Abstract: An anti-relief fan frame body structure includes a frame body and multiple anti-relief sections. The frame body has a receiving space and a shaft seat received in the receiving space. The frame body further has multiple flow guide members extending from a circumference of shaft seat to an inner circumference of the frame body to connect with the inner circumference of the frame body. The anti-relief sections are disposed on the inner circumference of the frame body between the flow guide members to increase the performance of the fan.

Abstract: An improved guide vane for an inline fan is provided, as is an inline fan assembly so characterized. The vane guide includes a first vane segment characterized by first and second end portions, and a second vane segment characterized by first and second end portions. The second end portion of the first vane segment is in a spaced apart and overlapped arrangement in relation to the first end portion of the second vane segment. The first end portion of the first vane segment is an adjacent most vane guide end portion in relation to an impeller of the fan. The first vane segment is of arcuate configuration, with the second vane segment being of linear configuration.

Abstract: A centrifugal pump includes an electric motor, an impeller driven by the motor and a pump housing having an impeller chamber, an inlet in communication with the impeller chamber via an opening, and first and second outlets in communication with the impeller chamber. The impeller chamber has an interference structure which forms first and second flow channels in communication with the first and second outlets. The interference structure directs the fluid in the impeller chamber to flow through the first outlet via the first flow channel when the impeller rotates in a first direction or to flow through the second outlet via the second flow channel when the impeller rotates in the opposite direction.

Abstract: A stator subassembly includes an array of circumferentially arranged stator vanes. A damper spring is provided between the array and an outer case, which supports the array. The damper spring is configured to bias the array radially inwardly from the outer case.

Abstract: A pump for a dishwasher has an impeller for conveying fluid, wherein it is formed as a centrifugal pump with the fluid to be conveyed being sucked-in in a central axial manner and flowing out in a radial manner. The impeller extends on a bottom surface above a pump base, wherein several fixed flow directing blades are arranged radially outside the impeller, said flow directing blades extending in a helicoidal manner with the pitch extending in the rotational direction of the impeller away from the pump base. At least one flow directing blade extends as far as up to the bottom surface of the impeller for picking up a circulating funnel or tube produced of fluid with air bubbles therein.

Abstract: A stator subassembly includes an array of circumferentially arranged stator vanes. An attachment liner secures the stator vanes to one another to provide the subassembly. A damper spring is integral with the attachment liner and is provided between the array and an outer case, which supports the array. The damper spring is configured to bias the array radially inwardly from the outer case.

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

Abstract: A pump for a fluid which can be blood has a stator housing and a rotor hub with leading and trailing portions and an intermediate portion disposed therebetween. At least one impeller blade at the leading portion drives circumferential and axial components of a flow into a pump annulus or intermediate pathway portion. At least one stator blade extends radially inward from the stator housing within the intermediate pathway portion and is configured to reduce a circumferential component of the flow.

Abstract: The invention concerns a gas turbine engine component (27) comprising an outer ring (21), an inner ring (20), a plurality of circumferentially spaced elements (22) extending between the inner ring (20) and the outer ring (21), wherein a primary gas channel for axial gas flow is defined between the elements (22), wherein the component (27) has an inlet side for gas entrance and an outlet side for gas outflow, and an annular load transfer structure (23) positioned internally of the inner ring (20) for transferring loads between said elements (22) and a bearing structure (24) for a turbine shaft (11) positioned centrally in the component (27), wherein the annular load transfer structure (23) extends circumferentially along at least a part of an inner side of the inner ring (20) and inwards in a radial direction of the component (27), wherein the annular load transfer structure (23) has a first portion (23a) and a second portion (23b), and wherein the first portion (23a) is located closer to the inner ring (20) t

Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, ?, and exit angles, ?. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, ?, and exit angle values, ?, set forth in one of Tables 1, 3, 5 and 7.

Abstract: A diffuser for an air cycle machine defines airflow both to a compressor rotor from the inlet and from the compressor rotor through a plurality of vanes that define radially extending airflow passages. The size and shape of both the inlet and the vanes of the diffuser define and tailor the character of airflow presented to and leaving the compressor rotor to provide a desired change in air flow.

