Abstract: A method of making hollow turbomachine components is disclosed. The method provides for an additive manufacturing step, wherein on a substrate the following are manufactured in sequence: a first terminal portion of a semi-finished component, said first terminal portion adhering to said substrate, an intermediate portion adjoining the first terminal portion, and a second terminal portion adjoining the intermediate portion. After cooling of the component, at least one of said first terminal portion and second terminal portion is removed. The removed terminal portion includes sacrificial features, where thermally induced deformations of the component are concentrated, or which are aimed at stiffening the component, such that deformations are reduced or prevented.

Abstract: A pump comprising an impeller having a hub base and an impeller body. The impeller body comprises a base which is concentric relative to a rotational axis of the impeller, and at least one eccentric apex.

Abstract: A tip shroud may include a platform to couple to an airfoil having a pressure side and a suction side. A front tip rail and a rear tip rail extend radially from the platform with each including a downstream side, an upstream side, and an origin(s). Each of the downstream side and the upstream side of the rear tip rail and the downstream side of the front tip rail has a shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, Z set forth in a respective table and originating at a selected origin. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, Z values by a minimum rear tip rail X-wise extent expressed in units of distance. The X, Y, Z values are connected by lines to define each respective surface profile.

Abstract: A blade for a turbo machine is provided. The blade for a turbo machine includes an airfoil body extending in a radial direction and including a suction side surface and a pressure side surface opposite to the suction side surface with respect to a circumferential direction extending across the radial direction, and a snubber structure including a first snubber element protruding in the circumferential direction from the suction side surface of the airfoil body and a second snubber element protruding in the circumferential direction from the pressure side surface of the airfoil body, wherein the first snubber element is connected to the suction side surface of the airfoil body by a concave curved first transition portion having a first radius, and the second snubber element is connected to the pressure side surface of the airfoil body by a concave curved second transition portion having a second radius, the first radius being smaller than the second radius.

Abstract: An exhaust chamber of a steam turbine according to an embodiment includes an outer casing which includes an end wall part in an axial direction and an extension part extending upward in the axial direction from the end wall part, a first flow guide formed into an annular shape, the first flow guide forming an upstream region of a diffuser surface in a hub-side flow guide and being fixed to an upstream end portion of the extension part on a radially inner side of the diffuser surface, and a second flow guide formed into an annular shape, the second flow guide forming a downstream region of the diffuser surface at a position downstream of the first flow guide and on a radially outer side of the extension part, and being fixed to the extension part.

Abstract: A tray-type fan impeller structure includes a plate body annularly disposed around a hub. The plate body has a connection side connected with the hub and a free side extending in a direction away from the hub. Multiple boss bodies are arranged on a top face or the top face and a bottom face of the plate body at intervals. By means of the boss bodies, the periodical noise problem caused by the conventional blades is improved.

Abstract: Provided is a supercharger (11) comprising: a hollow housing (15); a rotating shaft (14) rotatably supported by the housing (15); a turbine (12) provided at one axial end of the rotating shaft (14); and a compressor (13) provided at the other axial end of the rotating shaft (14). A threaded section (41) and a circular column section (42) are axially arranged at the other end of the rotating shaft (14). A threaded hole (43) with which the threaded section (41) is engaged and a fitting hole (44) in which the circular column section (42) is fitted are axially arranged in the compressor (13). The axial length of the circular column section (42) and the fitting hole (44) is set to be greater than the axial length of the threaded section (41) and the threaded hole (43).

Abstract: A centrifugal fan includes a housing, a hub and a plurality of blade sets. The housing includes an air outlet and at least one air inlet. The hub is rotatably disposed in the housing. The plurality of blade sets is arranged around the hub at intervals, and each of the blade sets includes at least three blades with different shapes.

