Abstract: A method of altering the twisting relationship for the aerodynamic surface of a fan blade of a gas turbine engine, wherein the following steps are performed: establishing, for a portion of the aerodynamic surface of the fan blade, an alteration relationship defined by variation of a pitch angle of the blade as a function of radial height along the blade, the alteration relationship including alterations that are each defined by a height along with the radial height of the fan blade and by an amplitude; and applying the alteration relationship as established in this way to an initial twisting relationship of the fan blade so as to obtain an altered twisting relationship for the fan blade, the initial twisting relationship being defined by a polynomial for the radial height of the fan blade as a function of its pitch angle.

Abstract: A diffuser system for a centrifugal compressor is provided. The diffuser system includes a nozzle base plate (206) that defines a diffuser gap (212), support blocks (216, 246), and a drive ring (220) rotatable relative to the support blocks. The drive ring includes cam tracks (224, 242) and bearing assemblies (226, 234) positioned proximate an outer circumference of the drive ring. The diffuser system further includes drive pins (214) extending through the support blocks and the nozzle base plate. The first end of each drive pin includes a cam follower (218) mounted into a cam track on the drive ring. The second end of each drive pin is coupled to a diffuser ring (208). Rotation of the drive ring causes axial movement of the drive pins by movement of the cam followers in the cam tracks. This results in movement of the diffuser ring to control fluid flow through the diffuser gap.

Abstract: A centrifugal compressor includes: an impeller fixed on an outer periphery of a rotary shaft; a diffuser disposed at a radially outer side of the impeller; a casing accommodating the impeller and the diffuser; a scroll flow passage connected to an outlet of the diffuser, the scroll flow passage being formed into a scroll shape by a scroll inner peripheral wall and a scroll outer peripheral wall positioned at a radially outer side of the scroll inner peripheral wall; and a discharge pipe connected to the casing so as to form a discharge flow passage for guiding a fluid from the scroll flow passage to outside of the casing. The scroll inner peripheral wall is positioned at an inner side, in a radial direction, of the outlet of the diffuser, and the discharge pipe includes an inner wall surface which has a radially inner region.

Abstract: A vaned diffuser provided on a downstream side of an impeller of a centrifugal compressor. The vaned diffuser includes: a diffuser passage forming portion having a hub-side surface and a shroud-side surface and forming an annular diffuser passage on a downstream side of the impeller; and a plurality of diffuser vanes provided in the diffuser passage at intervals in a circumferential direction of the impeller. A fillet is formed in a connection portion between each of the diffuser vanes and at least one of the hub-side surface and the shroud-side surface. Also, where R is a radius of the fillet and b is a vane height of each of the diffuser vanes, and a maximum value of R/b on a downstream side of a throat position of the diffuser passage is larger than a maximum value of R/b on an upstream side of the throat position of the diffuser passage.

Abstract: A fixed vane turbocharger includes: an impeller; a housing including, inside thereof, an impeller housing space which accommodates the impeller, a scroll flow passage formed on a radially outer side of the impeller, and a communication flow passage which brings the impeller housing space and the scroll flow passage into communication; and at least one fixed vane unit disposed in the communication flow passage and fixed to a portion of the housing on an inner side of the scroll flow passage with respect to a radial direction of the impeller. Each of the at least one fixed vane unit includes at least two vane portions and a coupling portion coupling the two vane portions, and is formed of a single sheet metal member.

Abstract: A diffuser for a radial compressor of a turbomachine is provided. The diffuser has a plurality of diffuser channels, wherein the diffuser channels extend across a radial area of the diffuser across a bent area into an axial area of the diffuser, wherein, in the radial area of the diffuser, the diffuser channels have diffuser walls in particular at v-shaped blades that are bent in the movement direction of the radial compressor or are straight.

