Abstract: The subject matter of this specification can be embodied in, among other things, a thrust reverser tertiary lock apparatus that includes a probe affixed to an aircraft engine frame and having a shaft having a barb at a first end and configurable to a first configuration and a second configuration, and a receiver affixed to a thrust reverser transcowl slider configured to accommodate the barb and having an end wall with an aperture defined therein, the aperture shaped to permit escapement of the barb in the first configuration and prevent escapement of the barb in the second configuration.

Abstract: A mounting assembly is provided. The mounting assembly includes a first flange; a second flange; a first asymmetric spacer; a second asymmetric spacer; and a bolt configured to pass through a void of the first asymmetric spacer starting at a first end, through at least one first opening of the first flange, through at least one second opening of the second flange, through a void of the second asymmetric spacer starting at a second end, and to be coupled to a nut, such that, in response to the nut being fastened to the bolt, the bolt bends due to a non-vertical slope of the first asymmetric spacer and a non-vertical slope of the second asymmetric spacer.

Abstract: A bearing and/or seal assembly where pressurized gas (e.g., air) may be arranged to produce a contact-free bearing and/or seal is provided. The assembly includes a permeable body (12) including structural features (13) selectively engineered to convey a pressurized gas (Ps) from an inlet side (20) side of the permeable body to an outlet side (22) of the permeable body to form an annular film of the pressurized gas relative to the rotatable shaft. Disclosed embodiments may be produced by way of three-dimensional (3D) Printing/Additive Manufacturing (AM) technologies with practically no manufacturing variability; and may also cost-effectively and reliably benefit from the relatively complex geometries and the features and/or conduits that may be involved to, for example, form the desired distribution pattern or impart a desired directionality to the pressurized gas conveyed through the permeable body of the bearing and/or seal assembly.

Abstract: An electrical submersible pump assembly comprising a first section and a second section with an outer housing and a drive shaft. A coupling assembly comprising a coupling, a thrust pin, and a retainer ring mechanically couples the first drive shaft to the second drive shaft. The coupling is generally cylindrical in shape with splines formed along the inner surface configured to transfer torque from the first shaft to the second shaft. The thrust pin is installed in a pin bore in the lower shaft and extends into a retainer bore in the upper shaft. The retainer ring is installed between a groove in the retainer bore and a retainer groove on the outside of the thrust pin. The thrust pin is configured to transfer tensile stress from the retainer bore in first drive shaft to the pin bore in the second drive shaft.

Abstract: An aircraft engine, comprising: a first wall and a second wall defining a gaspath between the first wall and the second wall, the gaspath extending around a central axis, each of the first wall and the second wall having a gaspath side facing the gaspath and an opposed side facing away from the gaspath; struts circumferentially distributed around the central axis, the struts extending across the gaspath, a strut of the struts having an airfoil including a leading edge, a trailing edge, a first end secured to the first wall, and a second end secured to the second wall; and protrusions extending from a baseline surface of the opposed side of the first wall, the protrusions increasing a thickness of the first wall, a protrusion of the protrusions overlapping a location where the leading edge or the trailing edge meets the gaspath side of the first wall.

Abstract: An axial fan includes a housing, an upper motor, and a lower motor. The housing includes an upper housing and a lower housing. A lower peripheral wall of the lower housing includes first engaging portions and lower protruding pieces. The lower protruding pieces oppose the first engaging portions in an axial direction and protrude axially upward from an axially upper surface. An upper peripheral wall of the upper housing includes upper engaging claws and upper notch grooves. The upper engaging claws extend axially downward from an axially lower surface, and include a second engaging portion that engages with the first engaging portion in a lower end portion. The upper notch grooves are notched axially upward from the axially lower surface radially inward of the upper engaging claw. At least a portion of the lower protruding pieces is located in the upper notch grooves.

Abstract: A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.

Abstract: A turbine shroud assembly includes a carrier assembly, a blade track segment, a retainer, and a clip shim. The carrier assembly is arranged circumferentially at least partway around an axis. The blade track segment is supported by the carrier assembly to locate the blade track segment radially outward of the axis and define a portion of a gas path of the turbine shroud assembly. The retainer extends into the carrier assembly and the blade track segment. The clip shim is located between the carrier assembly and the blade track and configured to urge the blade track segment axially toward the carrier assembly.

