Abstract: A compressor for an aircraft engine, has: a dual-impeller having: a first impeller having a first inlet and a first outlet located radially outwardly of the first inlet, and a second impeller rotatable with the first impeller, the second impeller having a second inlet and a second outlet located radially outwardly of the second inlet, the first inlet and the second inlet facing opposite axial directions; and first conduits having first conduit inlets and first conduit outlets, the first conduit inlets fluidly connected to the first outlet of the first impeller, the first conduit outlets fluidly connected to the second inlet of the second impeller; and second conduits having second conduits inlets fluidly connected to the second outlet of the second impeller, a second conduit of the second conduits disposed circumferentially between two adjacent first conduits of the first conduits.

Abstract: A centrifugal compressor includes: an impeller which is allowed to rotate around an axis; a casing in which the impeller is accommodated and a guide flow path guiding fluid to the impeller is formed; and a guide vane which is disposed in the guide flow path and is extended from a hub side wall surface of the guide flow path, which is continued to a hub side of the impeller, to a shroud side wall surface of the guide flow path to a shroud side of the impeller, wherein the guide vane is twisted forward the impeller in a rotating direction thereof as close to the shroud side wall surface from the hub side wall surface.

Abstract: The present disclosure relates to a compressor including: a motor having a rotating shaft; a first impeller housing forming a first inlet, through which a first refrigerant flows, and having a chamber into which a second refrigerant flows; a first impeller coupled to one end of the rotating shaft, and rotatably received in the first impeller housing; a diffuser spaced apart from an inside of the first impeller housing, and forming a first outlet; a second impeller housing having a second inlet formed therein; a second impeller coupled to the other end of the rotating shaft, and rotatably received in the second impeller housing; a volute case in which a volute is formed; and a motor housing having a connecting passage formed therein and connecting the first outlet and the second inlet.

Abstract: A vacuum pump includes a rotor provided with a plurality of rotor blades and a rotor cylinder portion, a driving portion, a bearing, stator blades, a thread groove stator that is disposed downstream of the stator blades and has an inner peripheral surface facing an outer peripheral surface of the rotor cylinder portion, and a heat insulating wall disposed downstream of the thread groove. The heat insulating wall includes a ring-shaped annular portion, and a substantially cylindrical wall portion extending from an inner portion of the annular portion in the radial direction to the upstream side and forming a flow path on the outer peripheral surface side. A first corner portion is formed between an upstream-side surface of the annular portion and the outer peripheral surface of the wall portion, the first corner portion being formed in an arc shape.

Abstract: A turbine wheel (100) for a turbocharger includes a hub (110) and blades (120). The hub includes a primary outer surface (116), a back wall surface (115), a peripheral edge (119) extending between the primary outer surface and the back wall surface, and a central axis (111). The hub has a back wall thickness measured parallel to the central axis from the primary outer surface to the back wall surface. The blades (120) extend from the primary outer surface of the hub and are integrally formed with the hub by casting. Each blade has a blade thickness measured tangential to the central axis between opposed surfaces of the blade. A maximum diameter of the peripheral edge is 60 mm or more. Over a majority of a radially outer region (117), a thickness ratio of the blade thickness to the back wall thickness varies by 25% or less. The radially outer region extends from the peripheral edge to a 25% meridional.

Abstract: A method of winding a pre-impregnated fabric strip onto a sloping surface includes a step of deforming the pre-impregnated fabric strip by applying differing traction forces to the pre-impregnated fabric strip, the traction forces being directed in a longitudinal direction of the strip, the values of the applied traction forces differing across the transverse direction of the strip. The differing traction forces are applied by tensioning the pre-impregnated fabric strip between firstly a pair of brake rollers and secondly a traction device present downstream from the pair of brake rollers, the traction device driving the pre-impregnated fabric strip at speeds that differ across the transverse direction of the strip. The method further includes winding the deformed strip onto a surface of revolution of winding tooling including at least one portion that forms a nonzero angle with the axis of revolution of the surface of revolution.

