Abstract: An apparatus and method for an engine component having a working airflow separated into a cooling airflow and a combustion airflow, the engine component comprising a plurality of circumferentially spaced airfoils rotatable about a centerline defining an axial direction, each airfoil comprising an outer wall bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip along a span-wise direction to define a span length; wherein each of the airfoils have an unguided turning angle to stagger angle ratio defined with respect to a percentage of the span length.

Abstract: A multistage centrifugal pump for conveying a fluid includes a pump housing, two first stage impellers, a last stage impeller and a shaft. The two first stage impellers and the last stage impeller convey the fluid from a housing inlet to a housing outlet. The shaft rotates each impeller about an axial direction, each impeller comprising a suction side to receive the fluid and a discharge side to discharge the fluid. The last stage impeller is a double suction impeller, having a first suction side and a second suction side, and the last stage impeller is arranged between the two first stage impellers with respect to the axial direction. Each impeller of the two first stage impellers is arranged with the suction side of a respective first stage impeller facing one of the first and second suction sides of the last stage impeller.

Abstract: A cooling fan and an electronic device are provided. The cooling fan comprises a plurality of blades disposed in a circumferential direction of a rotating shaft. The plurality of blades includes a first blade and a second blade. A windward surface of the first blade includes a first alignment part and a first offset part. The first alignment part is aligned with a windward surface of the second blade, and the first offset part and the windward surface of the second blade are arranged in a staggered manner.

Abstract: A centrifugal blower includes a centrifugal fan and a separation cylinder. The centrifugal fan has a separation plate. The separation cylinder is disposed inward of the blades in the radial direction of the centrifugal fan. The separation plate has an inner end surface extending from the one side to the other side in the axial direction at a position of an inner end in the radial direction. The separation cylinder has a separation cylinder end surface extending from the one side to the other side in the axial direction at a position of an end on the other side in the axial direction. A height of one of the separation cylinder end surface and the inner end surface in the axial direction is larger than a height of the other of the separation cylinder end surface and the inner end surface in the axial direction.

Abstract: A liquid pump for use with a fluid circulation system for a body of water includes a strainer assembly; a centrifugal pump assembly having at least first and second outlet ports respectively oriented in vertical and horizontal directions; a motor; and, at least one cap configured and dimensioned to engage and close an outlet port.

Abstract: A centrifugal blower assembly comprises a scroll wall and a pair of opposing sidewalls. The scroll wall is positioned between the pair of opposing sidewalls such that the scroll wall and opposing sidewalls together define a blower chamber and a blower outlet. A baffle element is positioned within the blower chamber and adjacent the blower outlet such that the baffle element is configured to facilitate uniform distribution of airflow downstream of the blower assembly. An air stream splitter is coupled to the scroll wall. The air stream splitter includes a spline member extending a varying distance from the scroll wall. The air stream splitter is positioned within the blower chamber to facilitate uniform airflow distribution within the blower assembly.

Abstract: A vertically shafted air moving device for circulating air includes a housing that defines an internal space. A shell is coupled to and extends from a top of the housing. The shell is meshed. The shell is configured to allow air to enter and exit the shell. A power module and a motor are coupled to the housing and are positioned in the internal space. The motor is operationally coupled to the power module. A shaft is coupled to and extends from the motor into the shell. Each of a plurality of blades is coupled to and extends from the shaft to proximate to an interior face of the shell. The motor is positioned to compel rotation of the shaft coincident with the blades. The blades are configured to circulate air in proximity to the shell.

Abstract: A fluid machine includes a rotatable hub; a plurality of blades spaced apart from one another along a circumferential direction with respect to a rotation center of the hub; and a shroud extending along a circumferential direction with respect to the rotation center of the hub and covering the plurality of blades. The shroud includes: a flow passage, the flow passage formed to be recessed with respect to an inner surface of the shroud facing the blades; and a plurality of resonators provided in the flow passage.