Abstract: A structure for a gas turbine engine includes a first engine component, a second engine component and fasteners. The component apertures include first fastener apertures and intergroup apertures. The first fastener apertures are arranged into a plurality of groups. The first group is formed by N1-number of the first fastener apertures. The second group is formed by N2-number of the first fastener apertures where the N2-number is different than the N1-number. Each of the intergroup apertures is disposed circumferentially between and adjacent a respective circumferentially neighboring pair of the groups. The second engine component includes a surface and second fastener apertures. The surface axially engages the first engine component and covers the intergroup apertures. The fasteners attach the first engine component and the second engine component together. Each of the fasteners is mated with one of the first fastener apertures and one of the second fastener apertures.

Abstract: An ammonia plant synthesis gas compressor train includes a steam turbine; and a compression unit that compresses a synthesis gas by being rotationally driven by the steam turbine. The compression unit includes a rotary shaft that rotates around an axis, and a plurality of impellers that are provided on the rotary shaft at intervals in a direction of the axis and are rotated integrally with the rotary shaft to pump a gas outward in a radial direction to compress the gas. In at least one of the impellers, a maximum operating peripheral speed at a radially outermost position of the impeller is within a range of 290 m/s to 390 m/s, a yield strength is 827 MPa or less, and a Brinell hardness is 311 or less.

Abstract: Pumps and fluid-handling devices for modifying at least one property of a fluid and related method comprise a compensation assembly including at least one biasing element to enable a hydraulic insert to move within a housing.

Abstract: A component for a turbine engine may be formed by spraying particulate with a nozzle toward a substrate. The particulate may be deposited to form one or more annular layers and a reinforcing structure. The component may be a closed loop annular component having a reinforcing structure of specific dimensions enabled by the methods described.

Abstract: A peristaltic pump may include a rotor rotatably mounted between a base of the peristaltic pump head and an end cap of the peristaltic pump head. The peristaltic pump may include an arcuate case between the base and the end cap partially surrounding the rotor. The peristaltic pump may include an arcuate occlusion bed removably mounted between the base and the end cap. The arcuate case and the arcuate occlusion bed form a cylindrical body around the rotor. The peristaltic pump may include a locking handle hingedly mounted to the arcuate occlusion bed, wherein the locking handle includes a bar extending between a pair of cam members, each cam member including a cam slot that engages a respective pin extending from the base and the end cap.

Abstract: A powerplant system is provided that includes a gas turbine engine system and an actuation system. The gas turbine engine system includes a rotating structure, a stationary structure and one or more bearings rotatably mounting the rotating structure to the stationary structure. The actuation system is configured to passively rotate the rotating structure about a rotational axis during transportation of the gas turbine engine system.

Abstract: The invention relates to systems for transferring molten metal from one structure to another. Aspects of the invention include a transfer chamber constructed inside of or next to a vessel used to retain molten metal. The transfer chamber is in fluid communication with the vessel so molten metal from the vessel can enter the transfer chamber. A powered device, which may be inside of the transfer chamber, moves molten metal upward and out of the transfer chamber and preferably into a structure outside of the vessel, such as another vessel or a launder.

Abstract: An induced draft fan includes a motor, a volute, a wind wheel, and a conversion interface. The volute includes a cavity for accommodating the wind wheel. The volute further includes a bottom surface and a side surface. The bottom surface includes an air inlet and the side surface includes an air outlet. The air inlet and the air outlet communicate with the cavity. The conversion interface includes a connection section, a transition section, and an exit section. The connection section and the exit section are disposed on two ends of the transition section, respectively. The transition section tilts upward so that the exit section and the connection section are staggered with each other. The connection section includes a rectangular hollow frame including an upper side plate, a lower side plate, a left side plate, and a right side plate.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nozzle extending axially along and circumferentially about an axial centerline. The nozzle includes a nozzle panel and a nozzle fairing fixedly connected to the nozzle panel at an axial end of the nozzle. The nozzle is configured with an internal flow passage radially between the nozzle panel and the nozzle fairing. The internal flow passage extends axially within the nozzle to an outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle.

Abstract: An electroformed heat exchanger suitable for use between rotating blades and seals in a stationary casing of a turbine engine. The heat exchanger comprising a non-electroformed carrier plate having a radial outer surface and a radial outer surface, an electroformed duct provided along the radial outer surface, an electroformed rail provided on the radial inner surface, and an electroformed stiffener formed by a portion of the electroformed duct and the electroformed rail.