Abstract: A single-stage compressor device includes a housing and a rotating group with a shaft and a compressor wheel. The compressor wheel includes a front face and a back face. The front face cooperates with the housing to define a compressor flow path. A motor drives rotation of the rotating group within the housing. Furthermore, the compressor device includes a bleed system fluidly connected to the compressor flow path and configured to receive bleed fluid from the compressor flow path. The bleed system includes a bleed passage. At least a portion of the bleed passage is cooperatively defined by the back face of the compressor wheel and an opposing surface of the housing. The bleed system is configured to pass bleed air from the bleed passage, thereby alleviating thrust loading of the compressor wheel on the rotating group.

Abstract: A device for a variable and adaptable diverterless bump engine inlet of an aircraft comprises a flexible inlet, a mechanism to change the shape of the flexible inlet, and a processing unit to control the mechanism. The flexible inlet of the device includes a plurality of edges attached partly to a fuselage skin and partly to an engine inlet duct. With this device, the shape of the flexible inlet can be controlled according to the flight conditions, and hence the engine air intake will perform more efficient at all speeds while fulfilling requirements for less radar visibility.

Abstract: In some embodiments, a plenum of an apparatus for transferring energy between a rotating element and a fluid may include a through hole disposed through the plenum; a plurality of inlet guide vanes disposed proximate a peripheral edge of the through hole, the plurality of inlet guide vanes comprising a first group of inlet guide vanes having a symmetrical profile, a second group of inlet guide vanes, and a third group of inlet guide vanes, wherein each inlet guide vane of the second group and third group have a cambered profile, wherein each inlet guide vane of the second group has same cambered profile, and further wherein each inlet guide vane of the third group has a different cambered profile from each other inlet guide vane of the third group.

Abstract: A turbocharger for an internal combustion engine has a bearing housing, in which a rotor shaft is mounted in a rotatable manner. A compressor having a compressor wheel is arranged for conjoint rotation on the rotor shaft. A fresh air supply channel conducts a fresh air mass flow to the compressor wheel. The fresh air supply channel has a first flow cross section upstream of the compressor wheel. A flow control device is provided and is adjustable between an open position, in which the first flow cross section is opened up, and a closed position, in which the first flow cross section is reduced to a second flow cross section. The flow control device is fluidically coupled to a compressor channel of the compressor downstream of the compressor wheel, such that the flow control device is adjusted in a manner dependent on a pressure prevailing in the compressor channel.

Abstract: A variable nozzle unit is used in a turbine having a gas inflow passage which is sandwiched between a first flow passage wall surface and a second flow passage wall surface facing each other and through which a gas flowing from a scroll flow passage into a turbine impeller flows. The variable nozzle unit includes nozzle vanes, each of which is rotatably supported on both sides thereof by the first flow passage wall surface side and the second flow passage wall surface side and pivots about a pivotal axis parallel to the rotational axis of the turbine impeller in the gas inflow passage. An end face of the nozzle vane is formed with a cut face that is located closer to a leading edge than the pivotal axis, is cut out such that a gap between the cut face and the second flow passage wall surface is greater than other regions, and intersects the leading edge.

Abstract: A turbocharger adjustment device adapted to alter the performance of a variable geometry turbocharger delivering boost pressure to an engine, comprising a replacement piston cap and a movable adjustment rod. The turbocharger adjustment device integrates with the actuator controlling the opening and closing of the variable inlet through which exhaust gas from the engine passes to turn the turbine wheel and compressor of the turbocharger. The replacement piston cap replaces the cap of the actuator so that the adjustment rod extends into the actuator housing interior to abut against and restrict the movement of the piston which actuates the variable inlet, preventing the piston from opening the variable inlet. The turbocharger adjustment device prevents the decrease in boost pressure caused by the variable inlet opening in response to an increase in exhaust gas pressure, and allows the user to customize the maximum area of the variable inlet.

