Abstract: In an axial flow fan, a line extending from a center axis and passing a corner where a following edge and a radially outer edge of a blade of an impeller meet is arranged forwardly in a rotational direction from an another corner where a leading edge of the blade and a radially outer surface of a hub meet. Furthermore, a camber ratio of the blade, which is minimum at a joint with the hub across the blade, monotonically increases to be maximum at the radially outer edge of the blade.

Abstract: A diffuser and exhaust system is provided for a turbine having an axial-radial diffuser and an exhaust hood including diffuser inner and outer flow guides that extend from an inlet to an outlet. The exhaust hood includes two throats or flow passages between the diffuser outlet and an exhaust hood side wall. The outer flow guide includes a recess, at one of the said two flow passages. The flow passage is positioned in relation to a point in the exhaust hood in the direction of the tangential flow velocity vector, where the point in the exhaust hood is farthest away from the exhaust hood outlet. The recess prevents a re-acceleration of the flow within the exhaust hood and affects an increase in the performance of the diffuser and exhaust hood system.

Abstract: Turbo machinery comprising an impeller and a diffuser positioned on a downstream side of the impeller that a channel wall surface of the diffuser is composed of a pair of a shroud side diffuser plate and a hub side diffuser plate which surface each other and a channel width is formed so as to be increased downstream, characterized in that guide vanes in a circular arc shape lower in height than the channel width are installed in a line of a plurality of vanes on both channel walls of the shroud side diffuser plate and hub side diffuser plate of the diffuser, and a total of vane heights of the two guide vanes at an outlet of the diffuser is set so as to be within a range from 30 to 70% of the channel width at the outlet of the diffuser.

Abstract: A turbomachine including an annular combustion chamber; a centrifugal compressor; an annular diffuser with a radially oriented upstream portion presenting diffusion passages connected to the outlet of the compressor; a curved intermediate portion; and a downstream portion having a series of circularly spaced-apart deflector vanes. The turbomachine also includes an outer casing externally surrounding the combustion chamber and the downstream portion. The zone of the outer casing that is situated facing the deflector vanes is covered in a coating of abradable material, and the flow passage through the downstream portion is defined on the outside by the outer casing and by the coating.

Abstract: Reduced size evaporative cooling apparatus utilizes a convex flare at the outlet of the apparatus to control air flow exiting the apparatus and cause air to flow along a helical path that produces an updraft off the ground below the apparatus.

Abstract: An example exit guide vane for a gas turbine engine is mounted adjacent to a diffuser case defining an air flow path. A thrust balance seal is attached to the diffuser and the exit guide vane is mounted adjacent the diffuser case for guiding air flow into the air flow path. The exit guide vane is mounted adjacent to the diffuser without interfering with the air flow path or restricting thermal expansion.

Abstract: An exhaust system for gas turbine engine is provided that reduces turbulence and backflow within the exhaust system and, thus, increases the efficiency of the turbine engine. In various embodiments, the system includes an exhaust plenum that provides a gradual expansion of the exhaust gases. The exhaust plenum may also include one or more flow splitters that further reduce turbulence in the plenum and provide a more uniform gas flow in the plenum and other downstream exhaust components.

Abstract: A diffuser for a turbine engine, including an annular casing to seal compressor discharge air and struts attached to the casing to delimit an annular array of intra-strut regions, is provided and includes a ring portion, including a ring shaped annular body with a forward face disposed on a forward side thereof, the ring portion being supportable by one or more of the struts, and a splitter portion, including a ring shaped annular body with an aft face disposed on an aft side thereof to mate with the forward face of the ring portion body, the splitter portion further including a lead edge, on a forward side of the splitter portion body, which is extendable into a flow path of the compressor discharge air to split the flow path into secondary flow paths defined radially outside of and inside of the splitter portion body.

Abstract: A compressor assembly for a gas turbine engine is provided. The compressor assembly includes a rotating impeller including an inlet, an outlet, and a body extending therebetween. The compressor assembly further includes a non-rotating impeller shroud. The body and the shroud define an impeller chamber including a radially inner surface and a radially outer surface. The radially inner surface includes an arcuate flow surface. The flow surface includes a first portion and a second portion extending downstream from the first portion. The impeller chamber includes a variable area wherein a first cross-sectional area is defined between the radially outer surface and the first portion, and a second cross-sectional area is defined downstream from the first cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. A method of operating the compressor assembly is also included.