Abstract: The present invention provides a pump impeller which has improved anti clogging characteristics, in particular through the use of an impeller vane having a specially profiled leading edge which, during operation of the impeller, forces rags or the like down along the leading edge, which increases in thickness along the length thereof, until the rags become re-entrained in the fluid and thus exit the impeller avoiding the clogging thereof.

Abstract: Embodiments of the invention provide a ventilation assembly including a scroll assembly that can include a blower assembly including a motor coupled to a blower wheel. Some embodiments include a discharge grid capable of being coupled to the scroll using a coupling pin or snap tabs. In some embodiments, the discharge grid includes a plurality of vertical and horizontal fins, and an outlet restriction. In some embodiments, at least one of the plurality of horizontal fins extends from the outlet restriction to couple with at least one vertical fin to form an aperture. In other embodiments, at least a portion of at least one of the plurality of vertical and horizontal fins includes a flared surface. Some embodiments include a scroll assembly that includes a scroll crescent. In some embodiments, a scroll including a discharge grid and scroll crescent can at least partially guide a fluid within the ventilation assembly.

Abstract: A turbine comprising an intermediate casing axially inserted between an upstream high pressure turbine casing and a downstream low pressure turbine casing and comprising an outer annular shroud from which an annular flange radially extends, characterized in that the downstream end of the high pressure turbine casing and the upstream end of the low pressure turbine casing are attached on the radial annular flange of the intermediate casing.

Abstract: A modular fan blade includes a first fan blade and a second fan blade. The first fan blade includes a hub and plural first vanes, and the hub has an external periphery, and the first vane is combined with the external periphery, and a flange is formed at the external periphery and a retaining space is formed on a surface of the flange; and the second fan blade includes a fan frame and plural second vanes, and the fan frame is installed at the flange of the hub, sheathed on the hub, and installed in the retaining space, so as to achieve the effects of increasing the wind output of the fan effectively and replacing the blades conveniently.

Abstract: The present disclosure provides an impeller and a mold for manufacting the impeller. The impeller includes a plurality of blades, and there is an overlapped area between two adjacent blades. The mold includes a first part, a second part and a plurality of slide groups. The first part and the second part move in a mold opening direction. At least a portion of each slide group is located in the overlapped area, and each slide group has a first slide block and a second slide block, and a movement direction of the first slide block and the second slide block is perpendicular to the mold opening direction. By using that the movement direction of the slide group is perpendicular to the mold opening direction, the impeller with blades that have the overlapped area may be manufactured. The blades of the impeller may have a special shape.

Abstract: A turbocharger (5) comprising a housing (10) including a compressor shroud (14) and a turbine shroud (12). A compressor wheel (18) is disposed in the compressor shroud (14) and includes a plurality of compressor blades (45, 46). Each compressor blade (45, 46) includes a leading edge (50, 51) and a compressor shroud contour edge (54, 55), wherein each compressor shroud contour edge (54, 55) is in close confronting relation to the compressor shroud (14). A turbine wheel (16) is disposed in the turbine shroud (12) and includes a plurality of turbine blades (26). Each turbine blade (26) includes a leading edge (30) and a turbine shroud contour edge (34), wherein each turbine shroud contour edge (34) is in close confronting relation to the turbine shroud (12). At least one of the compressor shroud (14) and turbine shroud (12) includes a plurality of grooves (70, 72) extending cross-wise with respect to the corresponding compressor or turbine shroud contour edges (34, 54, 55).

Abstract: A pump for pumping a multiphase fluid includes a housing and a rotor with an outer surface. A plurality of inducer vanes are attached to the rotor hub, each having a leading edge and a trailing edge where the leading edge of one inducer vane overlaps the trailing edge of an adjacent inducer vane by a first overlap angle. A plurality of impeller vanes are also attached to the hub. The impeller vanes each have a leading edge and a trailing edge where the leading edge of one impeller vane overlaps the trailing edge of an adjacent impeller vane by a second overlap angle larger than the first overlap angle. The pump includes a rotor flow channel extending between the hub outer surface and the housing inner surface. The rotor flow channel has an inlet area and an outlet area, whereby the outlet area is smaller than the inlet area.