Abstract: A fan device with at least one radial fan (12), with a fan housing (13) in which an impeller (14) which is rotationally driven about a rotation axis is arranged, wherein the fan housing has a guide wall (18) which extends in a circumferential direction (17) of the impeller (14) around this, is equipped with several arcuate wall sections and delimits air blow-out openings (19a-d), wherein an arcuate wall section of the guide wall (18) is assigned to each of the air blow-out openings (19a-d), wherein the fan housing (13) includes a front cover plate (20b) which is provided with an air suction opening (21), and a rear cover plate (20a) which with regard to the flow direction is arranged downstream of the front cover plate (20b), and wherein a frame-shaped peripheral wall (36) of an outer housing (35) is arranged around the guide wall (18) and at its rear side (37) includes a rear frame opening (38a).

Abstract: A compressor diffuser for a gas turbine engine is described which includes diffuser pipes having a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a generally radial direction, a second portion extending in a generally axial direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. A first curved side wall of the tubular body along the second portion is shorter than a second curved side wall of the tubular body along the second portion. The second portion of the tubular body has a cross-sectional profile defined in a plane normal to the pipe center axis. The first curved side wall of the cross-sectional profile has a smaller radius than a radius of the second curved side wall of the cross-sectional profile.

Abstract: A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates. The compressor includes a diffuser extending between an exducer of the compressor wheel and a volute for collecting pressurized air from the compressor. The diffuser is defined between first and second walls that diverge from each other in a radially outwardly direction through the diffuser. The divergent-wall diffuser enhances the shift of the surge line to lower flow rates when the inlet-adjustment mechanism is put in the closed position.

Abstract: A cooling module system for a heat producing information handling system component comprising a dual opposite outlet blower system comprising a power source and a blower fan motor for rotating a blower fan having a plurality of blades and a fan diameter for rotation of the blower fan in a rotational plane, a dual opposite outlet blower system housing including first surface having an fan inlet aperture, a second surface oppositely disposed of the first surface on which the blower fan is operatively coupled inside the dual opposite outlet blower system housing.

Abstract: A compressor includes a diffuser section having a diffuser structure and a silencer. The silencer includes a silencer housing defining a cavity and a silencing pad disposed within the cavity, wherein an exposed surface of the silencing pad is arranged in contact with a portion of the diffuser structure.

Abstract: A variable nozzle unit includes a variable nozzle vane which is disposed between a hub wall surface and a shroud wall surface and is rotatable around a rotation axis parallel to a rotation axis of a turbine impeller inside a gas flow passage. The variable nozzle vane includes a leading edge, a trailing edge, and an outer vane surface connecting the leading edge and the trailing edge and facing a radial outside of the rotation axis. A concave portion at least in a range of a leading edge side in relation to the rotation axis is formed at the hub wall surface side of the outer vane surface.

Abstract: A portable computer system includes a chassis, a fan, and a seal. The chassis includes an inlet vent to permit ambient air to be drawn from outside the chassis. The fan receives the ambient air via an input aperture, and blows the ambient air through a first outlet aperture to cool a first component of the portable computer system. The seal seals the input aperture to the input vent such that air from inside the chassis is prevented from recirculating through the fan.

Abstract: A fan includes a core part, a vanes, a ring part and a flow rectifying member. The ring part includes first second and third parts. The first part includes a first end overlapping with a flow rectifying member end and extends axially on a radially inner side of the flow rectifying member. The second part includes a second end spaced from the flow rectifying member end, overlapping with the flow rectifying member, and connected to the first end. The third part is connected to the second end, and extends on the radially outer side of the flow rectifying member end. The second end overlaps with a virtual point reached by the flow rectifying member end being linearly extended toward an upstream side. A first dimension, a radial length of the third part, is at least 0.5 times a first straight-line distance between the flow rectifying member end and the virtual point.

Abstract: An information handling system comprising a chassis supporting a central processor, a graphics processor, a memory, and a power source and a dual opposite outlet blower system having a powered blower fan for rotating a plurality of blades within a dual opposite outlet blower system housing where the dual opposite outlet blower system housing includes first surface and a second surface oppositely disposed on either side of a rotational plane of the powered blower fan, a first side wall having a first notch extending internally along a diameter in the rotational plane of the powered blower fan and second side wall oppositely disposed to the first side wall and having a second notch extending internally along the opposite side of the diameter in the rotational plane of the powered blower fan.