Abstract: A wastegate actuator assembly includes a regulating rod, an arm, and a shaft. The regulating rod includes a proximate end region and a distal end region wherein the proximate end region of the regulating rod may be connected to an actuator. The arm includes a first end region and a second end region. The first end region is pivotally coupled to the distal end region of the regulating rod via a crank pin, a first cup spring, and a second cup spring wherein the first and second cup springs retain a solid lubricant substantially around the crank pin. The regulating rod may move in a linear fashion causing the arm and the shaft to rotate so as to move a wastegate cover connected to the shaft from a closed wastegate duct position (toward the wastegate duct) to an open wastegate duct position (away from the wastegate duct).

Abstract: Methods and systems are provided for controlling a turbine within an internal combustion engine. In one example, a turbine system within an internal combustion engine may include at least one turbine with a housing that may further include at least one impeller mounted on a rotatable shaft, inlet and outlet regions, and at least one overpressure line including a self-controlling valve for controlling the flow of exhaust gas.

Abstract: A turbocharger compressor housing is configured to allow a releasable fixed adjustment of a geometry of a compressor housing to increase at least one of responsiveness, efficiency or the ultimate power obtainable by a turbocharged system. Adjustability can be provided by an air intake pipe that is threadably connected with a central portion of the compressor housing to allow an air gap between the housing and the intake pipe to be adjusted to create an effect similar to adjusting the inducer area of a compressor wheel disposed in the housing, whereby power can be exchanged for efficiency and responsiveness. Set screws may be used to releasably fix the position of the intake pipe relative to the compressor housing.

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. The inlet-adjustment mechanism includes an axially elongated ring. In the open position, the radially outer surface of the ring is spaced from a tapering inner surface of the air inlet so that air can flow in an annular passage between the tapering surface and the ring. In the closed position, the ring abuts the tapering surface to close off the annular passage, whereby the effective inlet diameter is then defined by the inner diameter of the ring at its trailing edge. 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.

Abstract: A variable geometry turbine comprises a turbine wheel and a primary inlet passage of variable axial width. The turbine has a secondary inlet passage provides a flow path for a working fluid which circumnavigates at least part of the primary inlet passage. A seal element and one or more apertures are cooperable to selectively allow or prevent fluid flow through the secondary inlet passage. The turbine wheel is of the radial-inflow axial-outflow type and secondary inlet passage has an outlet configured to direct working fluid to exit the secondary inlet passage in a direction which has an axial component in the opposite direction to the direction of axial outflow of the turbine wheel.

Abstract: A bleed valve having a piston with a sealing member, the piston being displaceable between a first position to seal an aperture of a fluid conduit and an opposed second position spaced apart from the aperture to allow the working fluid therethrough. The bleed valve also has a guiding assembly with at least one guide wheel mounted to the piston and being displaceable therewith along a guide rail. The guide wheel has a guide groove extending inwardly from an outer rolling surface. The guide rail has a rail surface with a guide protrusion. The guide groove and the guide protrusion are complementary and in rolling contact with one another. The bleed valve also has a displacement mechanism for displacing the piston between the first and second positions. A compressor with a bleed valve and method for controlling bleeding of a working fluid are also discussed.

Abstract: A variable geometry turbine comprise a housing; a turbine wheel supported in the housing for rotation about a turbine axis; and an annular inlet passage upstream of said turbine wheel defined between respective inlet surfaces defined by an annular nozzle ring and a facing annular shroud. The nozzle ring and shroud are axially movable relative to one another to vary the size of the inlet passage; the nozzle ring having a circumferential array of inlet vanes extending across the inlet passage. The shroud covers the opening of a shroud cavity and defines a circumferential array of vane slots, each vane slot corresponding to an inlet vane, the vane slots and shroud cavity being configured to receive said inlet vanes to accommodate axial movement of the nozzle ring.

