Abstract: A wedge-type diffuser includes a diffuser floor and a plurality of wedge-shaped vanes. The wedge-shaped vanes extend from the diffuser floor and have a top surface, a leading edge and a trailing edge. Each of the wedge-shaped vanes has a slot extending from the trailing edge toward the leading edge.

Abstract: A system, in certain embodiments, includes a centrifugal compressor diffuser that includes an elliptical plate including multiple vane receptacles disposed about an axis of the plate and multiple detachable vanes attached to the plate. Each vane receptacle includes a first two dimensional (2D) projection along a plane of the elliptical plate and each detachable vane includes a second two dimensional (2D) projection along a base portion of the vane, where each detachable vane is disposed in a respective vane receptacle with the first and second 2D projections blocking movement of the detachable vane in at least a first axial direction relative to the elliptical plate. In certain embodiments, the first and second 2D projections may include a first tab to fit in a recess between a pair of second tabs, respectively, or vice versa. However, in other embodiments, the first and second 2D projections may include alternative mating surfaces.

Abstract: A floor standing pedestal fan for creating an air current includes a base housing an impeller and a motor for rotating the impeller to create an air flow, an air outlet, and a telescopic duct for conveying the air flow to the air outlet.

Abstract: A turbocharger unit (18) for an internal combustion engine (10) with at least one exhaust line (15, 16) for conducting exhaust gases away from the combustion chamber (11) of the engine and at least one inlet line (12) for supplying air to the combustion chamber. The turbocharger unit includes a turbine (17) which interacts with a compressor (19) for extracting energy from the exhaust gas flow of the engine and pressurizing the inlet air of the engine. The compressor (19) is of radial type and provided with an impeller with backswept blades (35) where the blade angle (?b2) between an imaginary extension of the center line of the blade between root section and tip section in the direction of the outlet tangent and a line (36) which connects the center axis of the impeller to the outer tip of the blade is at least roughly 45°. The turbine (17) which drives the compressor (19) is of radial type.

Abstract: A power turbine employs a plurality of turbine blades which allows the turbine to regulate pressure and ventilate for a greater ability to generate power without back pressure of the power source. It also relieves much of the stress on the uni-body construction. The vent ports (30) work at various times to transfer pressure naturally from one compartment to another, greatly increasing the balance of pressure throughout the process within the turbine.

Abstract: A diffuser pipe (38) of a compressor diffuser assembly (28) for gas turbine engines defines a depressed local area (58) in the pipe wall of an upstream section of the diffuser pipe (38). The depressed local area (58) is bent into the diffuser pipe (38) to reduce the accumulation of fluid boundary layer and improve stall margin of the diffuser pipe (38).

Abstract: A bypass turbojet engine including an outer fan duct and an inner fan duct (IFD), between which the secondary flow passes, and a high pressure compressor having an outer casing is disclosed. The IFD is fastened on the outer casing.

Abstract: In a high pressure centrifugal compressor, the occurrence of rotating stall noticeable in a comparatively-low specific speed wheel stage is prevented, thereby high efficient fluid performance is obtained and reliability is improved. The centrifugal compressor has a first vaneless diffuser with a constant flow channel height on the downstream side of an impeller, and a second vaneless diffuser in which the flow channel height decreases in a flow direction from an inlet to an outlet on the downstream side of the first vaneless diffuser. These diffusers are combined with an impeller using thick blades.

Abstract: In a multistage centrifugal compressor, a plurality of impellers is attached to the same rotary shaft. Vaned Diffusers and vaneless diffusers are used, as diffusers, for respective compressor stages configuring the compressor. The vaned diffusers are continuously used from the first compressor stage to the middle compressor stage, and the vaneless diffusers are used for the last compressor stage and the previous stage. While high efficiency is maintained at the compressor stages having the vaned diffusers, an operating flow range is secured at the compressor stages having the vaneless diffusers.

