion. The stationary portion includes a stator and a bearing portion arranged inside of the stator. The rotating portion includes a rotor magnet arranged radially outside the stator; a shaft inserted in the bearing portion, and having an upper portion fixed to the impeller directly or through one or more members; and a thrust portion arranged axially opposite the bearing portion, and including an annular surface arranged around the shaft.

Abstract: A turbomachine apparatus for driving a compressor is disclosed. The turbomachine apparatus contains at least one rotor stage and at least one retaining element. The at least one rotor stage contains a plurality of blades and is configured to rotate about an axis. The at least one retaining element is configured to retain the at least one rotor stage with the blades thereof at least partly or wholly in radial compression during rotation thereof.

Abstract: Shrouded turbine blisks and methods of manufacturing same are provided. A shrouded turbine blisk includes a central disk portion including an axis of rotation, an inner rim, a plurality of airfoils that extends radially outwardly from the inner rim; and a shroud integrally coupled to each of the plurality of airfoils. The shroud includes a plurality of circumferentially-arranged arcuate shroud segments defined at least in part by gaps positioned between adjacent shroud segments. The central disk portion, the inner rim, the plurality of airfoils, and the shroud are defined from a single billet of blisk material.

Abstract: An impeller for a turbo-machine and is provided. The impeller includes a metallic base having a central hole, a back surface and a front surface opposite to the back surface; at least one blade extending on the front surface of the metallic base; a composite shroud attached to the at least one blade such that plural closed paths or vanes are formed by the front surface of the metallic base, the at least one blade and the composite shroud; and a connector configured to attach the composite shroud to the metallic base or the at least one blade.

Abstract: A gas turbine engine airflow member including a blade core portion, a shroud tip portion extending from the blade core portion, and an airfoil portion formed exteriorly to the blade core portion, where the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion is constructed as a second structure. A method of forming a gas turbine engine component is also disclosed.

Abstract: A turbine shroud for a gas turbine engine includes a metallic support ring and a ceramic blade track. The blade track is formed from a plurality of blade track segments including dovetail posts. The dovetail posts are inserted through apertures in the support ring and are coupled to the support ring by segment retainers coupled to the dovetail posts providing a retention system for the ceramic blade track.

Abstract: A fan rotor has a plurality of blades arranged circumferentially about a central axis, wherein the plurality of blades extend between 2.9980 and 3.0020 inches radially from the central axis. The fan rotor has a root portion arranged radially inward from the plurality of blades. The fan rotor also has a web portion that connects the plurality of blades to the root portion, the web portion having a minimum longitudinal thickness between 0.2000 and 0.2100 inches.

Abstract: A gas turbine engine bladed component, such as a turbine blade, is shown as including a shroud located above a blade portion and a stiffener located above the shroud. The stiffener is generally located in a central interior region of the shroud and includes a raised portion that extends above a top surface of the shroud. In one non-limiting form the stiffener can have a central ridge that is oriented in an axial direction. Seal members can be included in the shroud that can be used to interact with corresponding seal members in static gas turbine engine structure to discourage a flow of fluid. In one form the shroud includes an upturned leading edge portion.

Abstract: An impeller includes a shell having a plurality of blades. The shell may also define a cavity. The impeller may further include a backplate that engages at least a portion of the shell. The backplate can include a post which can be coupled to the impeller through a fastener such as a threaded nut. The backplate can be thereafter clamped to the impeller shell. Seals can be provided in the impeller, such as in the backplate. The backplate and impeller shell can be piloted onto each other. In some forms splines can be used to secure the backplate to the impeller shell.

Abstract: An apparatus includes a composite gas turbine engine multi-airfoil blade that includes first and second circumferentially spaced adjacent composite airfoils coupled together via a common composite attachment. The common attachment does not employ a fastener. The composite multi-airfoil blade may have a unitary construction having a ceramic matrix composition.