Abstract: A diffuser arrangement through which a fluid may flow is provided. The diffuser includes an outer diffuser comprising an inner surface, and a flow-guiding device, which is configured such that at least part of the boundary layer flow forming on the inner surface of the outer diffuser can be accelerated in the main flow direction, so that a flow separation is prevented on the inner surface of the outer diffuser. Also provided are an exhaust steam plenum of a steam turbine and an exhaust gas plenum of a gas turbine, both including a diffuser arrangement.

Abstract: A turbocharger system, in certain embodiments, includes a compressor, a turbine, a shaft coupling the compressor to the turbine, and a turbo casing configured to improve pressure recovery, wherein the turbo casing includes a non symmetrical geometry configured to improve flow towards an exhaust outlet.

Abstract: A method and apparatus are described that include a transition piece including a cooling sleeve. The cooling sleeve includes a first end and an opposite second end, the cooling sleeve is coupled to an inner wall of the transition piece, such that an annular passage is defined between the inner wall and the cooling sleeve. The first end defines an annular inlet and second end defines an annular outlet.

Abstract: An inducer that includes a profiled throat. In some embodiments, the inducer includes a conical shape upstream of the profiled throat with a relatively large circular inlet that narrows to the profiled throat and, downstream of the profiled throat, a downstream section that broadens from the profiled throat. The profiled throat may include an approximate convergent-divergent nozzle geometry.

Abstract: An axial flow steam turbine flow path that includes a rotor and a casing defining the axial steam flow path; and a toroidal diffuser for diffusing the exhaust steam and turning the exhaust steam from a generally axial flow direction to a generally transverse or vertical and tangential direction; wherein the toroidal diffuser comprises a diffuser that, at least in part, incorporates the shape of a toroid or a section of a toroid; and wherein a toroid comprises the shape generated by revolving a circular or oval shape in three dimensional space about an axis coplanar with the circular or oval shape, which does not touch the circular or oval shape.

Abstract: An apparatus for extending the effective exhaust gas path in order to allow gradual diffusion of the exhaust gases in a turboshaft engine wherein the engine includes an annular engine case with at least an exhaust gas duct having an axial component communicating with an annular duct with a substantially radial component and traversing the engine case, the apparatus comprising a collector plenum having a convex annular shape and a diameter larger than that of the engine case with at least one exhaust outlet defined in the plenum and wherein the annular duct extends into the plenum beyond the diameter of the engine case to extend the exhaust gas path.

Abstract: An exhaust system for a turbine includes an annular diffuser and a collector. The annular diffuser is positioned adjacent to a final stage of the turbine and includes a hub portion surrounding a turbine shaft and an outer cone having a substantially frusto-conical shape that is radially symmetrical about a central longitudinal axis thereof that is tilted relative to the turbine shaft. The collector has an inlet extending from the annular diffuser and an outlet. The collector is configured to include a turn that causes the collector to turn exhaust gases approximately 90° from the longitudinal axis of the turbine shaft. The outer cone of the annular diffuser is tilted in a direction of the turn of the collector.

Abstract: A diffuser apparatus in a turbomachine is provided comprising a diffuser structure and stabilizing structure. The diffuser structure includes inner and outer walls defining a flow passageway through which gases flow and diffuse such that kinetic energy is reduced and pressure is increased in the gases as they move through the passageway. The stabilizing structure stabilizes a separated gas recirculation zone.

Abstract: A diffuser and exhaust system is provided for a turbine having an axial-radial diffuser and an exhaust hood including diffuser inner and outer flow guides that extend from an inlet to an outlet. The exhaust hood includes two throats or flow passages between the diffuser outlet and an exhaust hood side wall. The outer flow guide includes a recess, at one of the said two flow passages. The flow passage is positioned in relation to a point in the exhaust hood in the direction of the tangential flow velocity vector, where the point in the exhaust hood is farthest away from the exhaust hood outlet. The recess prevents a re-acceleration of the flow within the exhaust hood and affects an increase in the performance of the diffuser and exhaust hood system.