Abstract: Disclosed are a bailer-type long-shaft pump (100) and an associated pump station (200). The long-shaft pump comprises a bailer vehicle (110), a long shaft (120), a bearing (130), a transmission device (140) and an electric motor (150). One end of the long shaft (120) successively passes through the bearing (130) and the transmission device (140) so as to be in transmission connection with a drive shaft of the electric motor (150). The pump station (200) comprises a pump station foundation (210), several equipment rooms (231) transversely distributed at intervals and constructed on the pump station foundation (210), and two ends of the long shaft (120) are supported on side walls of two adjacent equipment rooms. The bailer-type long-shaft pump achieve large water flow and low lift, the pump station is space-saving, has shorter construction cycle, and reduces investment and operation costs.

Abstract: An impeller for use in a centrifugal blower, the impeller includes a hub defining an axis of rotation for the impeller; a plurality of inclined blades, the plurality of inclined blades extending away from the hub; and a plurality of reverse inclined blades, the plurality of reverse inclined blades extending away from the hub. Each of the plurality of inclined blades are joined to an adjacent inclined blade at least in part by a reverse inclined blade.

Abstract: A centrifugal fan includes a housing and an impeller. The housing includes a sidewall, and the sidewall includes a tongue portion. The impeller includes a fan hub and a plurality of blades. The fan hub is rotatably disposed in the housing, and the tongue portion has an inner contour line on a reference plane. The blades connect to the fan hub. Each one of the blades has an end surface facing the sidewall. The end surface has an outer contour line on the section of the blade. Any two adjacent blades have different outer contour lines. The outer contour line of at least one first blade of the plurality of blades is parallel to the inner contour line. The outer contour line of at least one second blade of the plurality of blades is not parallel to the inner contour line.

Abstract: A rotor for a pump has a housing and a rotor, and has at least one blade. The rotor is able to be actuated to rotate about an axis of rotation in order to convey a fluid in the axial or radial direction, and the rotor is able to be deformed in the radial direction between a first, radially compressed state and a second, radially expanded state. At a maximum speed of rotation of the rotor at which the power of the pump is at a maximum, the blade is essentially radially oriented, and/or the rotor has its maximum diameter.

Abstract: A method of remanufacturing a turbine component is provided. This method includes removing a donor portion from a damaged component; removing a to-be-replaced portion from a serviceable component generally equivalent to the donor portion leaving a remainder; and welding the donor portion to the remainder. A BOAS for a gas turbine engine is also provided that includes a serviceable BOAS with a donor portion from a damaged BOAS welded thereto.

Abstract: A wind turbine including a plurality of substantially similar vertically extending blades with a semi-circular profile, wherein each of such blades is divided into two adjacent compartments; an upper plate; a lower plate; and an electric generator with a gear box. The wind turbine may also include a braking mechanism to control the rotational speed of the blades such that the produced electrical parameters are below the rated characteristics of the electric generator.

Abstract: A compressor wheel of a fluid compression device includes a wheel part, a shaft part and a plurality of connection parts. The wheel part includes a main body formed with a through hole, and a plurality of blades protruded from an outer side of the main body. The shaft part is accommodated in the through hole and configured to connect to a rotor shaft. The plurality of connection parts is connected between an inner side of the main body and the shaft part. Wherein, a fluid passage is formed between the inner side of the main body and the shaft part to allow fluid to flow to a rear side of the compressor wheel from a front side of the compressor wheel via the fluid passage.

Abstract: A semi-annular delta-airfoil is designed in conjunction with a fluid turbine rotor blade to provide increased rotor-tip speed, increased coefficient of power, reduced wind shear, reduced noise and increased self-yaw. A dual-winglet rotor blade in combination with a semi-annular delta-airfoil increases the above mentioned benefits by increasing the rotor-blade tip surface-area that is in contact with the area of increased fluid velocity over the semi-annular airfoil. Winglets on the semi-annular delta-airfoil provide self-yaw characteristics.

Abstract: A semi-ringed airfoil is designed in conjunction with a fluid turbine rotor blade to provide increased rotor-tip speed, increased coefficient of power, reduced wind shear and reduced noise. A dual-winglet rotor blade in combination with a semi-ringed airfoil increases the above mentioned benefits by increasing the rotor-blade tip surface-area that is in contact with the area of increased fluid velocity over the semi-ringed airfoil.

Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.

Abstract: The present invention relates to an air turbine capable of without change in its rotational velocity direction, efficiently absorbing the energy associated with a pressure difference between two spaces (A) and (B) of successively changing sign, as in the case of sea wave energy systems. The turbine comprises two sets of blades (I) and (II), each of which is similar to the blade system of a conventional turbine of radial-, mixed- or axial-flow type. The turbine also comprises a system of ducts that connect spaces (A) and (B) through any of the two blade sets (I) and (II). The turbine may be equipped with a fast-acting valve that stops the flow through one or both blade sets (I) and (II).

Abstract: A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.

Abstract: A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.

Abstract: A wind turbine having a set of curved blades mounted on a central rotatable huh. Each of the blades has a defined pitch angle, to a rotational axis of the hub, along the blade from the hub to the tip. A curve is provided on the wind contact surface along each of the blades over the blade surface from the leading edge of the blade to the trailing edge of the blade by an amount between about 6 and about 24 degrees. The defined pitch angle from any point along the leading edge of the blade being defined by the arc-sine of a ratio of blade velocity to apparent wind velocity, with a variance of ±30 percent of the complementary angle to the arc-sine; and apparatus for varying the velocity of the blade to control power output so that it is within fifteen percent of maximum obtainable power of the blade most distant from the hub.

Abstract: A gas or steam turbine is disclosed herein. The turbine may include a throat area formed between adjacent buckets. The turbine also may include a variable throat device associated with at least one of the adjacent buckets. The variable throat device may be configured to vary the throat area between the adjacent buckets for improved part load performance.

Abstract: A shroud assembly having rope seals disposed between the shroud hangers and the surrounding case structure.

Abstract: A heat-dissipation fan including a base and an impeller disposed at the base, wherein the impeller includes a plurality of first blades, a plurality of second blades and a plurality of connection ribs. Each of the first blades and each of the second blades are arranged alternately. Each of the connection ribs comprises a first edge, a second edge and a third edge. The first edge is connected with the first blade, the second edge is connected with the second blade, the third edge is connected with the first edge and the second edge, and the third edge and the second blade are spaced apart to form a first vent. The first edge comprises a first length, the second edge comprises a second length, and the first length is larger than the second length.

Abstract: Provided is a method of manufacturing an impeller assembly, the method including providing an impeller including: a rotary shaft; a base portion radially extending outward from the rotary shaft; and a plurality of blades extending radially outward from the rotary shaft and disposed on the base portion, each of the plurality of blades provided apart from one another in a circumferential direction around the rotary shaft; providing a mold in an area between the plurality of blades; and forming a shroud covering upper portions of the plurality of blades and an upper portion of the mold, wherein the forming the shroud comprises applying a melted metal on the upper portions of the plurality of blades and the upper portion of the mold.

Abstract: A fluid pump device, in particular for a medical application, is described having a compressible pump housing and rotor, as well as with a drive shaft which runs in a sleeve and on whose end the fluid pump is arranged. In order to utilize all possibilities of a space-saving arrangement of the respective pump housing of the rotor, which is compressible per se, and as the case a bearing arrangement, the mentioned elements are displaceable to one another in the axial direction compared to an operation position. In particular these elements may be end-configured by way of an axial movement of the drive shaft after the assembly.

Abstract: A fan for an engine ventilation system includes a housing defining an inlet and an outlet. A hydraulic motor is coupled to the fan housing and includes a motor housing, motor shaft, and shaft seal disposed between the motor housing and the motor shaft. An impeller assembly is disposed in the housing, as well as a stationary baffle that includes a baffle inner edge disposed axially between the impeller assembly and a second wall of the fan housing. A deflector disc is coupled to the impeller assembly and includes a deflector disc outer edge positioned axially rearward of the baffle inner edge. The deflector disc and baffle direct any hydraulic fluid leaking past the shaft seal away from the impeller assembly to a collection chamber.