Abstract: In a pipe diffuser (50) of a centrifugal compressor including a plurality of diffuser pipes (51), each diffuser pipe internally defines a diffuser passage including an inlet passage portion (74) having a diffuser inlet opposing an outer periphery of the impeller, an outlet passage portion (78) having a diffuser outlet (76) opening in an axial direction of the impeller, the outlet passage portion having an oval cross section elongated in a circumferential direction of the impeller, and a curved passage portion (80) connecting the inlet passage portion and the outlet passage portion to each other, wherein a part of each diffuser pipe defining the outlet passage portion is provided with a bulging part (82) that bulges into the diffuser passage from a radially inner side thereof with respect to the impeller.

Abstract: An axial fan according to an exemplary embodiment of the present disclosure includes an impeller, a motor, and a housing. The impeller is configured to rotate about a rotation axis extending in a vertical direction. The motor is configured to rotationally drive the impeller. The housing is disposed radially outside the impeller and the motor. In a region overlapping in the vertical direction with the impeller, an inner wall surface of the housing includes at least one first wall having a narrow gap with a radially outer edge of the impeller and at least one second wall having a wide gap with the radially outer edge of the impeller.

Abstract: In a centrifugal compressor including an impeller (70) having rotor blades (74), a shroud (72) surrounding the impeller, and a diffuser (76) having stator vanes (78), the shroud (72) includes a plurality of openings (80) opening toward the impeller (70) in a part thereof adjacent to an impeller outlet portion (42B), and a communication passage (82) communicating the openings (80) with one another, the openings including first openings (80A) that are arranged at a same interval as the stator vanes, and second openings (80B) arranged intermediately between the adjacent first openings.

Abstract: An air handling unit for use with an air conditioning system is provided including a housing duct through which air is circulated. A vane-axial flow fan circulates air through the housing duct. The fan includes an impeller having a plurality of fan blades extending therefrom and an axis of rotation arranged substantially in-line with a flow path of the air. A heat exchanger assembly is arranged within the housing duct in a heat transfer relationship with the air circulating through the housing duct.

Abstract: A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.

Abstract: A shaftless motor-compressor is disclosed, comprising a casing and at least one compressor stage arranged in the casing. Each compressor stage comprises a respective impeller arranged for rotation in the casing around a rotation axis. Each impeller is combined with an embedded electric motor housed in the casing and comprised of a motor stator and a motor rotor. The motor stator of each compressor stage circumferentially surrounds the impeller and the motor rotor, integral with the impeller. The motor rotor of each stage is arranged inside the respective motor stator.

Abstract: The invention refers to a fan system (10) comprising a fan shroud (14) and a ring fan (12) having a hub (30), a plurality of fan blades (32), and a ring structure (34). The ring structure (34) has a ring member (46) and a flange member (48), the ring member (46) having a hollow cylindrical shape, the flange member (48) extending radially outwardly from the ring member (46). The fan shroud (14) has an annular shroud flange (54), a shroud body (56) and a plurality of shroud guide vanes (58), the shroud flange (54) extending radially outwardly from the shroud body (56) and being disposed along the rotary axis (A) between the flange member (48) and the shroud body (56), the shroud body (56) being disposed about the ring member (46) and having a first body portion (70), a second body portion (72) and a divergent nozzle (74).

Abstract: An information handling system comprising a chassis supporting a central processor, a graphics processor, a memory, and a power source and a dual opposite outlet blower system having a powered blower fan for rotating a plurality of blades within a dual opposite outlet blower system housing where the dual opposite outlet blower system housing includes first surface and a second surface oppositely disposed on either side of a rotational plane of the powered blower fan, a first side wall having a first notch extending internally along a diameter in the rotational plane of the powered blower fan and second side wall oppositely disposed to the first side wall and having a second notch extending internally along the opposite side of the diameter in the rotational plane of the powered blower fan.