Abstract: A fan wheel (1) is designed as a radial or diagonal fan, comprising a top plate (2) with an inlet port (4), a base plate (6) and a plurality of fan blades (8) distributed around the inlet port (4) and around an axis of rotation (Z). Blade ducts extend (10) respectively between the adjacent fan blades (8). The blade ducts lead radially or diagonally outward from the area of the inlet port (4) and form blow-out ports in the outer region. The blade ducts (10) are designed, with respect to their effective flow cross-section, as large enough that during operation, a turbulent flow with a Reynolds number markedly greater than 2300 is achieved. The top plate (2) or the base plate (6) or both feature a rotationally asymmetrical geometry with a continuous profile, at least in angular sections encompassing the fan blades (8).

Abstract: Disclosed is a vacuum self-priming pump in which a main pumping chamber and a sub-pumping chamber divided from each other by a diaphragm are provided within a case, main impellers and a sub-impeller rotated by a motor are respectively installed within the main pump chamber and the sub-pumping chamber such that a space is formed between a pair of left and right main impellers, and connection pipes are respectively formed between suction pipes of the main pumping chamber and the sub-pumping chamber and between discharge pipes of the main pumping chamber and the sub-pumping chamber, so as to more rapidly suck fluid every pumping operation and to effectively pump the fluid without clogging even if the pumped fluid contains various sludge or solid matter.

Abstract: A gas turbine engine disk split retainer ring system is provided and includes an apparatus and method for retaining a split ring in relation to a turbine cover plate or disk. Pegs are used to capture and retain a split retainer ring of the gas turbine rotor in relation to the cover plate. An anti-rotation peg has a radially oriented tab for engaging the split ring so as to control the rotation of the ring. The system may be used to balance the operating condition of a turbo machine.

Abstract: A supersonic compressor rotor that includes a rotor disk that includes a substantially cylindrical endwall, a radially inner surface, and a radially outer surface. The endwall extends between the radially inner surface and the radially outer surface. A plurality of vanes are coupled to the endwall. The vanes extend outwardly from the endwall. Adjacent vanes form a pair and are spaced a circumferential distance apart such that a flow channel is defined between each pair of circumferentially-adjacent vanes. The flow channel extends generally radially between an inlet opening and an outlet opening. A first supersonic compression ramp is coupled to the endwall. The first supersonic compression ramp is positioned within the flow channel to facilitate forming at least one compression wave within the flow channel.

Abstract: A radial fan wheel arrangement includes a circular bottom plate (2) and a circular cover plate (3) with a central inflow opening (4), as well as wheel blades (6) running between the bottom plate (2) and the cover plate (3). Pocket-shaped recesses (9) are configured at least on one side of a plate surface in the space between the wheel blades (6) in an outer edge area of the cover plate (3) or the bottom plate (2) or both. At least one counterweight (13) is mounted on at least one of the two plates (2, 3) on a plate edge in an area of the pocket-shaped recesses (9).

Abstract: An impeller for use in a containment structure has a hub, a blade attaching to the hub for compressing air as the blade rotates with the hub, and an annulus disposed about the hub whereby the annulus reduces an effect of the hub breaking apart such that a weight of the containment structure is reduced.

Abstract: A sealless-type centrifugal pump includes a casing that forms a pump chamber having a liquid inflow port and an outflow port, an impeller disposed in the pump chamber and rotatably supported by a pivot bearing, and a magnetic coupling device including a driven permanent magnet built into the impeller and a driving magnet that rotationally drives the driven permanent magnet through a partition. The impeller supported in the direction of the rotation axis with respect to the casing is driven by the magnetic coupling device, and pressure is applied to liquid introduced from the direction of the rotation axis through the inflow port to send the liquid through the outflow port in a radial direction. The magnetic coupling device is disposed on a line inclined from an impeller rotating surface to the inflow port side toward the center of the rotation axis.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis and a shroud and a speed change device in communication with the fan.