Abstract: According to an aspect of an exemplary embodiment, there is provided a rotation body of a rotary machine, the rotation body comprising: an impeller comprising a blade; and a shroud that is integrally formed with the impeller and has a cladding stack structure in which a plurality of laser cladding layers are stacked.

Abstract: Disclosed are a shroud impeller of a centrifugal compressor and a method of manufacturing the same where the shroud impeller includes a rotary hub connected to a driving shaft, a plurality of blades radially provided about a rotational axis of the rotary hub, and an integral shroud bonded onto top ends of the blades.

Abstract: Various embodiments include a turbomachine bucket having a flow interrupter, as well as related turbomachines. Various embodiments include a turbomachine bucket having: a base section sized to couple with a turbomachine rotor, the base section having a leading edge and a trailing edge opposing the leading edge; a blade section coupled to the base section and aligned to extend radially from the base section; a shroud coupled to the blade section and aligned to extend radially from the blade section; and a flow interrupter coupled to the leading edge of the base section.

Abstract: Turbomachines having close-coupling flow guides (CCFGs) that are designed and configured to closely-couple flow fields of adjacent bladed elements. In some embodiments, the CCFGs may be located in regions extending between the adjacent bladed elements, described herein as coupling avoidance zones, where conventional turbomachine design would suggest no structure should be added. In yet other embodiments, CCFGs are located upstream and/or downstream of rows of blades coupled to the bladed elements, including overlapping one of more of the rows of blades, to improve flow coupling and machine performance. Methods of designing turbomachines to incorporate CCFGs are also provided.

Abstract: An impeller includes a substantially cylindrical cup portion arranged to rotate about a center axis, a plurality of blades fixed to an outer circumferential surface of the cup portion for unitary rotation with the cup portion to draw air from one axial side and discharge the air to the other axial side, and an annular connector portion arranged to interconnect the blades. The connector portion has a substantially cylindrical shape in a position spaced apart about 70% to about 90% of the radial length of the blades from the base of each of the blades on the outer circumferential surface of the cup portion, and the ratio of a total axial height of the connector portion to a total radial gap between the outer circumferential surface of the cup portion and the inner circumferential surface of the connector portion is equal to or smaller than about 0.9.

Abstract: A turbine rotor blade is provided. The turbine rotor blade includes an airfoil, an airfoil tip, a tip shroud, and a fillet about an intersection of the airfoil tip and the tip shroud. The fillet defines a fillet profile variable about the intersection as a function of aerodynamic airflow about the intersection.

Abstract: A turbine bucket shroud arrangement for a turbine system includes a contact region of a tip shroud, wherein the contact region is in close proximity to an adjacent tip shroud. Also included is a negative thermal expansion material disposed proximate the contact region, the contact region comprising a first volume during a startup condition and a shutdown condition of the turbine system and a second volume during a steady state condition of the turbine system, wherein the second volume is less than the first volume.

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 improved impeller for use in a centrifugal slurry pump is provided, comprising: a top shroud; a bottom shroud; and a middle portion therebetween, said middle portion having at least one substantially vertical wall defining a slurry flow channel, wherein the top shroud, bottom shroud and middle portion are configured as one piece to together define a first unitary body; at least one vane nose positioned at a leading edge of the at least one substantially vertical wall; and, optionally, a retaining ring mounted over the top shroud to secure the vane nose within the body.

Abstract: A bucket assembly includes a plurality of first buckets, and a pair of transition buckets. Each first bucket includes a bucket cover including a pair of lateral edges each having a first configuration. Each transition bucket includes a transition cover including a first lateral edge having the first configuration and a second lateral edge having a second configuration.

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 rotor blade for a turbine engine includes a first side that defines a first contact face with a hardcoat and a second side that defines a second contact face without a hardcoat.

Abstract: An impeller of a centrifugal pump is provided. The impeller includes at least two blades (4) for conveying media containing solids. An impeller blade leading angle (?1) is smaller than 0°. The blade angle (?) increases in a first section (9) until a value of 0° is reached. In a second section (10), another increase occurs until a maximum value is reached. In a third section (11), the blade angle (?) decreases again.