Abstract: A diffuser (10) comprises first (10.1) and second (10.2) annular portions bounded by forward (32) and aft (26) annular walls, wherein the first annular portion (10.1) is vaneless and radially within the second annular portion (10.2), and the second annular portion (10.2) is radially relatively compact and incorporates a plurality of vanes (48) with relatively high solidity, wherein the forward (32) or/and aft (26) annular walls is/are sloped so as to provide for meridional divergence within the second annular portion (10.2) of the diffuser (10), and the vanes (48) are shaped so as to substantially conform to the flow field within the second annular portion (10.2).

Abstract: A centrifugal fan with axial-flow wind includes a centrifugal fan wheel and a cover shell. The centrifugal fan wheel has a rotating core structure and a plurality of centrifugal vanes arranged around the rotating core structure; a circular wind guide surface is disposed on an internal side of the cover shell and around the rotating core structure and covered onto the centrifugal vanes, such that the circular wind guide surface can change a centrifugal airflow at the external periphery of the centrifugal vane into an axial-flow airflow.

Abstract: In a compressor, comprising a housing including a flow-through air guiding section with an inlet duct, a wheel chamber formed downstream of the inlet duct for accommodating a compressor wheel, and a spiral duct formed downstream of the wheel chamber, wherein flow slots are formed in a transition region connecting the inlet duct with the wheel chamber, and the transition region extends both in the directions of the inlet duct and of the wheel chamber along a leading edge of the compressor wheel, the flow slots each extend along an axial first length (L1) and along a radial length (RL) with a cross-section (Q), which cross-section (Q) changes over the axial first length (L1) of the flow slots.

Abstract: An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a plurality of guide vanes disposed in a second zone to slow the air from the compressor; a plenum disposed in a third zone located next to second zone to provide the air from the compressor to chambers; and a splitter disposed in a fourth zone to split the air from the compressor into an airflow required by each pulse detonation tube for detonation.

Abstract: A fan assembly (10) includes a shrouded fan rotor (24) including a plurality of fan blades (28) extending from a rotor hub (30) and rotatable about a central axis (26) of the fan assembly and a fan shroud (32) extending circumferentially around the fan rotor (24) and secured to the plurality of fan blades (28). The shroud (32) has a first axially extending annular portion (38) secured to the plurality of fan blades (28), a second axially extending annular portion (40) radially outwardly spaced from the first axially extending annular portion (38), and a third portion (44) connecting the first (38) and second (40) axially extending annular portions. A casing (22) is positioned circumferentially around the fan shroud (32) defining a radial clearance between the casing and the fan shroud. The casing (22) includes a plurality of casing elements (48) extending from a radially inboard surface (46) of the casing toward the shroud (32) and defining a radial element gap and an axial element gap.

Abstract: An impeller for a centrifugal fan includes a main plate having a disc shape, a plurality of blades arranged along a circumferential direction about a center part of the main plate, and an outer ring having a ring shape connecting the respective blades. The outer ring is connected to tip end portions of the respective blades at a side of a fluid discharge opening, and each of the blades has a shape which is bent in a rotating direction of the impeller in a vicinity of the tip end portion.

Abstract: A rotor assembly having a plurality of scoops disposed in a circumferential array, the scoops extending from an inner surface of the outer wall of the flow path along a radial distance smaller than a radial distance between the inner and outer walls of the flow path. Each of the scoops forms a closed channel from an inlet to an outlet with the inlet and outlet being axially spaced from one another, the outlet being upstream of and adjacent the annular blade path. A gas turbine engine and method of reducing tip vortices in a rotor assembly are also discussed.

Abstract: The invention relates to an exhaust-gas turbocharger (1) having a compressor housing (3), having a bearing housing (28) which can be connected at one end to the compressor housing (3) by means of a first fastening device (19), and having a turbine housing (2) which can be connected to the bearing housing (28) at the other end of the latter by means of a second fastening device (20), with the compressor housing (3), the bearing housing (28) and the turbine housing (2) extending along an exhaust-gas turbocharger longitudinal axis (R), wherein the first fastening device (19) is designed as a plug-and-twist connecting device.