Abstract: A turbine section of a gas turbine engine is provided. The turbine section is annular about a longitudinal axis and includes first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine; and a first guide vane disposed within the inter-turbine duct.

Abstract: According to one aspect, a turbine assembly includes a second component circumferentially adjacent to a first component, wherein the first and second components each have a surface proximate a hot gas path and a first side surface of the first component to be joined to a second side surface of the second component. The assembly also includes a first slot formed longitudinally in the first component which extends from a first slot inner wall to the first side surface and a second slot formed longitudinally in the second component which extends from a second slot inner wall to the second side surface. The assembly also includes a first groove formed in a hot side surface of the first slot, the first groove extending from the first slot inner wall to the first side surface, wherein the first groove comprises a tapered cross-sectional geometry.

Abstract: The present application provides a radial diffuser exhaust system for use with a gas turbine engine. The radial diffuser exhaust system may include a radial diffuser positioned within an asymmetric exhaust collector. The asymmetric exhaust collector may include a closed end chamber and an exhaust end chamber. The closed end chamber may have a first size, the exhaust end chamber may have a second size, and the first size may be smaller than the second size.

Abstract: A gas turbine engine includes a centrifugal compressor having an improved impeller structure. The impeller structure includes a near axial discharge configuration thus reducing the overall size of the envelop surrounding the compressor assembly. The impeller structure may have axial exit vanes.

Abstract: This girder (8) for supporting a tidal turbine fairing has a parallelogram-shaped cross-section (S), taken perpendicularly to a longitudinal axis (A8) of the girder (8). It includes at least one slot (86a, 86b) extending generally parallel with the longitudinal axis (A8) of the girder (8). a cross-section (S) taken perpendicularly to the longitudinal axis (A8) of the girder (8), the traces of the surfaces bordering the slot (86a, 86b) extend from one of the long sides (801, 803) of the cross-section (S) to an adjacent short side (802, 804) of the cross-section (S).

Abstract: A vane assembly for a gas turbine engine includes a first vane and a second vane. The first vane and the second vane include an inner platform, an outer platform and an airfoil that extends between the inner platform and the outer platform. The first vane and the second vane are attached at least at one of their inner platforms or their outer platforms with a first attachment mechanism and a second attachment mechanism.

Abstract: A turbine exhaust case for a turbofan engine comprises a plurality of arcuate acoustic panels assembled into a circumferentially extending inner shroud with circumferential gaps between adjacent acoustic panels. An outer shroud extends circumferentially about the inner shroud. The inner shroud and the outer shroud define an annular gaspath therebetween. A plurality of circumferentially spaced-apart exhaust struts extends radially across the annular gaspath and structurally connects the individual acoustic panels forming the inner shroud to the outer shroud.

Abstract: The present disclosure relates to a grill for an air circulator. The grill is configured to divert airflow from an airflow source. The air circulator includes a center hub with a plurality of arcuate ribs coupled to and extending outwardly from the center hub. The arcuate ribs extend outwardly to an outer perimeter of the circular grill.

Abstract: A fluid turbine apparatus which is able to increase the fluid velocity and consequently increase the rotation speed of the fluid turbine. The fluid turbine apparatus has a convergent section, a fluid turbine section and a divergent section. The fluid enters into the fluid turbine through the convergent section, passes through the fluid turbine and exits through the divergent section. The combination of the convergent section and the divergent section creates a Venturi effect and increases the fluid velocity and thus the energy density entering turbine for increasing the energy extracted by the turbine.

Abstract: A centrifugal fan with a pot-like impeller and with a housing, having a first circumferential wall region with an arc-like curvature which extends directly along the impeller. The housing includes in a direction of rotation of the impeller a second circumferential region with a radial distance from the impeller increasing spirally up to an outlet region. The housing includes in an opposite direction a third circumferential wall region extending to the outlet region, having an S-curvature and including a sub-region curved in the same direction as the first circumferential wall region forming a flow baffle element. Two side walls cover the axial end faces of the impeller wherein one of the side walls extends into the pot-like impeller and divides its interior into a first suction chamber having an intake and a second suction chamber. The outlet region expands in cross-section in the outlet flow direction.