Abstract: A turbocharger having a variable nozzle with stepped two-stage vanes (50), the variable nozzle comprising a tubular piston (70) disposed in the bore (44) of the turbine housing (38) such that the piston (70) is axially slidable adjacent to the vanes (50) that extend across the nozzle. Each vane defines a first vane stage (50a) proximate the free end of the vane, the second vane stage (50b) having a different aerodynamic contour in comparison with the first vane stage (50a), each vane comprising a step (60) transitioning from the first vane stage (50a) to the second vane stage (50b). The piston (70) in a closed position closes the second vane stage (50b) so that exhaust gas flows only through the first vane stage (50a). The second vane stage (50b) is progressively opened as the piston (70) is axially slid toward an open position.

Abstract: A blower for a vacuum cleaner has a diffuser with an increased efficiency by coupling the attack angle A of the diffuser vanes with the attack angle B of the return guide vanes where angle A is between 4° and 6° and angle B is between 6° and 20°.

Abstract: A centrifugal compressor having a wide operating range, being economically efficient and high reliability in terms of a stable operation is provided. A centrifugal compressor including a partition wall for dividing a flow channel in the diffuser section and the volute section into a plurality of channels in the direction of circulation of the fluid so as to define a hub-side flow channel and a shroud-side flow channel; and a flow rate adjusting valve for lowering the flow rate of the fluid flowing in the shroud-side flow channel to increase the flow rate in the hub-side flow channel when the flow rate of the fluid compressed by an impeller is low and not lowering the flow rate of the fluid flowing the shroud-side flow channel to allow the fluid to flow both in the shroud-side flow channel and the hub-side flow channel when the flow rate of the fluid compressed by the impeller is high is employed.

Abstract: A diffuser-nozzle assembly mounted at the outlet from a centrifugal compressor is disclosed. The assembly includes a plurality of vanes carried by a radially inner wall forming a surface of revolution and surrounded by an outer casing, elastically deformable devices interposed between the radially outer ends of the vanes of the nozzle and the outer casing. The elastically deformable devices prevent air from passing between the outer casing and the radially outer ends of the vanes.

Abstract: An air guide apparatus includes a body installed at a discharge side of a rotary fan for sucking air, a plurality of first vanes arranged at one surface of the body to guide air sucked by the rotary fan toward the outer circumferential surface of the body, and a plurality of second vanes arranged on the other side of the body to guide air which has been guided by the first vanes from the outer circumferential surface of the body toward a central portion, formed in a spiral shape from the central portion of the body toward the outer circumferential surface of the body, and having disconnected portions formed at middle portions thereof.

Abstract: A variable nozzle for a turbocharger includes a plurality of vanes rotatably mounted on a nozzle ring and disposed in a nozzle flow path defined between the nozzle ring and an opposite nozzle wall. Either or both of the faces of the nozzle ring and nozzle wall include(s) at least one step that defines sealing surfaces positioned to be substantially abutted by airfoil surfaces of the vanes in the closed position of the vanes and to be spaced from the airfoil surfaces in positions other than the closed position. This substantial abutment between the airfoil surfaces and the sealing surfaces serves to substantially prevent exhaust gas from leaking past the ends of the airfoil portions. At the same time, clearances between the nozzle ring face and the end faces of the airfoil portions can be sufficiently large to prevent binding of the vanes under all operating conditions.

Abstract: A turbomachine comprising an annular combustion chamber (40) with injection orifices (44); a centrifugal compressor (10) having a centrifugal downstream stage and an annular diffuser (20) comprising: a radially-oriented upstream portion (21)with diffusion passages (22) connected to the outlet of the compressor and an elbow-shaped intermediate portion (24)and a downstream portion (25) comprising a series of flow-straightening vanes (26) and inclined relative to the axis (A) of the turbomachine. In the section plane containing the axis (A) of the turbomachine and passing via the center (C) of one of said injection orifices (44), the curvilinear abscissa distance along a flow line (L) between the middle (0) of the flow path at the trailing edges of the flow-straightening vanes (26) and said center (C) is greater than or equal to three times the height (h) of said flow path.