Abstract: According to one embodiment, a coating apparatus includes a stage having a mounting surface on which a coating target is mounted, a rotating mechanism that rotates the stage, a coating nozzle that discharges a coating material, a moving mechanism that moves the coating nozzle, a supply device that supplies a material to the coating nozzle, an ejection device that ejects the material, a communication tube that allows the supply device, and a valve device. Further, the coating apparatus includes a control unit which rotates the stage by the rotating mechanism, switches the valve device to achieve the continuity of the supply unit and the coating nozzle, drives the moving mechanism to move the coating nozzle, and applies the coating material to the coating target on the stage.

Abstract: An inlet guide van device having a central axis comprises a first base, a guide sleeve, a blade, a second base, a transmission disk, and an actuator. The first base has at least one first support groove and at least one guide groove. The first support groove extends along a radial direction of the central axis, and the at least one guide groove is located in the first support groove. The guide sleeve is disposed on the first support groove in a manner that the guide sleeve is capable of moving along the radial direction. The guide sleeve has a sliding sleeve, an upper guide post and a lower guide post, the sliding sleeve has a through hole extending along the radial direction. The upper guide post and the lower guide post pass through the sliding groove, and the lower guide post is movably disposed on the guide groove.

Abstract: An external actuator for a variable water pump is provided having an actuator housing with an outer wall with a plurality of radially inwardly directed projections, and a drive ring rotatably mounted in the housing. The drive ring has an internal thread. The projections contact an outer surface of the drive ring to define a plurality of hydraulic chambers that are divided by vanes extending from the drive ring into first and second chamber portions. A control valve controls a flow of pressurized hydraulic fluid to the chambers to rotate the drive ring in both directions or hold it in position. A drive nut having external threads is located within the drive ring and rotation of the drive ring causes an axial displacement of the drive nut. An actuator pin connected to the drive nut extends into the water pump housing to actuate the variable flow impeller.

Abstract: A compressor of a turbocharger including a compressor housing and a compressor impeller. The compressor housing includes: a compressor flow passage, a compressor air inlet, and a compressor air outlet. The compressor impeller includes an impeller feeding flow passage. The compressor impeller is disposed inside the compressor housing. The compressor flow passage is disposed inside the compressor housing. The compressor flow passage is connected to the compressor air inlet and the compressor air outlet. The impeller air feeding flow passage is connected to the compressor air inlet and the compressor flow passage.

Abstract: In one aspect an apparatus for performing a downhole operation is disclosed that in one non-limiting embodiment may include a downhole tool that contains a hydraulically-operated motor and a flow control device that in one position allows a fluid to pass through the motor while preventing the fluid to flow to the motor and in another position allows the fluid to flow to the motor to operate the motor.

Abstract: Systems and methods are disclosed for a turbocharger compressor, the system comprising: an actuatable annular disk comprising choke slots therein; an outer annular disk comprising choke slots therein; and an actuator to rotate the actuatable annular disk relative to the outer annular disk to vary alignment of the choke slots of the actuatable annular disk and the outer annular disk. The actuator may be controlled by an engine controller responsive to operating conditions of the compressor and actuated to align choke slots. Alignment of the choke slots allows air to be drawn into the impeller effectively expanding the compressor flow capacity to prevent compressor choke.

Abstract: A radial turbine includes a radial turbine wheel provided with a main pathway in which blade height progressively increases while curving toward an axial direction from a radial direction. A sub-let is formed on a shroud side of the radial turbine wheel at a position separated from the main inlet in the radial direction and the axial direction. Also, a blade shape that forms the sub-inlet is such that, in a plane orthogonal to the axial line of the radial turbine wheel, a center line of the blade is inclined at a predetermined angle toward the rotation direction with respect to the radial direction.

Abstract: A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis. The housing defines an annular inlet passage around an inducer portion of the turbine wheel and an outlet passage including a tubular wall disposed around an exducer portion of the turbine wheel; the inlet passage is defined between first and second radial inlet surfaces, one of the inlet surfaces being defined by a moveable wall member and the other of the inlet surfaces being defined by a facing wall of said housing. The moveable wall member is moveable relative to the facing wall of the housing along the turbine axis to vary the size of the inlet passageway. The moveable wall member is displaceably mounted within an annular cavity defined between the tubular wall and a surrounding wall of the housing.