Abstract: A cooling fan module includes a frame, and a fan impeller having a plurality of fan impeller blades is located in an opening of the frame. The fan impeller blades are connected to a base portion of an outer fan ring. A lip portion of the outer fan ring extends from the base portion radially outward, and a leading end of the lip portion is turned in direction to the downstream side of the frame. A recirculating flow guiding device includes a plurality of guide vanes located on an upstream side of the frame and around the opening of the frame. An air gap is provided between the outer fan ring and the frame. A recirculating flow travels from downstream side of the cooling fan module through the air gap, and is turned by the leading end of the lip portion into the recirculating flow guiding device.

Abstract: An object is to provide a mixed flow turbine, wherein intermediate blades having an intermediate height are provided between main blades of the mixed flow turbine, thus improving an impulse blade turbine characteristic and reducing the moment of inertia for a rotor blade as a whole, thereby improving the efficiency and transient response.

Abstract: A centrifugal fan is provided. The centrifugal fan includes an impeller and a housing. The impeller has an impeller diameter. The housing includes an upper plate, a lower plate and a side wall, wherein the upper plate axially corresponds to the lower plate, a side wall is formed between the upper plate and the lower plate, an axial inlet is formed on the upper plate, a lateral outlet is formed on the side wall, the impeller is disposed in the housing and corresponds to the inlet, and a flow path communicates the inlet to the outlet, wherein a greatest width of the inlet is greater than or equal to the impeller diameter.

Abstract: A method for culturing algae comprising, forming an emulsion comprising a gaseous stream and a media utilizing a high shear device, wherein the emulsion comprises gas bubbles, and wherein the high shear device comprises at least one toothed rotor and at least one stator; introducing the emulsion into a bioreactor; and introducing an algae into the bioreactor for growing the algae culture. Additionally, a method for producing liquids from an algae culture, the method comprising forming an emulsion comprising a buffer and algal components, wherein the emulsion comprises algal component globules; separating algal hydrocarbons; and processing algal hydrocarbons to form liquid hydrocarbons. Additionally, a system for producing liquids from an algae culture comprising at least one high shear device.

Abstract: A pipeline pump shaped by stamping and welding, comprises a pump body, a pedestal, a pump rear cover and a motor installed at the opening of the pump body, and an impeller arranged inside the pump body. The pump body is comprised of an inner cylinder and an outer cylinder. A flow guide part, the impeller, an exhaust part, and the pump rear cover mounted on the opening of the outer cylinder are coaxially arranged upwards in turn from the opening of the inner cylinder. The impeller is axial suction and radial discharge. The disk bottom of the flow guide part is sealed with the opening of the inner cylinder. The impeller is coaxially arranged inside the flow guide part, and a flow guide vanes corresponding to a radial exhaust port of the impeller are provided on a circumferential wall of the flow guide part.

Abstract: A centrifugal pump is provided capable of pumping liquid volume flow rates of at least 20 m3/sec. The pump includes a centrifugal impeller rotatable about an axis and operable to direct a liquid towards a concrete volute arranged around the impeller. The pump further includes fixed fin-like elements arranged between the impeller and the volute. The elements form a discontinuous barrier around the impeller and are effective to reduce uneven radial thrusts exerted by the water on the centrifugal impeller, while limiting the water flow rate in a simple and economic manner.

Abstract: A compressor for a gas turbine engine with variable inlet guide vanes each defining an airfoil portion twisted such that at each location of the airfoil portion along the pivot axis, an angle is defined between a respective chord extending between the leading and trailing edges and a same reference plane containing the pivot axis and extending radially with respect to the compressor. The angle, which is measured along a direction of rotation of the rotor, varies from a minimum value near the hub side wall to a maximum value near the shroud side wall. A method of reducing vortex whistle in a radial inlet of a compressor is also provided.

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

Abstract: A compressor that includes an impeller, a diffuser and a shroud. The diffuser includes vanes and one or more projections, each of which extends from a top of a vane. The shroud includes one or more holes. The shroud covers the impeller and the diffuser such that each projection protrudes through one of the holes. The shroud is then secured to the projections by an adhesive.