Abstract: Disclosed is an axial blower that comprises a substantially circular cylindrical blower pipe wherein, in the blower pipe, a blower stator is provided that includes a central construction arranged in the blower pipe and a number of guide blades being disposed downstream of the blower rotor to the effect that they are, at their proximal ends, secured to the central construction and, at their distal ends, securely mounted to the inner side of the blower pipe, whereby the guide blades and the central construction are secured relative to the blower pipe. The central construction includes a number of separate stator segments that are mutually secured to each other; and wherein each of the guide blades is configured as an integral unit along with one of the stator segments.

Abstract: An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, defining a mean span therebetween. An inner endwall defines an inner endwall contour extending axially and circumferentially from the root section, and an outer endwall defines an outer endwall contour extending axially and circumferentially from the tip section. The inner and outer endwall contours are defined by varying radial deviations from circumferentially uniform nominal inner and outer radii, where one of the radial deviations varies axially and circumferentially by at least three percent of a mean span of the airfoil.

Abstract: Fan tray assemblies for cooling electronic devices in data processing units are described herein. In some embodiments, an apparatus includes a fan tray and a stator member. The fan tray is configured to be mounted within a data processing unit, and defines an opening. The fan tray is configured to be coupled to a fan such that the fan and the opening collectively define a portion of an air flow path. The stator member includes multiple stator blades. The stator member is separate from the fan and configured to be coupled to the fan tray such that the stator blades are within the air flow path.

Abstract: A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.

Abstract: A strut for application between an outer ring and an inner ring in a gas turbine structure and a gas turbine structure including such a strut are provided. The strut includes an end portion which has a diverging shape so that an internal space is formed in the end portion for receiving at least part of an engine mount. Engine mounting lugs can be positioned at such struts.

Abstract: A fixed vane section for a gas turbine engine includes an anti-rotation slot that receives a pin for maintaining a desired position while providing for movement encountered during operation. The example anti-rotation slot includes a compound radius on inner surfaces to reduce stresses encountered during operation.

Abstract: Humidifying apparatus includes a humidifier for emitting moist air into an external environment, and a fan assembly for generating an air current within the external environment for conveying the emitted moist air away from the humidifier. The fan assembly includes a device for creating an air flow and a nozzle including an interior passage for receiving the air flow and a mouth for emitting the air flow. The humidifier is located behind nozzle, the nozzle extending about and defining an opening through which both air from outside the nozzle and the moist air emitted from the humidifier are drawn by the air flow emitted from the mouth.

Abstract: Fan downstream guide vane profiles have an optimized form of skeleton line angle distribution in an area situated between an upper and a lower limitation as well as a specific thickness distribution superimposed on the respective skeleton line angle distribution. Such guide vanes are characterized by lower pressure losses and a larger working range than the known downstream guide vanes, thereby reducing fuel consumption of the engine and increasing the operating stability thereof.

Abstract: The strut is for use in a gas turbine engine has body, typically having an airfoil shape, having a leading edge and a trailing edge. The leading edge has at least one gas inlet in direct fluid communication with at least one outlet located in the trailing edge through which gas may be redirected from the leading edge to the trailing edge through the strut for injection back into a wake region downstream of the strut.

Abstract: A method and apparatus for reducing a selected tonal noise generated by a fan operating in a non-uniform flow by locating at least one obstruction in the non-uniform flow such that the at least one obstruction generates a noise that is out of phase with the selected tonal noise. The noise generated by the at least one obstruction interferes with the selected tonal noise, thus reducing the selected tonal noise. It is also contemplated to use additional obstructions to reduce other tonal noises generated by the fan.

Abstract: An aircraft jet engine with a longitudinal axis, including a wall enclosing a gas flow ejected from a downstream end of the wall in the longitudinal axis, plural ducts being distributed around the periphery of the downstream end of the wall each including a terminal section, including an outlet opening. Each duct can eject a fluid jet through the outlet opening thereof. The ducts are configured to eject the fluid jets essentially parallel to each other, each fluid jet ejected through the corresponding outlet opening forming a lateral angle with the longitudinal axis in a projection view in a plane with the longitudinal axis.