Abstract: The effective efficiency of a centrifugal compressor can be improved by achieving a uniform distribution of fluid velocity across the outlet end of a fluid passage of an axial diffuser for the centrifugal compressor and a high static pressure recovery ratio Cp in the axial diffuser passage. The cross section of each axial diffuser passage is configured such that a relatively high velocity fluid flow in an upstream part of the diffuser passage is directed toward a negative pressure side of a cross section thereof. It can be accomplished by directing a minor axis of a cross section of the diffuser passage substantially perpendicularly to a direction directed from a center of the cross section of the diffuser passage to the central axial line of an impeller or directing the minor axis toward the central axial line of the impeller.

Abstract: An airfoil diffuser for a centrifugal compressor formed by a diffuser passage area and a plurality of diffuser blades located within the diffuser passage area. The diffuser passage area is defined between a hub plate and a shroud of the centrifugal compressor. Each of the diffuser blades has a twisted configuration in a stacking direction as taken between the hub plate and an outer portion of the shroud located opposite to the hub plate. As a result of the twisted configuration, the diffuser blade inlet blade angle decreases from the hub plate to the outer portion of the shroud and solidity measurements at leading edges of the diffuser plates vary between a lower solidity value measured at the hub plate of less than 1.0 and a high solidity value measured at the outer portion of the shroud of no less than 1.0.

Abstract: A diffuser/guide vane assembly for an aircraft turbojet or turboprop engine is disclosed. The diffuser includes annular flanges joined by blades and the guide vane assembly includes cylindrical shelves joined by vanes. The annular flanges and the cylindrical shelves are formed from metal sheets to which the vanes are assembled by brazing.

Abstract: A wind turbine duct arrangement having a plurality of frusto-conical ducts each having an open apex and an open base defining an air intake, the ducts radially joined at their apexes to define a convergence zone wherein operatively rotating blades of a turbine may be installed transverse to the plurality of ducts. In use, the turbine duct arrangement provides a combination catchment and channelling area through the open bases of the plurality of ducts for channelling wind intake through the arrangement onto blades of a wind turbine transversely installed in the convergence zone defined by the radially joined apexes of the plurality of ducts.

Abstract: A technique improves the pumping performance of a centrifugal pump in a cost-effective manner. The centrifugal pump comprises a pumping component having one or more vanes defining fluid flow paths. A passage is formed through at least one vane such that an end of the passage is exposed to a low energy flow, i.e. secondary flow, region. Each passage enables the flow of a small amount of fluid from the low energy region to an opposite side of the vane to reduce the secondary flow effects and improve pumping efficiency.

Abstract: A turbine assembly for a variable-geometry turbocharger includes a turbine housing defining a divided volute having first and second scrolls, wherein the first scroll has a substantially smaller volume than the second scroll. The first scroll feeds exhaust gas to a first portion of a turbine wheel upstream of the throat of the wheel, while the second scroll feeds gas to a second portion of the wheel at least part of which is downstream of the throat. Flow from the second scroll is regulated by a sliding piston. The first scroll can be optimized for low-flow conditions such that the turbocharger can operate effectively like a small fixed-geometry turbocharger when the piston is closed. The turbine housing defines an inlet that is divided by a dividing wall into two portions respectively feeding gas to the two scrolls, a leading edge of the dividing wall being downstream of the inlet mouth.

Abstract: A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.

Abstract: A diffuser is provided having a number of diffuser channels defined by a top wall, bottom wall, and two sidewalls. The sidewalls can be constructed according to an involute of a circle which provides constant interwall distance between the sidewalls along the length of the diffuser channel. The top and bottom walls, however, diverge from one another along the length of the diffuser channel to provide a desired diffusion.