Abstract: A sealless-type centrifugal pump includes a casing that forms a pump chamber having a liquid inflow port and an outflow port, an impeller disposed in the pump chamber and rotatably supported by a pivot bearing, and a magnetic coupling device including a driven permanent magnet built into the impeller and a driving magnet that rotationally drives the driven permanent magnet through a partition. The impeller supported in the direction of the rotation axis with respect to the casing is driven by the magnetic coupling device, and pressure is applied to liquid introduced from the direction of the rotation axis through the inflow port to send the liquid through the outflow port in a radial direction. The magnetic coupling device is disposed on a line inclined from an impeller rotating surface to the inflow port side toward the center of the rotation axis.

Abstract: A rotor stage of a turbine has a rotational axis, a shroud and radially inward thereof a turbine blade defined partly by a pressure side wall, a suction side wall and a tip portion. The tip portion has a pressure side tip rib and a tip cavity floor defining a tip cavity. The pressure side tip rib has a width Wps, a height Hps above the tip cavity and defines a tip gap Gps with the shroud. The pressure side tip rib has a sloping side joining the tip cavity floor and having an angle ?ps to a radial line ZZ. The width Wps is in the range Gps to 5Gps, the height Hps is in the range 5Gps to 15Gps and the angle ?ps is in the range 20° to 70°.

Abstract: A turbine blade (100) having an airfoil (1). In its radially outer region, the turbine blade (100) has at least one shroud (200) or at least one shroud segment, as well as at least one cutting tooth (300) which is intended to engage at least once into portions of a turbine casing during use of the turbine blade (100). The cutting tooth (300) is connected to the shroud (200) or the shroud segment.

Abstract: An attached duct propeller system may include at least one propeller blade having at least one blade tip. A duct having an inner wall may surround the at least one propeller blade. The at least one propeller blade may attach to the inner wall of the duct. In certain embodiments, the attached duct propeller system may include a propeller shaft attached to a bore of the at least one propeller blade. In certain embodiments, the at least one blade tip may be trimmed to allow alignment within the duct and allow for the attachment of the at least one blade to the inner wall of the duct. The attached duct propeller system may be used for vehicles that use at least one propeller for propulsion.

Abstract: A vertical centrifugal pump comprises a housing, impeller, annular guiding vanes, annular outlet with outer and inner casings, forming a collector with a pressure pipe, and flow channels to lower and upper rims. Channels to the lower rim pass through the center of the pump axis. Blades direct flow between pipes into the pressure pipe. Pipes are connected with the lower rim through the lower confuser with flat radial ribs, positioned with the inner part of the confuser from the pipes and the outer part from the inner casing to the lower rim. An annular baffle is implemented between the housing and outer casing, dividing the inlet to the rims. Channels to the upper rim are created between the two annular elements, connected by radial outer ribs with a thickened, streamlined form and mated with flat inner ribs, merged in the upper confuser similarly to the lower confuser.

Abstract: A pump having anti-airlock provisions. The pump is comprised of a volute comprised of a volute wall, and an impeller comprising back vanes on a side of the impeller that is proximate to the volute wall, with the back vanes having a length extending radially outwardly along the impeller. A bleed hole is formed in the volute wall in communication with the portion of the volute between the back vanes and the volute wall, and the exterior of the volute, such that the bleed hole is located midway along the length of the back vanes. When the pump is operating with air, liquid, or a combination of air and liquid in the volute, the bleed hole is under positive pressure with respect to the exterior of the volute. The bleed hole may be in communication with the exterior of the volute through a lateral tunnel formed in the pump.

Abstract: A turbine blade has a root portion, a platform and an aerofoil, the aerofoil is mounted on the platform and is formed by a pressure side wall and a suction side wall and has an outer surface, the pressure side wall and the suction side wall meet at a leading edge and a trailing edge, the aerofoil has an axial chord length, the suction side wall defines part of the radially outward surface of the aerofoil, the suction side wall defines art overhang, the overhang has a maximum overhang length that is between 5% and 20% of the axial chord length of the blade and is located between 5% and 50% of the suction surface length from the leading edge.