Abstract: Centrifugal compressors, methods of forming centrifugal compressors, and methods of designing diffuser vanes in centrifugal compressors are provided herein. In an embodiment, a method of designing diffuser vanes includes providing an initial two-dimensional diffuser vane layout including initial diffuser vane peripheries radially spaced about an axis. The initial diffuser vane peripheries are rotated using a computer processor to produce rotated diffuser vane peripheries having offset trailing ends relative to the initial diffuser vane peripheries. The rotated diffuser vane peripheries are circumferentially shifted about the axis to produce shifted diffuser vane peripheries. Leading ends of the shifted diffuser vane peripheries are offset from the leading ends of the initial diffuser vane peripheries. Diffuser vane surfaces are generated that connect the shifted diffuser vane peripheries to the corresponding initial diffuser vane peripheries to form diffuser vanes in a twisted configuration.

Abstract: A diffuser plate for a centrifugal compressor includes an inner edge disposed at an inner diameter about a central axis; an outer edge disposed at an outer diameter, the outer edge displaced an axial distance from the inner edge; a deformable section that includes a substantially S-shaped cross-section, the deformable section disposed between the inner edge and the outer edge; and a spring constant for forced axial displacement of the outer edge with respect to the inner edge, the spring constant characterized, at least in part, by the deformable section.

Abstract: A method for culturing algae comprising, forming an emulsion comprising a gaseous stream and a media utilizing a high shear device, wherein the emulsion comprises gas bubbles, and wherein the high shear device comprises at least one toothed rotor and at least one stator; introducing the emulsion into a bioreactor; and introducing an algae into the bioreactor for growing the algae culture. Additionally, a method for producing liquids from an algae culture, the method comprising forming an emulsion comprising a buffer and algal components, wherein the emulsion comprises algal component globules; separating algal hydrocarbons; and processing algal hydrocarbons to form liquid hydrocarbons. Additionally, a system for producing liquids from an algae culture comprising at least one high shear device.

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 compressor housing for an air cycle machine is provided. The compressor housing includes a body having a compressor volute configured to provide centrifugal compression in the air cycle machine. A mating surface is integrally formed with the body. The mating surface includes a plurality of substantially equally angularly spaced bosses. The bosses include a first boss type at a first radial distance and configured to receive a threaded fastener coupled to a turbine nozzle of the air cycle machine. The bosses also include a second boss type at a second radial distance configured to secure a seal plate of the air cycle machine. The second radial distance is less than the first radial distance. A ratio of a number of the bosses of the first boss type to the second boss type is 17 to 2.

Abstract: A diffuser for a mixed flow or centrifugal compressor of a gas turbine. The diffuser includes at least one vane presenting a pressure side, a suction side, and a first flank. The vane includes a plurality of orifices opening out into the suction side and/or the pressure side and communicating with at least one cavity formed in the vane, the cavity extending transversely relative to the vane and opening out into its first flank. The cross section of the cavity varies in the transverse direction of the vane, the cross section increasing towards the first flank.

Abstract: A diffuser that includes a plurality of radial vanes having a blade count of between 15 and 20, a solidity of between 0.6 and 0.8, and a radius ratio of vane inlet to impeller outlet of less than 1.5. Additionally, a compressor that incorporates the diffuser.

Abstract: A system, in certain embodiments, includes a plurality of detachable, three-dimensional diffuser vanes attached to a diffuser plate of a centrifugal compressor. In certain embodiments, the detachable, three-dimensional diffuser vanes may be attached to the diffuser plate using threaded fasteners. In addition, dowel pins may be used to align the detachable, three-dimensional diffuser vanes with respect to the diffuser plate. However, in other embodiments, the detachable, three-dimensional diffuser vanes may include a tab configured to fit securely within a groove in the diffuser plate. In addition, the tabs of the detachable, three-dimensional diffuser vanes may include indentions that mate with extensions extending from the diffuser plate, wherein the tabs may slide into slots between the extensions and the grooves of the diffuser plate.

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: A centrifugal compressor may comprise a wheel and a pipe diffuser. The pipe diffuser may comprise an annular pipe diffuser section and at least one cylindrical hole passing through the annular pipe diffuser section for compressing gas emerging from the wheel. The at least one cylindrical hole may have an axis that is slanted at an angle A relative to a plane that is orthogonal to an axis of rotation of the compressor.