Abstract: An engine system incorporating an air breathing, reciprocating internal combustion engine having an inlet for air and an exhaust for products of combustion. A centripetal turbine receives products of the combustion and has a housing in which a turbine wheel is rotatable. The housing has first and second passages leading from the inlet to discrete, approximately 180°, portions of the circumference of the turbine wheel. The passages have fixed vanes adjacent the periphery of the turbine wheel and the angle of the vanes in one of the passages is different than those in the other so as to accommodate different power levels providing optimum approach angles between the gases passing the vanes and the blades of the turbine wheel. Flow through the passages is controlled by a flapper valve to direct it to one or the other or both passages depending upon the load factor for the engine.

Abstract: The nozzles are in the form of blowing-in openings in the housing wall which bounds the flow channel. The blowing-in openings are fed directly by means of air which is extracted from the flow channel downstream from the diffusor. This air is at a higher pressure than the flow in the flow channel upstream of the diffusor. This results in a passive, dynamic stabilization system for a compressor stage in the high pressure-ratio range, which does not require any additional control or actuating elements.

Abstract: A nozzle for radial inflow turbines having an outer surface having a concave shape, and an inner surface having a non-concave, i.e. straight or convex, shape. Also a leading edge may have a hole that is capable of receiving a fastener to secure the nozzle vane to an assembly housing.

Abstract: A centrifugal compressor includes an impeller and a diffuser, the diffuser having a plurality of descrete D-shaped passages intersecting each other.

Abstract: A compressor includes a compressor wheel, a diffuser and a device for the wet cleaning of the diffuser of a compressor, the diffuser being arranged downstream of the compressor wheel in the flow direction of the medium to be compressed. The device includes an arrangement for injecting a liquid, which is arranged in such a way that the liquid can be introduced, downstream of the compressor wheel, to the diffuser. The diffuser has at least partially a non-stick coating. A device of this type is suitable for removing deep-seated deposits from the surface of the diffuser.

Abstract: The present invention is directed to a pump casing and a centrifugal pump comprising a single piece casing, the casing comprising a first cut-water fluid flow path, a second cut-water fluid flow path, a first joint-water path, a second joint-water path, and an impeller cavity, the first cut-water fluid flow path and the second cut-water fluid flow path communicating with the first joint-water path and the second joint-water path, the pump further comprising an impeller positioned within the cavity, and a suction head overlaying the impeller. The first joint-water path communicates with a first discharge nozzle and the second joint-water path communicates with a second discharge nozzle, the first discharge nozzle and the second discharge nozzle situated substantially at opposing ends of the casing.

Abstract: The effective efficiency of a centrifugal compressor can be improved by achieving a uniform distribution of fluid velocity across the outlet end of a fluid passage of an axial diffuser for the centrifugal compressor and a high static pressure recovery ratio Cp in the axial diffuser passage. The cross section of each axial diffuser passage is configured such that a relatively high velocity fluid flow in an upstream part of the diffuser passage is directed toward a negative pressure side of a cross section thereof. It can be accomplished by directing a minor axis of a cross section of the diffuser passage substantially perpendicularly to a direction directed from a center of the cross section of the diffuser passage to the central axial line of an impeller or directing the minor axis toward the central axial line of the impeller.

Abstract: The present invention discloses an apparatus including: a blower fan, the blower fan having multiple blades; a diffuser attached to a housing of the blower fan; diffuser vanes located in the diffuser, wherein the diffuser vanes are also fins for a heat exchanger.

Abstract: A low solidity vaned airfoil diffuser for a centrifugal compressor wherein each blade has a lean angle greater than zero and wherein the hub stagger angle may be the same as or may be different from the shroud stagger angle for each blade.

Abstract: A heat dissipation apparatus. A fan frame includes an air inlet, an air outlet, a passage, and a curved expansion portion. The air inlet is opposite the air outlet. The passage is between the air inlet and the air outlet, guiding airflow from the air inlet to the air outlet. The curved expansion portion is radially and outwardly extended from an inner peripheral wall of the passage at the air inlet or air outlet. An impeller is disposed in the fan frame and includes a plurality of blades. Each blade is disposed in the passage and includes an extension end extending to the curved expansion portion.