Abstract: An impeller of a rotary machine, in which the direction of flow changes from an axial direction to a radial direction as it goes from the inside in the radial direction of a fluid flow passage to the outside in the radial direction thereof, includes a hub surface constituting at least a portion of the fluid flow passage. The impeller also includes a blade surface constituting at least a portion of the fluid flow passage, and a bulge that bulges toward the inside of the fluid flow passage at a corner where a pressure surface, which configures the blade surface, comes in contact with the hub surface in the vicinity of an inlet of the fluid flow passage.

Abstract: A gas turbine engine has a plurality of compressor rotors, as well as a plurality of turbine rotors. A tie shaft of the engine is constrained to rotate with the compressor and turbine rotors during normal operating conditions. Further, an upstream hub is in threaded engagement with the tie shaft. The threads of the upstream hub are handed in a first manner when viewed from an upstream location. A downstream abutment member is positioned downstream of the turbine rotors and is also in threaded engagement with the tie shaft. Threads of the downstream abutment member are handed in the first manner when viewed from a downstream location. Accordingly, the compressor and turbine sections of the engine are reliably held together, and the tie shaft is substantially prevented from unwinding.

Abstract: There is provided a centrifugal fan including an upper casing which has an air suction opening, a lower casing, and an impeller which is disposed between the upper casing and the lower casing. The impeller includes an upper shroud which is provided on an upper casing side, and a plurality of blades which are arranged along a circumference direction below the upper shroud, and is rotatable around a rotary shaft. The upper casing and the lower casing configure an open-type casing. A surface of the upper shroud facing the upper casing includes a first portion which becomes closer to the lower casing as separating further from the rotary shaft. A surface of the upper casing facing the upper shroud includes a second portion which faces the first portion of the upper shroud and becomes closer to the lower casing as separating further from the rotary shaft.

Abstract: A centrifugal compressor includes a rotor assembly with a shaft and a plurality of impellers, bearings located at ends of the shaft and configured to support the rotor assembly, a sealing mechanism disposed between the rotor assembly and the bearings, and a gas bearing disposed between the plurality of impellers for supporting the shaft and receiving a working gas from an impeller downstream from a location of the gas bearing.

Abstract: An air-intake assembly adapted for use with a fire container assembly includes a first plate and a plurality of vanes. The plurality of vanes is engaged to the first plate. Each of the vanes includes a first longitudinal side engaged to the first plate and an oppositely disposed second longitudinal side. The plurality of vanes defines a plurality of pathways. A chamber is cooperatively defined by the first plate and the plurality of vanes. The chamber extends through the first plate. The plurality of pathways swirl air about a longitudinal axis of the chamber.

Abstract: In order to increase the flexibility of the positioning of a stacked computer system within a data center, a removable fan unit is positioned within the stacked computer system. The removable fan unit includes a housing and a fan housing rotatably attached to the housing. The fan housing supports a fan that is electrically connected to a connector on a side of the housing of the removable fan unit. The connector of the removable fan unit may be electrically connected to a computer system-side connector. The fan housing may be rotated into at least two different orientations relative to the housing of the removable fan unit, such that the removable fan unit moves air through the stacked computer system in at least two corresponding directions.

Abstract: The present application thus provides a gas turbine engine. The gas turbine engine may include a turbine and a diffuser positioned downstream of the turbine. The turbine may include a number of last stage buckets, a number of last stage nozzles, and a gauging ratio of the last stage nozzles of about 0.95 or more.