Abstract: A centrifugal fan includes a casing having an upper casing and a lower casing, and an impeller disposed between the upper and lower casing. The impeller includes an upper shroud having an upper portion formed with an inlet, a lower shroud, and a plurality of blades arranged along a circumference direction between the upper shroud and the lower shroud. The lower shroud is provided only on a portion at a side of a rotation axis of the impeller such that at least an outer circumferential side portion of each blade faces an upper surface of the lower casing. A surface of the lower casing, which faces the impeller, configures a portion of a wall surface which guides the fluid introduced from the inlet. Each blade has a shape which becomes thinner as increasing a distance from the upper shroud in a direction parallel to the rotation axis.

Abstract: A swimming pool water inlet generator operable to allow the generator to be attached to a swimming pool water inlet, a turbine assembly arranged and operable to generate electricity when water flows through the inlet and at least one electrically powered device operable to use the generated electricity in the operation thereof.

Abstract: A fan assembly includes a shrouded fan rotor having fan blades extending from a hub and rotatable about a central axis. A fan shroud extends circumferentially around the fan rotor and secured to the fan blades. The shroud includes a first axially extending annular portion secured to the fan blades, a second axially extending annular portion radially outwardly spaced from the first axially extending annular portion, and a third portion connecting the first and second axially extending annular portions. A casing is located circumferentially around the fan shroud defining a radial clearance between the casing and the fan shroud, and includes casing wedges extending from a radially inboard surface of the casing toward the shroud and defining a radial wedge gap between a first wedge surface and the shroud and an axial wedge gap between a second wedge surface and an upstream end of the fan shroud.

Abstract: The invention relates to a turbine engine including a stack of stages, each of which includes a cross-flow turbine and a generator, where each turbine-generator stage has an independent shaft, and wherein each stage is associated with an independent fairing (31-32) directing it with respect to a current, each fairing being of shroud type, with symmetrical profiled wings.

Abstract: An airfoil with a tip cover surface treatment for reducing leakage flows, minimizing tip vortex size and penetration into main flow that will improve turbine efficiency. The surface treatment for the airfoil tip covers includes a series of concave shapes, such as grooves or holes. These grooves and holes will cause the leakage flow into separate flow paths within the cavities and generate more resistance to leakage flows through the airfoil tip clearance, thereby reducing the leakage mass flow and weakening tip vortex and its interaction with turbine main flows. The material removed from the tip cover provides the additional benefit of reducing the weight of the tip cover, thereby enhancing blade reliability.

Abstract: Embodiments of the present disclosure are directed toward systems including a turbomachine blade tip shroud having a pressure side portion and a suction side portion. The pressure side portion and the suction side portion are divided by a mean camber line of a turbomachine blade, and the pressure side portion has a greater surface area than the suction side portion.

Abstract: A turbine blade assembly that is able to be driven by the wind, the turbine blade assembly comprising a hub, a multiplicity of hub blades attached to and extending outwardly from the hub, a first cowl attached to an end of the hub blades, wherein the first cowl is at an angle of between 9 and 15 degrees with respect to a central axis of rotation of the hub.

Abstract: The present invention relates to a fan wheel in a version as a radial or diagonal fan, of a baseplate and of a plurality of fan blades arranged so as to be distributed over the circumference of the inlet port and around an axis of rotation. The fan wheel has a shroud with an inlet port and the shroud and/or the baseplate have/has in this case a nonrotationally symmetrical geometry which in each case has a continuous and point-invariable profile, as seen in the axial or axially parallel direction.

Abstract: A wind turbine 10 includes a turbine wheel 14 that includes a circular air foil 22 surrounding the turbine blades 24, with the angle of attack 39 of the air foil directing some of the trailing air outwardly in a cone-shaped path to form an area of low air pressure that induces more rapid flow of atmospheric air through the turbine blades.