Abstract: A fan frame assembly includes a first fan frame and a second fan frame. The first fan frame includes a first annular wall part and a plurality of first engagement parts connected to the first annular wall part. The second fan frame includes a second annular wall part and a plurality of second engagement parts connected to the second annular wall part. Each of the first engagement parts has a positioning structure extending along an axial direction of the first annular wall part, and each of the second engagement parts has a positioning structure extending along the axial direction of the first annular wall part. when the first engagement parts and the second engagement parts are respectively engaged with each other, the positioning structures of the second engagement parts are positioned by the positioning structures of the first engagement parts.

Abstract: A positioning method of an arc-like member according to at least one embodiment of the present invention includes a step of moving a protruding part disposed at a circumferential end of the arc-like member in a radial direction with respect to a reference member positioned on a radially outer side as viewed from the circumferential end of the arc-like member. In the step of moving the protruding part, a wall portion is arranged on a radially outer side or a radially inner side with respect to the reference member, a jack is arranged between the wall portion and the reference member, and the jack is operated to move the protruding part with respect to the reference member by the pressing piece mounted on the wall portion via a rod.

Abstract: A turbine housing for a two-wheel air cycle machine includes a first side of the turbine housing, a second side of the turbine housing, a central axis, an outer housing portion, an inner housing portion, a plurality of struts between the inner housing portion and the outer housing portion and a plurality of cooling slots between the plurality of supports. The outer housing portion includes an inner surface, an outer surface, a cooling inlet extending from the outer surface of the outer housing portion and a cooling outlet opposite the cooling inlet and extending from the outer surface of the outer housing portion. The inner housing portion includes a thrust bearing support surface substantially parallel to the second side of the turbine housing and a journal bearing bore extending between the first side of the turbine housing and the thrust bearing support surface.

Abstract: A power generating unit including a hydraulic unit; an interface unit connected to the hydraulic unit, the interface unit being connectable to a stationary unit; a power flow shaft connected between the hydraulic unit and the interface unit for supply of a torque load therebetween; and at least one connecting element arranged between the hydraulic unit and the interface unit, the at least one connecting element being controllable between a first state in which a relative rotation between the hydraulic unit and the interface unit is allowed, and a second state in which a relative rotation between the hydraulic unit and the interface unit is prevented.

Abstract: A steam turbine includes a rotor, a casing, a partition plate, and a center guide pin. The center guide pin has a positioning portion. In a state of being attached to a pin attachment portion formed in one of the casing and the partition plate, the positioning portion is disposed in a groove portion formed in the other of the casing and the partition plate. The positioning portion includes a plurality of abutment portions capable of abutting on an inner side surface of the groove portion, around a pin axis. The plurality of abutment portions is formed to have different horizontal distances from the pin axis.

Abstract: A compressor housing (12) for a turbocharger includes a recirculation cavity (4) formed in a portion of the compressor housing (12). The recirculation cavity (4) is defined by an inner cavity wall (2) and an outer cavity wall (5). In addition, an inlet groove (1) and an outlet (7) are formed in the recirculation cavity (4) for circulating airflow from the compressor housing (12) through the recirculation cavity (4), and at least one recirculation noise obstruction (6) is fixedly secured within the recirculation cavity (4) to disrupt air flow through the cavity and reduce noise in the compressor housing (12).

Abstract: In a water pump, a water reservoir portion into which cooling water leaking from between a bearing portion and a rotating shaft flows via an introduction hole is divided into a first division portion and a second division portion by a gasket. The first division portion and the second division portion communicate with each other through a communication hole formed in the gasket. The second division portion includes a drain hole through which cooling water is discharged to outside.

Abstract: The invention relates to acoustic management, on an aircraft turbomachine (3,12) or on a nacelle (1,10), via a panel (30,32). On a support (38) is reserved a recess (34), recessed with respect to a surrounding general surface (36) for contact with moving air. The recess (34) is adapted to receive the panel, as another so-called surface for contact with moving air. The support (38) and/or the panel comprise removable connecting elements for, in the recess (34), mounting it removably with respect to the support, the panel being an acoustic panel or a non-acoustic panel.