Abstract: An air conditioner includes a unit casing, an impeller, a scroll casing, and a heat exchanger. The unit casing is partitioned by a partition member into a fan chamber and a heat exchanger chamber. The heat exchanger is disposed inside the heat exchanger chamber so as to face a scroll blowout opening in the scroll casing. The scroll casing is disposed inside the fan chamber. A wall section projects from a heat exchanger side of a flat plate section of the partition member and is disposed outside a scroll outlet section of the scroll casing.

Abstract: A turbine exhaust system includes an exhaust hood inner casing that involves the turbine rotor; an exhaust hood outer casing that forms an exhaust hood, together with the exhaust hood inner casing; a flow guide that forms an annular diffuser flow path; and exhaust hood upper part flow guides each of which serves as means for separating annular plane upper part exhaust steam within a range including a vertical upward flow out of exhaust steam radially discharging from the flow guide into the exhaust hood, from other exhaust steam, to thereby introduce the separated steam to the condenser, wherein exhaust steam introduction-side end faces thereof are located further toward the upper side than the horizontal plane containing the central axis of the turbine rotor.

Abstract: A gas turbine arrangement comprising: a passage, annular in cross section, for conveying combustion gases; located in the passage, turbine blading to be driven by the combustion gases; a diffuser, annular in form, for diffusing the combustion gases following their passage through the turbine blading; and a collector for collecting the combustion gases diffused by the diffuser, the collector comprising an annular main part, and, located at a position around the annular main part, a neck exit, in use of the gas turbine arrangement, combustion gases collected by the collector being conveyed around the annular main part of the collector in opposite senses so as to arrive at the neck exit of the collector travelling in opposed directions, wherein the neck exit of the collector includes a partition device whereby the opposed direction flows at the neck exit are kept substantially separate.

Abstract: A tip turbine engine has a more efficient core airflow path from the hollow fan blades, through the combustor and to the combustion chamber of a combustor. The turbine engine includes a rotatable fan having a plurality of radially-extending fan blades each defining compressor chambers extending radially therein. A turbine is mounted to the outer periphery of the fan. A diffuser at a radially outer end of each compressor chamber turns core airflow through the compressor chamber toward the combustor. The high velocity, high pressure core airflow from the compressor chambers in the hollow fan blades is diffused before the compressed core airflow enters the combustor, thereby improving the efficiency of the tip turbine engine. Further, the overall diameter of the tip turbine engine is reduced by the arrangement of the diffuser case in a position not directly radially outward of the fan blades.

Abstract: A diffuser for diffusing the exhaust gas produced by an engine, said diffuser comprising a wall or walls defining sections of the diffuser, said diffuser comprising: an initial section which extends for substantially one third the length of the diffuser, at the entry to said initial section the shape factor of the boundary layer flow at the or each wall of the section being in the range 1.3 to 1.6, said initial section being configured so as to substantially linearly increase said shape factor so that at the exit of said initial section said shape factor is in the range 1.6 to 2.2; and a main section following the initial section and extending for the remaining length of the diffuser, said main section being configured so as to maintain said shape factor in the range 1.6 to 2.2 over the length of the main section.

Abstract: A plastic compressor housing, in particular a radial flow compressor housing, preferably for a turbocharger, has at least one thermosetting plastic body for providing an intake pipe, a compressor duct, and an outlet pipe, and a thermoplastic at least partially covering the thermosetting plastic body in a hood-like fashion. The thermosetting plastic body is formed as a basic body and the thermoplastic is injection molded on the basic body. At least a first anchoring element is embodied on at least a first surface of the thermosetting plastic body and at least a second surface of the first anchoring element is substantially completely covered with the thermoplastic. The disclosure further relates to a method for producing a plastic compressor housing.

Abstract: In an axial flow fan, for reducing fluid noise and further reducing the noise by suppressing solid-conveyed noise (structure-borne noise) generated by the vibration of an electric motor or the like, the axial flow fan is equipped with a propeller, a motor for driving the propeller, and a venturi portion disposed on the outer circumference side of the propeller and provided on its inner circumferential side with a bellmouth through which an air flow generated by the revolution of the propeller passes, wherein the bellmouth has an intake portion whose diameter contracts in a curved shape in the direction of the air flow, a cylindrical portion having a cylindrical shape, and a discharge portion whose diameter slantingly expands in the direction of the air flow.

