Abstract: A submersible pump assembly. The submersible pump assembly comprises a motor comprising a first drive shaft; a seal section comprising a second drive shaft that is coupled to the first drive shaft of the motor; and a centrifugal pump assembly comprising a third drive shaft that is coupled to the second drive shaft of the seal section and a plurality of pump stages, wherein each pump stage comprises an impeller coupled to the third drive shaft and a diffuser retained by a housing of the centrifugal pump assembly, wherein the diffuser of each pump stage comprises a first plurality of vanes each having a first axial length and a second plurality of vanes each disposed between a pair of vanes of the first plurality of vanes and each having a second axial length, wherein the second axial length is less than the first axial length.

Abstract: A blower for a breathing apparatus has a diffuser for increasing static pressure and/or reducing noise and/or mitigating pressure instabilities and/or managing reverse flow.

Abstract: A modular heat exchange assembly includes a cold plate defining a finned surface and a corresponding plurality of microchannels. Selected ones of the plurality of microchannel extend from a first end to an opposed second end. A fluid receiver unit defines an inlet port and a first fluid connector fluidically coupled with the inlet port. A fluid transfer unit defines an outlet port and a second fluid connector matingly engageable with and disengageable from the first fluid connector to fluidly couple the fluid receiver unit and the fluid transfer unit together. The fluid transfer unit defines a distribution manifold configured to distribute coolant among the selected microchannels at a position between the first ends and the second ends of the selected microchannels. The fluid transfer unit further defines a collection manifold configured to receive coolant from the selected microchannels. The collection manifold and the outlet port are fluidically coupled together.

Abstract: A double curvature blade for a portion of system. The system may include a pump, such as a submersible pump. The pump may include a multiple or single stage pump. The pump may be powered by a selected motor.

Abstract: A compressor diffuser for a gas turbine engine includes one or more diffuser pipes having a tubular body defining an internal flow passage extending therethrough. The tubular body includes a first portion extending in a first direction, a second portion extending in a second direction different from the first direction, and a curved portion fluidly linking the first portion and the second portion. A splitter vane is disposed within the internal flow passage of the curved portion of the tubular body, the splitter vane defining a convergent flow passage between itself and a radially inner wall of the curved portion, and a divergent flow passage between itself and a radially outer wall of the curved portion.

Abstract: A gas turbine engine for an aircraft having a centrifugal compressor including an impeller with impeller blades extending from a hub, the impeller mounted for rotation about a central longitudinal axis within an outer shroud. A main flow passage wall is located on a shroud side near the impeller exit, the main flow passage wall separating a cavity disposed on the shroud side from the main flow passage. One or more apertures are defined through the main flow passage wall and extending along a respective aperture axis between the cavity and the main flow passage. The apertures have a main flow passage side opening located radially outward from the impeller exit. The aperture axis is disposed at a radial angle relative to the central longitudinal axis.

Abstract: A diffuser assembly is disclosed for conditioning the effluent of a centrifugal compressor. The diffuser assembly comprises an annular conduit, a first set of vanes, and a second set of vanes. The annular conduit comprises a first wall and a second wall displaced from each other and cooperating to define an inlet, an outlet, and a passage extending from the inlet to the outlet. The passage has a first linear portion, a curved portion, and a second linear portion. The first set of vanes are positioned in the first linear portion of said passage. The second set of vanes are positioned in the curved portion of the passage. Each vane of the second set of vanes curves axially and laterally from a vane leading edge to a vane trailing edge.

Abstract: A centrifugal compressor includes an impeller, a diffuser flow passage forming portion forming an annular diffuser flow passage on a downstream side of the impeller, a plurality of small chord-pitch ratio diffuser blades disposed in the diffuser flow passage at intervals in a circumferential direction of the impeller, and a flow passage dividing annulus extending to the diffuser flow passage along a radial direction of the impeller, and dividing the diffuser flow passage into a hub-side flow passage and a shroud-side flow passage.