Abstract: Centrifugal pumps and methods of making and using them are disclosed. One inventive pump includes a plurality of flow passages, at least one pump component having one or more non-axisymmetric flow passage contours defined at least in part by non-equal blade or vane heights.

Abstract: Centrifugal compressor flow stabilizing devices and methods of operation thereof are disclosed that act upon the flow field discharging from the impeller of a centrifugal compressor and modify the flow field ahead of the diffuser vanes such that flow conditions contributing to rotating stall and surge are reduced or even eliminated. In some embodiments, shaped rods and methods of operation thereof are disclosed, whereas in other embodiments reverse-tangent air injection devices and methods are disclosed.

Abstract: An axial flow turbine blade and diaphragm construction comprises an annulus of static turbine blades 20 and inner and outer spacer rings 40, 42 having apertures 41, 43 shaped to accommodate inner and outer platform portions 22, 23 of the blades, whereby the platform portions and the spacer rings together form inner and outer port walls of the turbine diaphragm. A particular feature of the blades is that the inner and outer platform portions 22 and 23 have straight side edges 22B, 22C and 23B, 23C, which are joined to each other by curved leading edges 22D and 23D that in plan view have a shape that follows the edge of the corner fillet 24 in the region of the leading edge 26 of the aerofoil 21.

Abstract: A blower motor for a vacuum cleaner or the like has an impeller/rotor assembly which is dynamically balanced. Air guide vanes are disposed between the diffuser plate and fan cover and surround the impeller periphery. A fan cover 13 accommodates the impeller 12. A vane plate 14 is fitted to the fan cover 13 for easy assembly and has guide vanes 28 which locate about the impeller 12 for guiding the working air from the impeller to a diffuser plate.

Abstract: A Francis runner that includes a crown, a band and blades which extend between the crown and the band. An angle (?24) between a linear speed (U, D224) of one of the blades and a median of the blade at the trailing edge, has a value between 20 and 25°. As a result, a machine utilizing the Francis runner of the invention is efficient, while an equivalent power under high load is high.

Abstract: A gas turbine diffuser assembly and a method for assembling same, includes providing a loose fit between the diffuser body and the diffuser pipes. Damper members provide a snug attachment.

Abstract: A gas turbine engine diffuser comprises a bowl-shaped diffuser casing and a cover nested into the bowl-shaped diffuser casing and cooperating therewith in defining a diffuser passage having a channeled entry portion in fluid flow communication with a vaned exit portion via a vaneless intermediate portion. The channeled entry portion is divided into an array of inlet flowpaths by a first set of vanes. Likewise, the vaned exit portion is divided into an array of outlet flowpaths by a second set of vanes.

Abstract: A turbine comprises a turbine wheel having radial blades and supported in a housing for rotation about an axis. An annular inlet passageway extends radially inwards towards the turbine wheel, the inlet passageway being defined between first and second facing annular walls. An annular array of vanes extend across the inlet passageway. Each vane has a trailing edge extending adjacent the turbine wheel blades, wherein the trailing edge of each vane deviates from a straight line over at least a portion of its length defined between its ends.

Abstract: A mixed flow turbine includes a hub attached to a rotation axis and a plurality of rotor blades. Each of the plurality of rotor blades is attached to the hub in a radial direction, and the hub is rotated based on fluid supplied to a rotation region of the plurality of rotor blades. Each of the plurality of rotor blades has a curved shape that convexly swells on a supply side of the fluid.

Abstract: Improved efficiency is obtained in a rotary machine having a rotary shaft (18) mounting a compressor wheel (20) that discharges into a heat exchanger (36) having a core (82) with a central opening (42) in surrounding relation to the shaft (18). The heat exchanger (36) includes a coolant tank (90) on one side of the core (82) and in fluid communication with the same which serves as one boundary of radially extending space (68) through which a gas is discharged by a compressor wheel (20). A deswirling vane structure (80) causes gas discharged by the compressor wheel (22) to move radially outward within the space (68) and is formed of a material of good thermal conductivity and thermally bridged to the tank (90) to conduct heat thereto to be rejected to coolant in the tank.