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: A shroud 15 attached to an air discharge side of a radiator 13 narrows toward a centrifugal-flow-type rotary fan 11 and forms a cylindrical shape. A surrounding portion 17 is provided so as to surround the rotary fan 11. A guide portion 23 extending in the centrifugal direction of the rotary fan 11 is provided at a circumferential edge portion of the surrounding portion 17. A cylindrical portion 19, which is smaller in diameter than the surrounding portion 17 is provided inside the surrounding portion 17, and an upper portion of the cylindrical portion 19 is fixed to the wall surface of the shroud 15. A lower portion of the cylindrical portion 19 is fixed by a fixing portion 21 having an inner diameter equal to the diameter of the cylindrical portion and an outer diameter equal to the diameter of the surrounding portion 17.

Abstract: A rotary ram compressor for use in gas turbine engines and the like, having a plurality of vanes attached to discs, with the opposing parts of each two adjacent vanes and the opposing parts of the disks' surfaces confined between the opposing parts of the surfaces of the two adjacent vanes defining a channel in-between. Each channel is formed of two successive freely communicating portions: a first diverging inlet portion; and a second constant cross-sectional area outlet portion. In operation, gases are rammed into the first diverging inlet portion of the channel and are gradually displaced to the second constant cross-sectional area outlet portion of the channel, while being diverged, resulting into a rise in the static pressure energy of the gases, followed by smoothening of the stream of flow of the pressurized gases within the second constant cross-sectional area outlet portion of the channel.

Abstract: A centrifugal pump (1) is proposed, in particular for household appliances, such as washing machines or dishwashers, which comprises a pump housing (2) having an axial inlet (11), an outlet (12) and a heating element, wherein the pump housing (2) incorporates a rotatably mounted impeller (4) and a flow channel (15) enveloping the impeller (4) and heating element. The centrifugal pump (1) according to the invention is intended to have improved efficiency. This is achieved by having the flow cross-section of the flow channel (15) increase along the periphery toward the outlet (12).

Abstract: It is possible to keep a diameter of an impeller and a cross sectional area of an air channel as large as possible while reducing a size of a centrifugal fan in a direction perpendicular to an axis. Thereby, it is possible to acquire characteristics of a high air volume and a high static pressure without lowering the efficiency. In the centrifugal fan, when the radial gap of the cross section in an air channel 10b is gradually enlarged from a clapper portion 10c toward an outlet 10d except for a specific region 10h, the cross inner sectional area of an air channel 10b is gradually enlarged from the clapper portion 10c toward the outlet 10d.

Abstract: A centrifugal fan, comprising a frame and a first guide portion. The frame comprises a bottom portion and a curved wall connected thereto. The curved wall comprises an airflow inlet. The first guide portion disposed along the curved wall at the bottom portion comprises a beginning area, a middle area, and an ending area. The middle area connects the beginning and the ending areas, and the beginning area extends from the airflow inlet. The beginning area has a width less than that of the ending area, and the beginning area has a height greater than that of the ending area.

Abstract: A turbojet diffuser disposed between a compressor and a combustion chamber, and secured to an outer upstream annular flange of an outer casing of the combustion chamber by suspension means which comprise a first frustoconical wall extending from the outer longitudinal wall of the diffuser towards the combustion chamber, and a second frustoconical wall extending towards the compressor between the first frustoconical wall and the outer casing of the combustion chamber.

Abstract: This invention refers to a hydraulic or pneumatic machine with tilting blades, running either as an engine on a fluid flow or on pressure fluid or as a pump or a compressor. The hydraulic or pneumatic machine on a fluid flow according to the invention consists of a cylindrical casing with inlet and outlet openings, radially arranged, diametrically oposed, along the fluid flowing direction, some disk like rotors with tilting blades, hinged over their front faces and provided with driving mechanisms of their own, and some fixed drums located between the rotors, concentrically to them, making inside the machine some channels, symetrically arranged on one or several stages. Flowing through the channels, the fluid drives the tilting blades causing the movement of the rotors, all the rotors moving to one sense being coupled to the same outlet shaft of the machine.