Abstract: Provided is a radial diffuser that includes a housing, a plurality of diffuser vanes, and a plurality of deswirl vanes and at least one vane extension providing a service routing. Each of the vane extensions is disposed after a radial section and may extend into or through a transition and into the deswirl cascade. At least a portion of the vane extensions include a service passage extending therethrough. Each service passage is configured to allow a service conduit to extend therethrough without adversely crossing either a diffusion flow passage or a transition flow passage.

Abstract: A backfeed stage of a radial turbo fluid energy machine for deflecting a flow direction of a process fluid issuing from a rotor, rotating around an axis, from radially outward to radially inward, having a backfeed duct which has three adjacent sections in the flow direction, wherein a first section is designed for conducting the process fluid radially outward, wherein a second section is designed for deflecting the process fluid from the radially outward to radially inward direction, wherein a third section is designed for conducting the process fluid radially inward, wherein the second section and third section, or only the third section, have/has first guide vanes which define flow passages of the backfeed duct in relation to each other in the circumferential direction.

Abstract: A system, in certain embodiments, includes a centrifugal compressor diffuser including a flow path having a first surface and a second surface defining opposite axial sides of the flow path. The centrifugal compressor diffuser also includes multiple vanes extending from the first surface to the second surface of the flow path. A first profile of each vane varies along an axial direction. The centrifugal compressor diffuser further includes multiple vanelets extending from the first surface toward the second surface in the axial direction. A first axial extent of each vanelet is less than a second axial extent of the flow path. In addition, a second profile of each vanelet varies along the axial direction and/or the vanelets form a non-periodic pattern around a circumference of the flow path.

Abstract: A system, in certain embodiments, includes a centrifugal compressor diffuser vane including a leading edge, a trailing edge, and a constant thickness section extending between the leading edge and the trailing edge. A radius of curvature of the leading edge and a radius of curvature of the trailing edge vary along a span of the vane. A ratio of a length of the constant thickness section to a chord length of the vane is at least approximately 50%, and the ratio is substantially constant along the span of the vane.

Abstract: A system, in certain embodiments, includes a centrifugal compressor diffuser including a flow path having a first surface and a second surface defining opposite axial sides of the flow path. The centrifugal compressor diffuser also includes multiple vanes extending from the first surface to the second surface of the flow path. A first profile of each vane varies along an axial direction. The centrifugal compressor diffuser further includes multiple vanelets extending from the first surface toward the second surface in the axial direction. A first axial extent of each vanelet is less than a second axial extent of the flow path. In addition, a second profile of each vanelet varies along the axial direction and/or the vanelets form a non-periodic pattern around a circumference of the flow path.

Abstract: A system, in certain embodiments, includes a centrifugal compressor diffuser including a flow path having a first surface and a second surface defining opposite axial sides of the flow path. The centrifugal compressor diffuser also includes multiple vanes extending from the first surface to the second surface of the flow path. A first profile of each vane varies along an axial direction. The centrifugal compressor diffuser further includes multiple vanelets extending from the first surface toward the second surface in the axial direction. A first axial extent of each vanelet is less than a second axial extent of the flow path. In addition, a second profile of each vanelet varies along the axial direction and/or the vanelets form a non-periodic pattern around a circumference of the flow path.

Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

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 motor suspension for fans has an air grille with radially extending braces and grille rings that are positioned coaxially to each other and are connected to each other by the radially extending braces. For adapting the motor suspension to a vibration behavior of a fan, at least one of a feature selected from a number of the braces and a diameter of the braces is varied to effect a reduction of acoustic noises and/or natural resonances of the motor suspension. The number of the braces that are preferably made of metal is preferably unequal to the number of vanes of the fan.

Abstract: A restraint system (300, 300?, 500) for a vaned diffuser (225) of a turbocharger (100) or other fluid boosting device is provided that can reduce or eliminate losses. The system (300, 300?, 500) uses a structure to provide both a pressure load on the vaned diffuser (225) and a seal for the vaned diffuser (225). The structure can be a fluoroelastomer O-ring (350, 350?, 550). The O-ring (350, 350?, 550) can be positioned at least partially in a channel (325, 325?, 525) formed in at least one of the diffuser ring (206, 206?), the compressor housing (103) and the center housing (102).