Abstract: A vibration damper capable of damping vibrations occurring from a turbine casing, an exhaust diffuser system including the vibration damper, and a gas turbine including the exhaust diffuser system are provided. The vibration damper installed on an outer casing of a gas turbine to damp vibrations generated in the gas turbine, the vibration damper includes a reinforcing support part including a plurality of reinforcing plates, a first flange coupled to both longitudinal ends of the reinforcing support part and fixed to a protruding support protruding from the outer casing, and a second flange disposed between the plurality of reinforcing plates to connect the plurality of reinforcing plates, wherein each of the plurality of reinforcing plates is erected and installed on an outer circumferential surface of the outer casing.

Abstract: Method to assemble a water pump with an impeller driven by an electrical machine comprising a housing cap and a volute with an inlet and an outlet and a boot hosting a stator and a rotor of the electrical machine and an electronic board mounted at the side apart from the impeller and covered by the cap housing, the boot having a radial extending rim comprising at least slots defined by the following steps: connecting the volute to the boot by inserting axial hooks in the boot's slots, twisting the volute versus the boot to fix the axial hooks, inserting radial hooks of the cap housing in the same slots.

Abstract: A diaphragm latch may comprise a housing, a diaphragm disposed in the housing, a pin coupled to the diaphragm, an opening in the housing, and a pin aperture disposed in the first side, wherein the pin extends from the pin aperture. The diaphragm may be configured to move in response to a pressure being communicated through the opening, and the pin may be configured to at least one of extend or retract from the pin aperture in response to the diaphragm moving. The diaphragm latch may passively couple an inner fixed structure (IFS) to an intermediate case (IMC) during an overpressure event.

Abstract: A fan carrier is to be placed in physical communication with a fan-side connector of an information handling system. The fan carrier includes a plunger assembly and multiple isolators. The plunger assembly is biased toward an at-rest position. The plunger assembly is in physical communication with the fan-side connector when the plunger assembly is in a deformed position. The isolators are mounted on the fan carrier, and dampen vibration energy in the fan carrier and prevent the vibration energy from being transferred to the fan-side connector. The isolators enable the fan-side connector to float within the fan carrier.

Abstract: An air inlet section for an enclosure for an aircraft engine is provided that includes an inner barrel panel, an outer barrel panel, a lipskin and a forward bulkhead. The lipskin extends between an inner barrel end and an outer barrel end. The inner barrel end is disposed proximate the forward end of the inner barrel panel and the outer barrel end is disposed proximate the forward end of the outer barrel panel. The forward bulkhead has a panel that extends between an outer radial end and an inner radial end. The inner barrel panel, the outer barrel panel, and the lipskin define an interior annular region, and the forward bulkhead defines a sub-portion of interior annular region. The outer radial end of the forward bulkhead panel is disposed forward of the inner radial end of the forward bulkhead panel.

Abstract: A turbomachine housing, in particular of a radial turbomachine which transfers technical work to a process fluid or from a process fluid, includes: an opening extending along an axis, for the axial feed-through of a shaft extending along said axis; a contact surface extending along a circumferential direction with respect to the axis, for contact with a housing jacket of the turbomachine housing. A flow line provided as an inflow or outflow of the process fluid is designed as an integral part of the cover.

Abstract: In one instance, a cooling unit for cooling a refrigerated room includes a fan base and a fan guard that both twist and rotate to change pitch thereby allowing the cooling unit air to be directed in many directions as desired. The fan base has a flange portion and a conduit portion. The conduit portion of the fan base mates with an opening in a conduit member of the fan guard. The opening in the fan guard is sized and configured to form an interference fit with at least a portion of a conduit portion of the fan base while allowing rotation of the fan guard relative to the fan base about the longitudinal axis. The second longitudinal end of the fan-guard conduit member is at least partially angled to allow the rotation about a lateral axis in order to pitch the direction of the grill front wall.

Abstract: The subject matter of this specification can be embodied in, among other things, a thrust reverser tertiary lock apparatus that includes a probe affixed to an aircraft engine frame and having a shaft having a barb at a first end and configurable to a first configuration and a second configuration, and a receiver affixed to a thrust reverser transcowl slider configured to accommodate the barb and having an end wall with an aperture defined therein, the aperture shaped to permit escapement of the barb in the first configuration and prevent escapement of the barb in the second configuration.

Abstract: In an inner pipe assembly step, sheet-metal-made inner-pipe divided bodies and a cast inner-pipe divided body are connected to assemble an inner pipe. In a center flange connecting step, the sheet-metal-made inner-pipe divided bodies are connected to a center flange. In an outer pipe connecting step, an outer pipe covering the inner pipe is connected to the center flange and an exhaust-air-inlet-side flange. In a masking step, at least one of: a connected portion between the sheet-metal-made inner-pipe divided bodies and the cast inner-pipe divided body; or an opening portion between the outer pipe and the inner pipe is sealed. In a cutting machining step, an inner wall surface of the cast inner-pipe divided body facing the turbine wheel is subjected to a cutting machining after the masking step.