Abstract: A water driven turbine has a divergent cone coupled to the exit end of the housing in which diameter of the cone increases with increasing distance from the exit end of the housing. A diverter formed of rigid material surrounds the free end of the cone and defines an annular space therebetween through which a flow of water passes to accelerate the flow exiting the turbine housing. The diverter is shorter in the length than the divergent cone and longitudinally overlaps the divergent cone. The diverter also has straight walls which are sloped to extend in the longitudinal direction away from the exit end of the housing at an inward incline between the leading end and the trailing end thereof.

Abstract: A discharge collector and diffuser for a screw compressor, including a housing having an inlet for receiving flow from a compressor and an outlet and defining therebetween a collector portion, a transition portion and a diffuser portion, the collector portion being adapted to receive a plurality of non-parallel streams from a compressor and to guide the streams into a substantially parallel flow direction, the housing further having a splitter plate positioned in the collector portion to separate the non-parallel streams from each other, whereby the streams are maintained separate until they are substantially parallel, thereby reducing flow losses.

Abstract: The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell (6) of the compressor and an annular structure (7) connected to the shell, and, on the other hand, by the external casing (12) of the diffuser grating and a strut (13) connected to said external casing and to an external engine casing shell (14), this external casing shell (14) being fastened to the annular structure (7) by bolting together flanges, using sealing means provided between the annular structure (7) and the external casing (12) of the diffuser grating.

Abstract: An air outlet unit (101) for a large blower assembly comprising an outlet tube member (103) with an upstream inner end in flow communication with the pressure side of an impeller of the blower asembly and a downstream outer end for connection with a duct and a mainly cylindrical inner tube member (105) arranged coaxially to the outlet tube member (103) and having an inner end substantially aligned with the inner end of the outlet tube member (103) and a downstream outer end, the inner tube member (105) being closed by a closing means (106). The inner tube member (105) has an open downstream end (8114) projecting in the downstream direction beyoud the downstream outer end of the outlet tube member (103) to thereby achieve a reduced pressure loss and a more uniform velocity profile.

Abstract: Disclosed is a fan module. In one embodiment, the fan module includes a fan having an inlet end and an exit end, and a fan housing in which the fan is positioned, the fan housing including at least one angled interior wall adjacent the exit end of the fan that diffuses air downstream of the fan.

Abstract: An exhaust adapter for use with a draft inducer having a blower housing with a rectangular blower outlet. The exhaust adapter provides a transition from the rectangular outlet of the blower housing and a round exhaust pipe. The exhaust adapter includes a transition section extending between an attachment flange and a round exhaust outlet. The exhaust adapter thus facilitates attachment of the blower housing to a round exhaust pipe. The exhaust adapter is formed from two sections of stamped metal joined to each other along a top and a bottom seam. The two sections of stamped metal allow the exhaust adapter to be formed using inexpensive materials and an inexpensive manufacturing process.

Abstract: A gas turbine engine combustor inlet diffuser assembly has at least one diverging annular wall including a flowpath surface bounding a diffuser flowpath. An annular blowing slot is axially located along the annular wall and an annular blowing air flowpath leads to and is in fluid communication with the blowing slot. An annular array of scoops disposed in the diffuser flowpath downstream of the blowing slot have upstream facing openings and are in fluid communication with the blowing air flowpath. The annular scoops are supported on hollow struts. Each of the hollow struts has at least one radially extending flow passage for directing blowing air from the scoop to the blowing air flowpath. The blowing slot opens in a downstream direction with respect to the diffuser flowpath. A row of blowing air compressor blades disposed across the blowing air flowpath may be used to pump up the pressure of the blowing air.

Abstract: A small cooling fan includes a rotating fan body with a vane in a flat fan housing, and an air channel for backflow prevention. The air channel is provided outside of the vicinity of the tip of the vane of the rotating fan body, extends to an air outlet, and has an inner height larger than that of a fan chamber. This structure can prevent the backflow of the wind at the air outlet and reduce the loss of the static pressure, thereby increasing the airflow quantity in spite of the small size.