Abstract: Method and rotor for a compressor. The rotor includes a solid first stub having a first end configured to engage with a corresponding bearing and a second end having a flange configured to be attached by bolts to a corresponding flange of a first impeller of the compressor; a tie rod configured to pass through the first impeller of the compressor; a nut being configured to engage a threaded region of the first end of the tie rod; and a solid second stub having a first end configured to receive the threaded portion of the second end of the tie rod and a second end configured to engage with a corresponding bearing. The tie rod does not contact the solid first stub.

Abstract: A shaft assembly for a gas turbine engine that includes a shaft with a threaded shaft segment, an annular rotor disposed on the shaft, and annular stack nut. The stack nut includes a base nut segment and a clamping nut segment. The base nut segment includes a threaded nut bore that is mated with the threaded shaft segment. The clamping nut segment axially extends from the base nut segment to a load bearing surface. The clamping nut segment includes a radial thickness that decreases as the clamping nut segment extends from the load bearing surface towards the base nut segment. The load bearing surface exerts a force against the rotor securing the rotor to the shaft.

Abstract: Disclosed is a vacuum self-priming pump in which a main pumping chamber and a sub-pumping chamber divided from each other by a diaphragm are provided within a case, main impellers and a sub-impeller rotated by a motor are respectively installed within the main pump chamber and the sub-pumping chamber such that a space is formed between a pair of left and right main impellers, and connection pipes are respectively formed between suction pipes of the main pumping chamber and the sub-pumping chamber and between discharge pipes of the main pumping chamber and the sub-pumping chamber, so as to more rapidly suck fluid every pumping operation and to effectively pump the fluid without clogging even if the pumped fluid contains various sludge or solid matter.

Abstract: A turbomachine rotor includes: a rotor body having an outer surface; and a patterned abrasive or abradable coating formed over the outer surface of the rotor body, the patterned abrasive or abradable coating for directing a flow of a working fluid across the turbomachine rotor.

Abstract: A multistage radial turbocompressor has at least first, second, and third intake parts each forming a respective intake spaced along an axis and first, second, and third output parts each forming a respective output axially juxtaposed with the respective intakes. Respective first, second, and third fans having axially directed vanes are rotatable in the housing formed by the parts between the intakes and outputs. A shaft centered on the axis carries the first, second, and third fans. One of the fans is back-to-back with another of the fans with the vanes of the one fan facing axially oppositely away from the vanes of the other of the fans. Radial bearings support the shaft in the housing, and an axial bearing between the one fan and the other fan supports the shaft in the housing.

Abstract: A gas turbine engine comprises a fan and a turbine section having a first turbine rotor. The first turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from a fan drive turbine rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor: (the number of blades×the rotational speed)/(60 seconds/minute)?5500 Hz; and the rotational speed being in revolutions per minute. A compressor module and a method of designing a gas turbine engine are also disclosed.

Abstract: A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s?5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine and a compressor module are also disclosed.

Abstract: A gas turbine engine has a fan, a compressor section having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a low pressure portion. The low pressure turbine portion drives the low pressure compressor portion and the fan. A gear reduction effects a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor portion. At least one of the low pressure turbine portion and low pressure compressor portion has a number of blades in each of a plurality of rows. The blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the at least one of the low pressure turbine portion and/or the low pressure compressor sections: (number of blades×rotational speed)/60?5500. The rotational speed is an approach speed in revolutions per minute.

Abstract: A divisible housing of a fluid machine for a transmission to be received in the divisible housing is provided. The transmission provided for receiving in the divisible housing includes a large wheel and at least two pinion shafts which are in engagement with the large wheel. The divisible housing includes a first housing element and a second housing element which is connected to the first housing element via a parting joint. The at least two pinion shafts may be received in the parting joint. The parting joint includes a parting joint step, the at least two pinion shafts being receivable in the parting joint on both sides of the parting joint step.

Abstract: The flow path of exhaust gas to the turbine wheel (70) of a twin volute turbocharger is influenced by the shape and size of the nozzle formed by the shape (22) of the divider wall (21) and the shape of the flow passage determined by the walls (85, 86) of the turbine housing. By moving the walls (85, 86) toward, or away from the divider wall, the flow of exhaust gas through the nozzle, to the turbine wheel (70) can be modulated, which thus modulates the turbocharger boost pressure. The invention also applies to single volute turbines.