Abstract: A variable geometry turbine comprising: a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet; the annular inlet divided into axially adjacent annular portions by at least one annular baffle which is axially spaced from the first and second inlet sidewalls; inlet formations extending axially across at least two of said annular portions defined by the or each baffle so as to divide said annular inlet into at least two axially offset inlet passages; the baffle(s) and inlet formations forming part of a nozzle assembly located within said annular inlet; wherein first and second components of the nozzle assembly define complementary features which co-operate to connect together said first and second components.

Abstract: A connecting device, comprising: a linearly driving drive member; an actuating member driven in a rotating manner by an internal combustion engine charging device with at least one pivot arm connected to the actuating member in a fixed manner, wherein the actuating member transmits rotational moments about a pivot axis, with a slide element connected to the driving member in a fixed manner, and wherein the driving member transmits linear forces oriented obliquely to the pivot axis, with at least one bearing arrangement, which moveably couples the slide element to the pivot arm such that the slide element is displaceably mounted along a displacement axis running parallel to the pivot axis and rotatably mounted about the displacement axis and about a rotary axis running perpendicularly to the displacement axis.

Abstract: A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis. An exhaust gas inlet passageway is defined between a shroud and a wall of a nozzle ring. The shroud is moveable in the axial direction to vary the size of the inlet passageway. The nozzle ring has an array of vanes that extends across the inlet passageway. An array of openings is provided in the shroud for receipt of the array of vanes. The shroud is part of a substantially annular axially moveable sleeve that is slidably disposed on an annular supporting wall. At least one biasing member is disposed between the moveable sleeve and the support and is designed to apply a circumferentially distributed force in the radial direction so as to maintain concentric alignment of the supporting wall and the sleeve.

Abstract: A piston ring for sealing gas flow past a sliding cylinder is provided at the interface of the turbine and bearing housings, and is axially close to the turbine inlet. A V-band or similar connection joins the turbine and bearing housings but it is axially further away from the turbine inlet. The piston ring is provided with a spacer element between it and the bearing housing that is at least partially thermally decoupled from the bearing housing.

Abstract: An assembly includes a synchronizing ring, a vane arm, and a multi-axis joint. The multi-axis joint connects the synchronizing ring to the vane arm and provides the vane arm with movement about a first pivot axis and a second pivot axis.

Abstract: Variable geometry turbomachine with a bearing housing, an adjacent turbine housing, a turbine wheel rotating in the turbine housing about a turbine axis; an inlet passage upstream of the turbine wheel between inlet surfaces of first and second wall members, one wall member moveable along the turbine axis to vary the inlet passage size; vanes across the inlet passage connected to a first wall member; an array of vane slots defined by the second wall member to receive the vanes for relative movement between the wall members; the second wall member comprising a shroud defining vane slots; the second wall member supported by a support member retained by a mounting feature; the mounting feature being one of the bearing housings, the turbine housing, or the actuation element; and the shroud is fixed to the support member so axial movement of the shroud relative to the support member is substantially prevented.

Abstract: The invention relates to a turbine (1) for a turbocharger, comprising a turbine wheel (2) and a turbine housing (5) forming a passage (6) for guiding a fluid flow to the turbine wheel (2), said passage (6) comprising a variable throat providing a throat area (8) as a smallest cross section of the fluid flow, wherein the variable throat is always defined by a annular member (7) surrounding the turbine wheel (2) and being movable in the axial direction of the turbine wheel (2).

Abstract: A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The turbine further comprises a cylindrical sleeve that is axially movable across the annular inlet to vary the size of a gas flow path through the inlet. The annular inlet is divided into at least two axially offset inlet passages. The inner diameter of the sleeve is greater than the inner diameter of the inlet passages.