Abstract: A hydrokinetic turbine system, including a plurality of hydrokinetic turbines is installed on a bed of a body of water. Each turbine has a shroud with a forward entrance portion and rear exit portion. The shroud includes a propeller disposed in a middle portion thereof. An inner surface of the shroud includes a plurality of rifling vanes formed therein to induce water entering the forward entrance portion to rotate in a vortex-like fashion. A plurality of pre-spin guard blades disposed adjacent the forward entrance portion also induce rotation of water and serve to provide a barrier preventing objects from passing into the forward entrance portion. A plurality of stabilizers extending from an exterior surface of the shroud that position the forward entrance portion in the direction of current flow.

Abstract: A diffuser divider shaped as disc with a central axis, a leading edge disposed at an inner radius about the central axis, a trailing edge disposed at an outer radius about the central axis, an upper surface disposed between the leading edge and the trailing edge, a lower surface disposed between the leading edge and the trailing edge and one or more mounting features configured to mount the disc in a diffuser section configured to receive air compressed by two compressor wheel faces and to direct the compressed air to a volute. Such a divider can define throats in a diffuser section of a compressor assembly. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A gas turbine compression system (1) comprising a gas channel (5), a low pressure compressor section (8) and a high pressure compressor section (9) for compression of the gas in the channel and a compressor structure (14) arranged between the low pressure compressor section (8) and the high pressure compressor section (9). The compressor structure (14) is designed to conduct a gas flow in the gas channel and comprises a plurality of radial struts (15,16,21,24,25) for transmission of load, wherein at least one of the struts (15,16,21,24,25) is hollow for housing service components. The compressor structure (14) is arranged directly downstream of a last rotor (10) in the low pressure compressor section (8) and designed for substantially turning a swirling gas flow from the rotor (10) by a plurality of the struts (15,16,21,24,25) having a cambered shape.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of the profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: A turbine exhaust diffuser adjustment system for a gas turbine engine capable of altering the flow of turbine exhaust gases is disclosed. The turbine exhaust diffuser adjustment system may be formed from one or more flow ramps positioned in a flowpath. The flow ramp may include a downstream, radially outward point that extends radially outward further from the ID flowpath boundary than an upstream, radially outward point that is positioned upstream from the downstream, radially outward point. The flow ramp may be adjustable such that an angular position of a radially outer surface of the flow ramp may be adjusted relative to the ID flowpath boundary, thereby enabling the flowpath to be changed during turbine operation to enhance the efficiency of the turbine engine throughout its range of operation.

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: An air diffuser device suitable for use in an air diffuser system for a centrifugal pump the pump including a pump casing with a pumping chamber therein, an impeller mounted within the pumping chamber for rotation about a rotation axis, the impeller including a front side and a rear side. The air diffuser system comprises one or more passages extending through the impeller from the front side to the rear side, the or each passage having a first opening at the rear side and a second opening at the front side of the impeller.

Abstract: A cleaning system for a combine harvester that includes a cleaning shoe having a sieve, a cleaning fan, an air plenum and a pair of air diverters is provided. The cleaning fan is rotatably driven for generating a flow of air and positioned within the air plenum. The air plenum extends across the entire length of the cleaning fan and includes an inlet for the intake of air, an outlet downstream the inlet for directing the flow of air in a first direction, lateral walls forming a portion of the outlet, and a bottom wall extending between the lateral walls. The pair of air diverters extends inwardly from the lateral walls. Each air diverter is configured substantially as a pyramid having a rounded corner that extends inwardly from the lateral wall and upwardly from the bottom wall.

Abstract: A blower includes an electric motor having a shaft, a housing having an inlet and outlet between which is defined a gas flow path, the outlet structured to direct gas exiting the blower in an axial first direction, a first impeller attached to the shaft and adapted to accelerate air tangentially and direct it radially outward, a stationary portion, and a shield. The stationary portion includes a first stator vane structure defining a plurality of stator vane leading edges and a stator vane outer radial edge. The first stator vane structure is arranged to direct gas flow along a curved path that directs flow at an inner end thereof in a radially inward direction. The shield has an outer edge extending radially beyond the outer radial edge of the first stator vane structure and is adapted to isolate the stator vane leading edges from an impeller blade pressure pulse.

Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

Abstract: An exhaust gas diffuser for a gas turbine generally includes an inner wall that extends along an axial centerline of the exhaust gas diffuser. An outer wall is coaxially aligned with the inner wall. The outer wall is radially separated from the inner wall so as to define a flow passage therebetween. An airfoil shaped strut is disposed in the flow passage. The strut extends between the inner and the outer walls. The strut includes a leading edge and a trailing edge positioned relative to a direction of flow through the flow passage. The leading edge and the trailing edge are tapered from the inner wall to the outer wall in the direction of flow through the passage.

Abstract: A fan diversion structure comprises at least one deflector and at least one connecting part. The deflector, which is adapted to be disposed across front of an air outlet of the fan, is disposed on one side next to a center of the fan and without overlapping the center of the fan, wherein the deflector extends outwardly so as to deflect an airflow to the side direction of the fan. The connecting part is adapted for connecting the deflector to the fan. The fan is a ceiling fan, the connecting part is a hollow annular board corresponding to a circular structure of the ceiling fan, the deflector further comprises two joint poles extending from the connecting part, and the joint poles are respectively connected to two sides of the deflector and near to the center of the fan.

Abstract: An arrangement with a ring diffuser for an axial turbomachine, for example for a gas turbine, is provided. The ring diffuser includes an outer wall and with an inner wall coaxial thereto, between which a diffuser duct extends in ring form along an axial extent so as to diverge from an inflow-side end to an outflow-side end, the inner wall and the outer wall in each case including a wall surface delimiting the diffuser duct. In order to specify a diffuser duct which is adapted to an inflow uneven along the circumference and by means of which a specially efficient conversion of kinetic energy into static energy is possible, the wall surface which delimits the diffuser duct on the inlet side is rotationally asymmetrical.

Abstract: A ring diffuser for an axial turbomachine is provided. The ring diffuser includes an outer wall and an inner wall coaxial thereto, between which a diffuser channel extends in a ring shape along an axial extension from an inflow-side end diverging to an outflow-side end, wherein the inner wall and the outer wall each include a wall surface bounding the diffuser channel. In order to specify a diffuser channel that is tailored to an inflow that is uneven along the circumference and that facilitates a particularly efficient conversion of kinetic energy into static energy, a rotationally asymmetric wall surface bounding the diffuser channel on the inlet side is provided.

Abstract: A pumping apparatus comprises a rotatable shaft coupled to a motor. At least one control structure is mounted on the shaft, and at least one impeller is carried by the shaft. The impeller is adapted to rotate independently of the shaft so as to pump a fluid. The apparatus also comprises a magnetic coupling between the control structure and the impeller. Further, the impeller is adapted to translate axially along the shaft in response to a change in downstream pressure to alter the strength of the magnetic coupling.

Abstract: A wind turbine is provided with turbine blades mounted for axial rotation about an axis. The blades are surrounded by a shroud to define an axial air passage. Plates are attached to the shroud at a position radially outward from the shroud forming an air passage between the shroud and the plates. The plates have gaps between the adjacent plates so that air exiting the downstream opening of the shroud and air moving through the axial air passage between the shroud and the plates are mixed and a portion of the mixed air exits through the gaps.

Abstract: A heat dissipation device includes an axial-flow fan and an air guider. The axial-flow fan has an air inlet and air outlet. The air guider is connected to the air outlet and includes an air input section, an air output section, at least an air divider and at least an arc air divider. The air input section has an area smaller than that of the air outlet. The air output section has an area smaller than that of the air input section. The air divider is located within the air output section to divide the air output section into a plurality of air output channels. The arc air divider is located within the air guider.

Abstract: A fan assembly for creating an air current includes a nozzle mounted on a base. The base comprises an outer casing, an impeller housing located within the outer casing, the impeller housing having an air inlet and an air outlet, an impeller located within the impeller housing and a motor for driving the impeller to create an air flow through the impeller housing. The nozzle includes an interior passage for receiving the air flow from the air outlet of the impeller housing and a mouth through which the air flow is emitted from the fan assembly.