Abstract: Sound is reduced after securing sufficient air volume. An intake side fan including a first housing, a first drive motor that functions as a drive source, a first hub that is rotated by drive force of the first drive motor, and a plurality of first impellers that is rotated along with the first hub; and an exhaust side fan including a second housing, a second drive motor that functions as a drive source, a second hub that is rotated by drive force of the second drive motor, and a plurality of second impellers that is rotated along with the second hub are provided. An axial maximum chord length of the first impellers is smaller than an axial maximum chord length of the second impellers.

Abstract: In a rotary machine and a seal member, a casing, a rotor, a stator blade, a rotor blade, and a seal device disposed between the casing and a tip portion of the rotor blade are provided, in which a blade attachment groove is provided in the inner peripheral portion of the casing, and a caulking groove is provided adjacent to the blade attachment groove, in which a base end portion of the stator blade is mounted in the blade attachment groove and a caulking member is locked to the caulking groove and a blade root portion of the stator blade, so that the stator blade is fixed to the inner peripheral portion of the casing, and in which a seal ring as a seal device is mounted in the inner peripheral portion of the casing, and the seal ring covers at least a part of the caulking groove.

Abstract: An anterior part of a nacelle of an aircraft propulsion unit. A rigidifying frame annular about a longitudinal axis of extension of the nacelle is at the rear end of the anterior part. An annular shield is in front of the rigidifying frame and connects an internal peripheral edge of the rigidifying frame to an internal structure. The shield has a portion extending towards the external panel beyond the internal peripheral edge of the rigidifying frame, the portion forming a non-zero angle with respect to the rigidifying frame to form a free space with respect to the rigidifying frame behind the portion. The shield can thus deform in the event of an impact of a foreign object entering through the air inlet lip, without the rigidifying frame itself being deformed, thereby absorbing all or some of the impact energy. A nacelle can have such an anterior part, and an aircraft can have such a nacelle.

Abstract: A connection device for an exhaust gas turbocharger has a bent first element with a first tensioning arm at a first end. A second bent element has a second tensioning arm at a second end opposite the first end. A third end of the first element is formed opposite a fourth end of the second element. The first tensioning arm and the second tensioning arm are connectable by a first connecting element. The third end and the fourth end are movably connected with each other by a second connecting element. A transition is elastically formed between the respective tensioning arm and a supporting portion of the particular element, which extends between the tensioning arm and the third or fourth, respectively, end. The first element or the second element is formed in a profiled manner.

Abstract: A centrifugal compressor includes: an impeller (compressor impeller); a main flow passage, which has the impeller arranged therein, and extends in a rotation axis direction of the impeller; an auxiliary flow passage formed on a radially outer side of the impeller with respect to the main flow passage; an upstream communication passage configured to allow the auxiliary flow passage and the main flow passage to communicate to each other; a downstream communication passage configured to allow the auxiliary flow passage and the main flow passage to communicate to each other on a side closer to the impeller with respect to the upstream communication passage; and a partition portion (rib or fin) configured to partition the auxiliary passage in a circumferential direction while maintaining a gap larger than a flow passage width of the downstream communication passage in the auxiliary flow passage.

Abstract: A centrifugal compressor includes an impeller including a hub and a plurality of blades disposed on an outer peripheral surface of the hub at intervals in a circumferential direction, and a casing accommodating the impeller and defining an inlet passage for introducing air along an axial direction of the impeller. An inner peripheral surface of the inlet passage includes a narrowed portion, and an inclined portion connected to a downstream side of the narrowed portion and having a radial distance from a rotational axis of the impeller gradually increasing toward the vicinity of tips of leading edges of the blades. Further, 0.01R1???0.1R1 is satisfied, where R1 is radial distance between a downstream end of the inclined portion and the rotational axis, R2 is radial distance between a downstream end of the narrowed portion and the rotational axis, and ? is constriction amount which is a difference between R1 and R2.

Abstract: Pin latch assemblies and cam latch assemblies are disclosed. A pin latch assembly is provided comprising a pin housing at least partially enclosing a pin, an actuating device coupled to the pin, and a retaining feature comprising an aperture.