Abstract: A reduce electric power consumption when an electric motor starts an engine and the time required to start the engine. Engine start control is implemented as follows. The RPM of the engine is increased to an RPM (R1) by the electric motor. Fuel is supplied to the engine of which RPM has reached to the RPM (R1) and further increases in the RPM are detected. If a further increase in the RPM is not detected, the supply of electric power to the electric motor is temporarily stopped. If the RPM has decreased to a RPM (R2), the supply of fuel to the engine is interrupted and also the supply of electric power to the electric motor is resumed. If a further increase in the RPM is detected or if the RPM has not decreased to the RPM (R2), it is determined that the engine has been started.

Abstract: A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member having a track channel. The slider assembly translatably engages the track assembly. The slider assembly includes a slider body configured to be received within the track channel. The slider assembly further includes a slider arm member pivotably coupled to the slider body with a hinge joint disposed within the track channel. The slider arm member extends from the body portion and outwardly of the track assembly. Associated apparatuses are also provided.

Abstract: A turbomachine that includes a radial-flow impeller and one or more of a variety of features that enhance the performance of machinery in which the turbomachine is used. For example, when the turbomachine is used in a dynamometer, the features enhance the useful shaft horsepower range of the dynamometer. One of the features is a variable-restriction intake that allows for adjusting flow rate to the impeller. Other features include a unique impeller shroud and a shroud guide each movable relative to the impeller. Yet another feature is an exhaust diffuser that facilitates an increase in the range of shaft power and the reduction of deleterious vibration and noise. The turbomachine can also include a unique impeller blade configuration that cooperates with the adjustable intake and the exhaust diffuser to enhance flow through the turbomachine.

Abstract: A turbocharger is provided herein. The turbocharger includes a housing and an adjustable core at least partially circumferentially surrounded by the housing, the adjustable core having a turbine rotor coupled to a compressor rotor via a shaft. The turbocharger further includes an adjustment mechanism coupled to the adjustable core configured to adjust an axial position of the housing relative to the adjustable core in response to adjustment commands.

Abstract: An expansion turbine with a radial turbine wheel has a main path that gradually increases in height and axially discharges fluid while swirling from a main inlet located at the outer circumferential side into the main path, with a radial flow as a main component, the radial turbine wheel has a sub-path branching off from the side of a hub of the main path at a position radially inward of the main inlet and extending rearward from the main path, the sub-path has, at an outer circumferential end, a sub-inlet located at a position in the radial direction different from the main inlet and supplied with a fluid having a pressure different from the pressure of the fluid supplied through the main inlet, the main inlet and the sub-inlet are partitioned by a back plate portion, in which the gap between it and the main path or the sub-path is adjusted.

Abstract: In one aspect of the present invention, a downhole drill string assembly comprises a bore there through to receive drilling fluid. A turbine may be disposed within the bore and exposed to the drilling fluid. At least one flow guide may be disposed within the bore and exposed to the drilling fluid wherein the flow guide acts to redirect the flow of the drilling fluid across the turbine. The flow guide may be adjusted by an actuator. Adjustments to the flow guide may be controlled by a downhole telemetry system, a processing unit, a control loop, or any combination thereof. In various embodiments the turbine may comprise rotatable turbine blades.

Abstract: According to an aspect of the present invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted on a turbine shaft within a housing assembly for rotation about a turbine axis, the housing assembly defining a gas flow inlet passage upstream of the turbine wheel; an annular wall member defining a wall of the inlet passage and which is displaceable in a direction substantially parallel to the turbine axis to control gas flow through the inlet passage; at least one moveable rod operably connected via a first end of the rod to the annular wall member, the rod being moveable to control displacement of the annular wall member, the rod extending in a direction substantially parallel to the turbine axis, the rod being connected to the annular wall member via a first arm and a second arm, a first end of the first arm and a first end of the second arm being attached to the rod, and a second end of the first arm being attached to the annular wall member at a first circumferential positi

Abstract: According to an aspect of the invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the annular inlet, the annular inlet being divided into at least two axially offset inlet portions; and a ring-like seal adjacent a free end of the sleeve, at least a part of the ring-like seal being located in-between the sleeve and the inlet portions, or a structure defining the inlet portions.