Abstract: The invention relates to a rotor wheel constructed of sheet metal for a centrifugal pump, particularly a multi-stage centrifugal pump, with means for fastening to the drive shaft of an electric motor, wherein the rotor wheel has a central coaxial opening in which a sleeve is fastened coaxially, wherein the sleeve projects out of the rotor wheel on at least one side of the rotor wheel, and wherein the sleeve has, in its inner wall, projecting, axially parallel ridges for fastening into axially parallel notches or grooves of the motor drive shaft.

Abstract: A gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in operational noise that is above a sensitive range for human hearing. A method and turbine module are also disclosed.

Abstract: A centrifugal pumping system having a stack of impellers and diffusers for pressurizing fluid. The impellers are rotated by a motor for pressurizing and lifting fluid from within a wellbore. Undulating profiles are provided on leading edges of the impellers for inducing turbulence in the fluid being pumped. Increasing turbulence better homogenizes the fluid, so that choked flow is avoided when different density components are present in the fluid. Reducing the possibility of choked flow increases pump efficiency and lift capacity.

Abstract: A centrifugal blower apparatus includes a scroll-shaped housing with first and second air inlets which open to a blower chamber that is in fluid communication with an air outlet. The blower includes a motor to drive an impeller, wherein the motor is secured to a frame that is coupled with the housing in a manner to substantially enhance aerodynamic performance of the blower.

Abstract: A vane structure of a gas turbine engine includes a plurality of vanes extending radially between outer and inner shrouds. At least the outer shroud is formed substantially from a single-piece annular skin of sheet metal. A plurality of reinforcing plates are placed against and are affixed to an outer surface of the skin of the outer shroud in respective joining locations where a radial outer end of each of the respective vanes joins the skin.

Abstract: A centrifugal fan with a multistage impeller includes a hub and a multistage impeller having at least two stages of blade assemblies. The hub has a top section and a circumferential section extending from the top section. At least one extension section outward extends from the circumferential section. The multistage impeller is connected with one end of the extension section. The multistage impeller includes a first-stage blade assembly and a second-stage blade assembly. The second-stage blade assembly has a diameter larger than that of the first-stage blade assembly. The centrifugal fan can be installed in an application environment with limited space without being interfered with by peripheral parts. Also, the centrifugal fan is able to provide an optimal flow and wind pressure at the same rotational speed to lower the load on the motor and reduce the noise.

Abstract: A method of operating an axial turbine, having a stage including stationary blades and moving blades, each stationary blade having a radial height of an outlet thereof higher than the radial height of an inlet thereof, each moving blade being located downstream of a corresponding one of the stationary blades along a flow direction of a working fluid, the moving blades being constructed such that a moving blade front-end peripheral velocity Mach number exceeds 1.0, the method including restraining a radial velocity component of a working fluid flowing through an outer peripheral portion of the stationary blade from the stationary blade inlet to the stationary blade outlet, whereby the working fluid having passed through the stationary blade flows substantially parallel to the central axis of the turbine from the stationary blade outlet to the moving blade inlet.

Abstract: A multi-stage centrifugal pump assembly includes at least two impellers (2, 6) and two impeller groups (4, 8) which are consecutive in a flow direction and each with at least one impeller (2, 6). A backflow channel (24) connects an exit side of the first impeller group (4) to an entry side thereof is located in a first impeller group (4) of the two impeller groups (4, 8).

Abstract: A rotor (10) of a rotary machine (T1) according to the invention includes a plurality of rotor members (20, 30, and 40) which are joined to each other in the axial direction in which the axis (P) extends, and among the plurality of rotor members (20, 30 and 40), the first rotor member (30) in hydraulic fluid injection portions (3a and 3b) of a passageway (3) is formed of Ni-based alloy so that the inside thereof is hollow throughout the entire length in the axial direction.