Abstract: The shafts of upstream and downstream turbines are interconnected by a coupling. A diffuser is provided in an intermediate cavity between the upstream and downstream turbines to recover kinetic energy, as well as minimize or eliminate windage and spinning losses resultant from exposure of the coupling to the flowpath along the turbines. A radial entry inlet provides a supplemental fluid admission into the intermediate cavity, the admission being turned axially and circumferentially for joining with the flow exiting the upstream turbine for combined flow to the downstream turbine.

Abstract: A furnace blower housing has a two-piece exhaust transition, one piece of which is an integral extension of the blower housing, that transitions a rectangular cross section outlet of the blower housing to a circular cross section outlet of the exhaust transition that is adapted to be attached to a circular exhaust pipe.

Abstract: A screw compressor includes a housing containing at least one rotor for generating a discharge flow in a discharge flow direction; a diffuser communicated with the housing and having a collecting portion for receiving the discharge flow, a diffuser throat and a diffuser portion, said diffuser extending from the housing in a diffuser direction; and at least one turning vane positioned in the collecting portion and adapted to guide flow from the discharge flow direction to the diffuser direction.

Abstract: A screw compressor including a housing containing at least one rotor for generating a discharge flow in a discharge direction; a diffuser member communicated with the housing to receive the discharge flow, the diffuser extending from the housing in the discharge flow direction, the diffuser having a converging collecting section, a diffuser throat downstream of the collecting section and a diffusing section downstream of the throat, whereby the discharge flow can be collected and diffused in the discharge flow direction.

Abstract: A diffuser for slowing down a fluid and a method for operating a diffuser is described. A channel of the diffusor has an inlet with a smaller flow cross section than a flow cross section of an outlet and at least one opening for receiving an energizing fluid to be transported selectively into the channel. Pulsations of the impact interface are suppressed effectively at all of the operating points by injecting the energization fluid. Pressures of the fluid moving in the diffusor are measured, and amplitudes and frequencies of the measured pressures are evaluated. Energizing fluid is fed into the diffusor if the amplitudes within a predetermined frequency band exceed a threshold value. The utilization ratio of the inventive diffuser is considerably improved as a result of such a measure.

Abstract: A furnace blower housing has a two-piece exhaust transition, one piece of which is an integral extension of the blower housing, that transitions a rectangular cross section outlet of the blower housing to a circular cross section outlet of the exhaust transition that is adapted to be attached to a circular exhaust pipe.

Abstract: A blower for a furnace is provided where the blower has a housing with an industry standard 4″ diameter exhaust port. The discharge of the blower housing is coupled directly to exhaust piping without the use of transition pieces or expender pieces.

Abstract: An annular diffuser has its inlet located at the exit of a last row of blades of a gas turbine having initially very slowly increasing cross-sectional area with distance to accommodate the diffusion produced by the decaying wakes in the diffuser so as to prevent flow separation from diffuser walls and as a result to foster the diffusion process and to increase the efficiency of the gas turbine. The rate of increase of cross-sectional area, which is much smaller than that appropriate in diffusers having uniform flow at their inlets, allows wakes which form near the trailing edges of the last turbine blades to dissipate while avoiding flow separation. In the diffuser of this invention, at a distance from inlet of one half of diffuser height at inlet, the cross-sectional area increase is smaller than 6.5% of the inlet cross-sectional area. This is equivalent to the corresponding two-dimensional straight-wall diffuser angle of, approximately 3.7 degrees.

Abstract: There is provided an axial-flow turbine comprising an exhaust chamber; a turbine including multiple stage rotor blades, said multiple stage rotor blade including terminal stage rotor blades; an annular diffuser located between the turbine and the exhaust chamber; and an annular axial-flow turbine passage defined by the turbine, the diffuser and the exhaust chamber, wherein fluid flows through the axial-flow turbine passage toward the exhaust chamber, and an annular stepped portion which inwardly projects in a radial direction is formed on the portion of an inner wall of the axial-flow turbine passage that is located on the downstream side of a trailing edge of a tip portion of the terminal stage rotor blades provided in the flow direction of the fluid. In the stepped portion, a projecting portion which inwardly projects in a radial direction may be provided.