Abstract: A position adjustment device of a turbo compressor that supports an annular member of which at least a portion is capable of being disposed in a diffuser flow path and that can be disposed in and adjusts the height of the annular member. The position adjustment device has a plurality of lever mechanisms that each have a rod connected to the annular member and are disposed separated from each other in the circumferential direction; and a transmission mechanism that transmits a drive force that at least one of the plurality of lever mechanisms has received to the other lever mechanisms. The transmission mechanism has a substantially circumferential linkage in which an open section is partially provided.

Abstract: In an exhaust gas turbocharger turbine for an internal combustion engine having a housing including a turbine wheel rotatably supported in the housing, wherein the housing has an exhaust gas flow guide section including an exhaust gas flow control arrangement with a guide vane structure for directing exhaust gas onto the turbine rotor, an adjustment mechanism with an axially movable control slide is provided which is movable by an operating fork which is slidably supported on a guide element and engages the control slide at opposite sides so as to prevent cogging of the movable control slide during movement into, and out of, the exhaust gas flow guide section.

Abstract: A variable geometry turbine comprises a turbine wheel (5) supported in a housing (1) for rotation about a turbine axis. An annular inlet passage (9) is defined between first and second radial inlet surfaces, one of said first and second inlet surfaces being defined by a moveable wall member (40). A substantially annular array of vanes (41) is provided which extend across the inlet passageway (9); each vane (41) being fixed to said first inlet surface. Each vane (41) has first and second major vane surfaces (45, 46) having a chordal length extending between a radially outer leading vane edge (47) and a radially inner trailing vane edge (48), the first major vane surface (45) facing generally away from the axis and the second major vane surface (46) facing generally towards the axis. A rib (43) extends across at least a substantial portion of the chordal length of at least one of the first and second major vane surfaces (45, 46) of one or more vanes (41) of the array.

Abstract: In an internal combustion engine having two exhaust gas turbochargers which are connected in series and a bypass line which bypasses the exhaust gas turbine close to the engine and extends to a collecting space of the turbine remote from the engine, and a blow-off valve is integrated into the turbine housing of the remote exhaust gas turbine for controlling a communication path between the collecting space and the turbine wheel, and includes a control sleeve supported axially movably between a closed position in which the communication path is blocked and a fully open position in which a flow path by-passing the turbine wheel of the turbine remote from the engine is provided.

Abstract: A turbine of a turbocharger includes a floating insert which defines a nozzle for passing a fluid and which is supported axially slidable with respect to a housing by a sliding support. Furthermore, the turbine comprises a sealing member for preventing a flow of fluid between the floating insert and the housing. The sealing member is axially expandable and has a fixed end attached to the turbine housing and an opposite movable end attached to the floating insert.

Abstract: A variable geometry turbine comprises a turbine wheel (5) supported in a housing for rotation about a turbine axis with an annular inlet passageway (9) defined between a radial face of a nozzle ring (11) and a facing wall of the housing (10). The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and has a circumferential array of vanes (20) that are received in corresponding slots (24) in the facing wall. A wastegate valve (15) is provided in a chamber behind the facing wall and gas bypasses the turbine through the chamber to the wastegate port (14) at high flow rates.

Abstract: A sliding piston cartridge (50) for a turbocharger (20) that is insertable into a bore (44) in the turbine housing (38) as a unit and that includes all of the components of a sliding piston type variable nozzle. The sliding piston cartridge comprises a carrier (52) having a tubular portion that interfaces with the bore of the turbine housing. A sliding piston (62) is disposed within the carrier and makes sliding contact therewith. Vanes (58) are mounted on or formed as a part of the carrier at its upstream end, the vanes extending across a turbine nozzle. The piston slides between a closed position and an open position relative to the carrier. The tubular portion of the carrier can include openings (66) that are progressively uncovered by the piston as it moves toward the open position, to allow additional flow to enter the turbine wheel without passing through the vanes.