Abstract: A pump includes a cutting impeller (38) and a pre-chopper (50) driven by a shaft portion (46) that projects axially from the cutting impeller (38), with the pre-chopper (50) being surrounded by an intake port (22) of the pump, the intake port having, at least on a part of its length, in the vicinity of the pre-chopper, a non-circular internal cross-section.

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 gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in operational noise that is above a sensitive range for human hearing. A method and turbine module are also disclosed.

Abstract: A multi-impeller arrangement and to a pump having the impeller arrangement. The impeller arrangement or impeller cluster includes at least two impellers, each impeller having an annular back plate and an annular front plate. The impellers are releasably secured together in an axially in-line series having the front plate of a first impeller at one end and the back plate of a second impeller at the other end. The second impeller includes an axial projection which extends from its back plate, through and beyond its front plate to the first impeller. The first impeller is engaged with the projection of the second impeller such that all impellers are rotatable as an assembly.

Abstract: An air diffuser system for an impeller for a centrifugal pump has least one channel (36) with first opening (40) through the backside (14) and a second opening (42) through the front side (38) of the impeller (12). Tubes (44) are associated with each channel (36) and extend from the backside (14) of the impeller (12). Tube ends (48) are oriented in the direction of rotation (46) of the impeller (12).

Abstract: A waterproof and dustproof fan motor structure includes a base, an annular enclosure, and a stator assembly. The base has a vertically forward extended bearing cup; the annular enclosure internally defines a closed annular space and is externally fitted around the bearing cup; and the stator assembly is disposed in the closed annular space of the enclosure. The waterproof and dustproof fan motor structure can be assembled to a frame and a rotor assembly to complete a fan. With the stator assembly disposed in the closed annular space of the enclosure, the fan motor is protected against damage caused by moisture and dust, and the stator assembly can be easily removed from the closed annular space for necessary maintenance and repair to thereby reduce the bad yield and the manufacturing cost of fan and fan motor.

Abstract: A fan device includes a housing, a fan wheel assembly, a stator and an enclosure unit. The fan wheel assembly is located within the housing and includes a rotor and a plurality of blades. The stator is connected to a circuit board, and the enclosure unit encloses the stator and the circuit board therein, and is located within the housing. The enclosure unit has at least an extension portion located corresponding to the blades. Heat produced by the stator and the circuit board is transferred to the extension portion and then carried away therefrom by airflow that is sucked into the housing by the blades and blown to the extension portion, so as to cool the extension portion and produce a heat dissipation effect to the stator and the enclosure unit.

Abstract: A multistage pump assembly includes a manifold having an inlet port configured to be coupled to a supply pipe and an outlet port configured to be coupled to a discharge pipe. The inlet and outlet ports define an end suction, radial outlet port configuration. The pump assembly also includes a cartridge having a sleeve and plurality of pumping stages that define a pump stack received within the sleeve. An outer chamber is defined between the pump stack and the sleeve. Each of the pumping stages includes an impeller mounted along a pump shaft that rotates about a rotation axis. The cartridge is aligned horizontally such that the rotation axis is substantially horizontal. An end plate is positioned between the manifold and the cartridge and includes at least one cartridge engagement surface supporting the cartridge. The end plate is removably coupled to the manifold.

Abstract: The present invention relates to a multi-stage turbocharger arrangement (1), having a high-pressure turbocharger (20) which has a turbine housing (26A), a bearing housing (27A), a compressor housing (28A); and having a low-pressure turbocharger (21) which has a turbine housing (26B), a bearing housing (27B), a compressor housing (28B); wherein the turbine housings (26A, 26B) are combined to form at least one turbine housing unit (26), and/or wherein the bearing housings (27A, 27B) are combined to form at least one bearing housing unit (27), and/or wherein the compressor housings (28A, 28B) are combined to form at least one compressor housing unit (28).