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: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

Abstract: The guide device for the diffusor at the compressor impeller outlet of a radial compressor has guide blades with stepped inlet edges. The step is implemented by setting back the hub-side inlet edge. This meridional stepping divides the guide blades into two component blades, of which the first component blade is made longer than the second component blade. The set-back of the inlet edge of the hub-side component blade and the associated superposition of the noise fields which are produced on the front and rear inlet edge of the diffusor leads to improvement of the acoustic properties of the compressor.

Abstract: A turbomachine including an annular combustion chamber, a centrifugal compressor, an annular diffuser enabling the flow of gas leaving the compressor to be diffused and directing this flow of gas towards the combustion chamber, and an outer casing surrounding the outside of the combustion chamber is disclosed. The diffuser includes an upstream portion oriented radially and presenting diffusion passages connected to the outlet from the compressor, an intermediate portion that is elbow-shaped, and a downstream portion having a series of circularly spaced-apart flow-straightening vanes. The flow stream in the downstream portion is delimited externally by the outer casing. The outer casing presents a shoulder against which the outer downstream edge of the intermediate portion comes into abutment.

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: A casing for an aircraft turbine bypass engine comprises a splitter having slots to receive and be welded to a plurality of struts extending between an outer ring and an inner hub of the casing.

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 gas turbine engine rotor stack includes one or more longitudinally outwardly concave spacers. Outboard surfaces of the spacers may be in close facing proximity to inboard tips of vane airfoils. The airfoils have dihedral and sweep.

Abstract: A support system for a motor within a fan shroud. Struts extending from the shroud to the motor support the motor. The struts are arranged in groups, which are spaced from adjacent groups, and each group contains a non-radial strut.

Abstract: An integrated assembly is provided for a centrifugal compressor, which integrates selected static portions of the centrifugal compressor into a monolithic structure to allow a small deflection of the inner flow path at assembly. The integrated assembly may include a machined compressor shroud casting having integral diffuser vanes, an aft sheet metal inner flow ring having a radially extending rim with slots in the inner flow ring for receiving diffuser vanes and slots in the rim for receiving deswirler vanes, an outer deswirler band surrounding the inner flow ring and having slots opposing those in the rim, and a plurality of deswirler vanes for fabrication between the inner flow ring and the deswirler band within the respective slots.

Abstract: Systems and methods for absorbing acoustic noise generated by computer cabinet cooling fans are described herein. In one embodiment, an acoustic absorber for use with a fan carried by a computer cabinet in a room includes a first acoustic panel spaced apart from a second acoustic panel. The first acoustic panel is configured to be positioned proximate to an outlet of the fan and at least approximately parallel to a flow of cooling air discharging from the outlet. The second acoustic panel is also configured to be positioned proximate to the outlet of the fan and at least approximately parallel to the flow of cooling air discharging from the outlet. The first and second acoustic panels together form an opening configured to direct the flow of cooling air away from the fan outlet and into the surrounding room. In a further embodiment, the opening formed by the first and second acoustic panels can be configured to extend at least approximately 360 degrees around the fan.

Abstract: Integrally formed stamping sheet-metal blades having 3D structure for impeller or diffuser of a centrifugal pump or blower includes at least two integral forming blade or vane members. Each blade or vane member has a plurality of relatively short 3D blades or vanes extending radially outward and an engaging edge of selected shape. Two or more blade or vane members may be positioned and stacked together through mating the engaging edge and be spot welded to form a complete impeller or diffuser assembly. The blade or vane may be joined to form a completed smooth blade or vane, or may be spaced from each other to form a multi-row blade or vane assembly. The impeller and vane assembly may be made with less number of stamping molds and jigs. Production is less expensive. Positioning and assembly of the blade and vane is easier at a lower cost.