Abstract: A diffuser for converting high velocity fluid into high pressure fluid. The diffuser includes a pair of spaced opposing walls between which extend a plurality of blades. Each of the blades has a pressure side and a suction side, wherein the pressure side of one of the blades is adjacent the suction side of another one of the blades. Each pair of adjacent blades and spaced walls define a channel that extends from an inlet end to an outlet end with a generally increasing cross-sectional area. The suction side of each blade has a height greater than the pressure side of the adjacent blade defining the channel whereby the fluid is less likely to stall due to separation from the suction side. Each blade has a leading edge positioned at a 10° angle further minimizing the incidence of stall and increasing the operating range of the diffuser.

Abstract: A bypass motor assembly includes a motor having a rotatable shaft, a working air fan secured to the rotatable shaft and a shroud having an intake eyelet and at least one exhaust apertures. The assembly includes an end bracket having a shaft hole through which the shaft extends. The end bracket and the shroud partially enclose the working air fan, wherein rotation of the working air fan draws air in through the intake eyelet and pushes the air through the plurality of exhaust apertures, the end bracket having a plurality of vanes that form a fan chamber that receives the working air fan such that air expelled by the working air fan is efficiently re-directed by the vanes toward the exhaust aperture. An air intake seal can be disposed between the shroud and the working air fan to further enhance the working air flow.

Abstract: A gas compression apparatus and method according to which an impeller rotates to flow fluid through a casing, and a plurality of vanes are mounted on a plate in the casing. A series of cells are formed in the plate to form an array of acoustic resonators to attenuate acoustic energy generated by the impeller.

Abstract: A diffuser for converting high velocity fluid into high pressure fluid. The diffuser includes a pair of spaced opposing walls between which extend a plurality of blades. Each of the blades has a pressure side and a suction side, wherein the pressure side of one of the blades is adjacent the suction side of another one of the blades. Each pair of adjacent blades and spaced walls define a channel that extends from an inlet end to an outlet end with a generally increasing cross-sectional area. The suction side of each blade has a height greater than the pressure side of the adjacent blade defining the channel whereby the fluid is less likely to stall due to separation from the suction side. Each blade has a leading edge positioned at a 10° angle further minimizing the incidence of stall and increasing the operating range of the diffuser.

Abstract: An inlet air compressor for an internal combustion engine is provided which has one inlet and a plurality of outlets. Within the compressor are disposed a plurality of diffusers coupled to the plurality of outlets. The flow is divided among the plurality of outlets so that at conditions of low overall flow rate through the engine, which would, in a compressor according to the prior art, ordinarily surge, allow the flow to be substantially discontinued through one or more diffusers and continue at through the remaining diffusers. In this way, the diffusers with flow operate within an acceptable operating range and avoid a surging condition. The present invention is directed to engines having a wide range of flow rates. A couple of examples are gasoline engines and variable displacement engines.

Abstract: The present invention is a system of symmetric guides (25A, 25B) and baffles (26, 28) for directing and diffusing the external air drawn from a fan blower (12) before distributing the flow evenly to the outlet of a fan filter unit (32). This arrangement not only reduces the turbulence and minimizes pressure loss within a fan filter unit (32) but also maintains the even distribution of air when discharged through the same system. Furthermore, the present invention is implemented in dimensions substantially similar to that of the fan blower (12) in terms of heights. As such, the present invention minimizes noise of a fan filter unit (32) even in low clean room ceiling height. Finally, the present invention's guides (25A, 25B) and baffles (26, 28) are symmetrical surrounding the fan blower (12), which allows either the clockwise fan or the anti-clockwise fan to be used for the same fan filter unit (32) for user's convenience.