Abstract: A fan of a motor vehicle is particularly suited as a main fan of an internal combustion engine. The fan has a fan wheel with an outer ring which has a substantially L-shaped ring cross section. The L-shape is defined with a radial limb and an axial limb. The radial limb has a cross-sectional enlargement on a free-end side.

Abstract: A turbine rotor blade of the embodiment is made up of plural rotor blades each including: a blade effective part, a blade planting part, and a cover part, in which the cover parts adjacent in a turbine rotor circumferential direction are engaged with each other to make up an annular blade cascade. From among the rotor blades, a cover part of a stopping blade implanted to a planting part of the turbine rotor or the cover part of at least one of the rotor blades engaged with the cover part of the stopping blade is formed at the blade top part of the rotor blade so as to be able to be fitted when the rotor blade is installed in the turbine rotor.

Abstract: An omni-directional wind power harnessing device is disclosed. The device of the present invention includes a platform, a rotary mechanism and an output shaft. The platform has a plurality of channeling ducts, which are circumferentially provided around the platform. Therefore, wind blowing in any direction may be channeled into the platform. Each of the vanes has an arc shape and the vanes are circumferentially provided around the rotary mechanism with a tilted angle to prompt the rotary mechanism to rotate.

Abstract: A paddle wheel rotatable about an axis and exposed to radial inward and crosswise water flow has a hub on the axis and about which the wheel is rotated in a rotation direction about the axis and a plurality of angularly spaced blades spaced radially outward from the hub, forming spaces through which water can flow, and each formed by a plurality of radially spaced arcuate elements each in turn having a radially outer end and a radially inner end. These elements are each concave between the respective ends toward the incoming water flow with the radial outer ends more widely spaced than radial inner ends such that each element forms an acute angle with the adjacent element or elements and the spaces between the blades narrow in a direction of flow of water through them.

Abstract: A ring-type fan includes a frame having a receiving space defined between an air inlet and an air outlet thereof and being provided along an inner side of the air outlet with an inward projected wall portion; an impeller assembly rotatably mounted in the receiving space and including spaced impellers outward extended from a hub, and a ring member connected to radially outer ends of the impellers and externally provided with a circle of stop section, which and the projected wall portion together define an air passage between them; and at least one pressure relief section defining an airflow guide on the frame to communicate with the receiving space and the air passage. Any backflow can be guided out of the frame via the air passage and the pressure relief section without interfering with the inflow of air, allowing the ring-type fan to have upgraded heat dissipation performance.

Abstract: In one example, a turbocharger for an internal combustion engine is described. The turbocharger comprises a casing containing an impeller having a full blade coupled to a hub that rotates about an axis of rotation. The casing includes a bleed port and an injection port. The full blade includes a hub edge, a casing edge, and a first distribution of angles, each angle measured between the axis of rotation and a mean line at the hub edge at a meridional distance along the hub edge. The full blade includes a second distribution of angles, each angle measured between the axis of rotation and a mean line at the casing edge at a meridional distance along the casing edge. Further, various systems are described for affecting the aerodynamic properties of the compressor and turbine components in a way that may extend the operating range of the turbocharger.

Abstract: A centrifugal compressor provided with an impeller which is configured to have a plurality of blades arranged at a predetermined interval in a circumferential direction of a hub rotating together with a rotation shaft, in which a blade angle on a shroud side of the blade distributes to have a minimum value at a position between a leading edge of the blade and a midpoint of a camber line on the shroud side, and a maximum value at a position between the midpoint of the camber line on the shroud side and a trailing edge of the blade, and a blade angle of the blade on a hub side distributes so as to have a maximum value at a position between a leading edge and a midpoint of a camber line on the hub side.