Abstract: The centrifugal compressor of the present invention is equipped with a plurality of vane groups (A, B) comprised of a plurality of vanes (16A, 16B) disposed in the peripheral direction of an impeller (12) so as to be concentric about the center of an axis of rotation (15) of the impeller, and the individual vanes (16A) belonging to vane group (A) nearest to the impeller are able to rotate. Since diffuser efficiency decreases if the intake flow volume of the impeller changes and the flow of gas is unable to easily continue from the vanes (16A) to vanes (16B), the vanes (16A) are rotated to change the inclination of the direction of a wing center line on their front edges so as to coincide with the direction of the flow of gas discharged from the impeller. As a result, diffuser efficiency is maintained at a high level even if the intake flow volume of the impeller is changed.

Abstract: The centrifugal compressor of the present invention is equipped with a plurality of vane groups (A, B) comprised of a plurality of vanes (16A, 16B) disposed in the peripheral direction of an impeller (12) so as to be concentric about the center of an axis of rotation (15) of the impeller, and the individual vanes (16A) belonging to vane group (A) nearest to the impeller are able to rotate. Since diffuser efficiency decreases if the intake flow volume of the impeller changes and the flow of gas is unable to easily continue from the vanes (16A) to vanes (16B), the vanes (16A) are rotated to change the inclination of the direction of a wing center line on their front edges so as to coincide with the direction of the flow of gas discharged from the impeller. As a result, diffuser efficiency is maintained at a high level even if the intake flow volume of the impeller is changed.

Abstract: A diffuser for a centrifugal compressor in which the diffuser has a plurality of passageways that each include a diffuser inlet region, a diffuser throat region, and a diffusion region. Within the diffuser inlet region are positioned pairs of opposed ridges that disrupt the boundary layer growth and minimize aerodynamic blockage at the throat region. The diffusion region includes a first diffusion region downstream of the throat region and that has a first area expansion ratio, and the second diffusion region that includes flow dividers to allow a total area expansion rate within the second diffusion region that is about twice that of the area expansion rate in the first diffusion region.

Abstract: A turbine comprises a housing having an inlet and an outlet, a stator mounted in the housing and including an arcuate stator blade projecting radially inward, and a turbine rotor having a central annular jet path accommodating therein said arcuate stator blade in communication with the inlet and the outlet. The turbine rotor comprises a pair of annular flywheel discs formed with pluralities of rotor blades facing each other in an axial direction. The arcuate stator blade has at least one deflection guide to direct the jet stream of working fluid toward the rotor blades in the central annular jet path.

Abstract: In a multi-stage centrifugal compressor, having a plurality of impellers mounted on a rotation shaft, or a single-stage centrifugal compressor, a vaned diffuser, having a plurality of vanes, is mounted at a downstream side of the impeller, and a vaneless diffuser portion is formed downstream of this vaned diffuser. A meridian plane cross-sectional shape of each of two wall surfaces forming the vaneless diffuser portion provided downstream of the vaned diffuser is such that its channel height is decreased progressively in a downstream direction. Instead of this vaneless diffuser, there can be provided a second vaned diffuser having a small number of vanes. In this case, also, two wall surfaces, forming the second vaned diffuser, are contracted progressively in the downstream direction.

Abstract: A wave augmented diffuser for a centrifugal compressor surrounds the outlet of an impeller that rotates on a drive shaft having an axis of rotation. The impeller brings flow in in an axial direction and imparts kinetic energy to the flow discharging it in radial and tangential directions. The flow is discharged into a plurality of circumferentially disposed wave chambers. The wave chambers are periodically opened and closed by a rotary valve such that the flow through the diffuser is unsteady. The valve includes a plurality of valve openings that are periodically brought into and out of fluid communication with the wave chambers. When the wave chambers are closed, a reflected compression wave moves upstream towards the diffuser bringing the flow into the wave chamber to rest. This action recovers the kinetic energy from the flow and limits any boundary layer growth. The flow is then discharged in an axial direction through an opening in the valve plate when the valve plate is rotated to an open position.