Abstract: An oil seal structure and a compressing apparatus including the oil seal structure are provided. The oil seal structure includes a rotating shaft, a bearing, a lower housing portion, an upper housing portion, an assembly surface seal member inserted into a first assembly surface seal groove, and an oil seal member provided in a first seal groove and a second seal groove and including a flange portion, wherein a lower oil receiving portion is formed in the lower housing portion, a first passage groove is formed in the first seal groove, and an oil passage is formed between a bottom surface of the first passage groove and the flange portion.

Abstract: A number of variations may include a turbine housing comprising a turbine body; an inlet passage and an outlet passage connected to the turbine body; a wastegate passage operatively connected to the outlet passage; a diffuser positioned within the outlet passage comprising at least one radial opening; wherein the first flow passage accepts fluid flow from the wastegate passage and the second flow passage accepts fluid flow from the turbine wheel; wherein a first end of the diffuser is attached to a first end of the turbine outlet and a second end of the diffuser is attached to a second end of the turbine outlet so that fluid flow from the first flow passage is directed into the second flow passage through the at least one radial opening before exiting the outlet passage, and wherein the at least one radial opening minimizes turbulence of fluid flow exiting the turbine housing.

Abstract: A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.

Abstract: Blower case provided in centrifugal blower of the present invention has side wall, suction port, a discharge port, and flow channel. In flow channel, when impeller is rotated by rotation action transmitted from motor, air sucked from suction port and passed through an inner peripheral side end and outer peripheral side end is guided to the discharge port along side wall. A shape of a cross section of flow channel including rotational axis is wider, toward an opposite side where the suction port is located relative to a side where suction port is located in a direction along axial center direction, in a second cross section located near the discharge port than in a first cross section located far from the discharge port in a direction in which impeller rotates.

Abstract: An internally-cooled compressor is provided including a casing and a diaphragm disposed in the casing. The diaphragm includes a diaphragm box defining a plurality of box channels and a bulb defining a plurality of bulb channels. A plurality of return channel vanes connect the diaphragm box and bulb in fluid communication, such that each return channel vane defines a plurality of return vane conduits coupled in fluid communication with the plurality of box channels and the plurality of bulb channels thereby forming a section of a cooling pathway. The cooling pathway is configured such that a cooling agent introduced from an external coolant source into the diaphragm box and flowing through a box channel flows through a return vane conduit into and through a bulb channel and back through another return vane conduit into another box channel before flowing back to the external coolant source.

Abstract: A compressor housing for a turbocharger includes an outer housing structure, an inner housing structure, and a rear housing structure. The outer housing structure includes a first tubular portion and a first radial portion extending radially outward of the first tubular portion. The inner housing structure includes a second tubular portion and a second radial portion extending radially outward of the second tubular portion. The rear housing structure includes an inner radial portion and an outer radial portion extending radially outward of the inner radial portion. The outer housing structure, the inner housing structure, and the rear housing structure are formed separately from each other and are coupled to each other. A recirculation cavity is defined radially between the first tubular portion and the second tubular portion. A volute is cooperatively formed by the first radial portion and the outer radial portion.

Abstract: Oscillating angularly rotating a container containing a material may cause the material to be separate. Denser or heavier material may unexpectedly tend to collected relatively close to the axis of rotation, while less dense or light material may tend to collect relatively away from the axis of rotation. Oscillation along an arcuate path provides high lysing efficiency. Alternatively, a micromotor may drive an impeller removably received in a container. Lysing may be implemented in batch mode, flow-through stop or semi-batch mode, or flow-through continuous mode. Lysing particulate material may exceed material to be lysed or lysed material and/or air may be essentially eliminated from a chamber to increase lysing efficiency.

Abstract: An air flow-enhancing insert (30) is configured to be inserted into the air inlet (16) of a compressor (3). The insert includes a hollow, cylindrical inner member (32) and lugs (44) protruding outward from an outer surface (36) of the inner member, each lug having an elongated cross sectional shape and including a leading edge (46), a trailing edge (48), and a long axis (50) that extends between the leading edge and trailing edge, the long axis defining a helix about the outer surface. When the insert (30) is disposed in the compressor air inlet, an air recirculation path (20) is defined between the inner member outer surface, an inner surface (17) of the air inlet, and the lugs. The air recirculation path improves air flow in the compressor, whereby compressor efficiency is improved and noise is reduced.