Abstract: An air blower includes an impeller rotatable about a central axis extending vertically, a motor to rotate the impeller, and a holder to hold the motor. The air blower is a centrifugal air blower which generates a radial airflow perpendicular to the central axis. The holder includes a base supporting the motor, attachments on a radial directional-outer side of the impeller, arms connecting the base and each of the attachments, and a wall surface on a side of the impeller, between the base and each attachment, and opposing a radial-directional inner side. An axial lower end of the impeller is located below an axial upper end of the wall surface.

Abstract: A variable turbine geometry assembly for controlling flow of exhaust gas to a turbine wheel of a turbocharger includes an adjustment ring extending about an axis and rotatable about the axis, at least one vane lever coupled to the adjustment ring, and at least one vane coupled to the at least one vane lever. The at least one vane is moveable with respect to the adjustment ring when the adjustment ring rotates about the axis. The variable turbine geometry assembly further includes a wave spring operably in contact with at least one of the at least one vane lever and the adjustment ring. The wave spring is configured to bias one of the at least one vane lever and the adjustment ring toward the other of the at least one vane lever and the adjustment ring.

Abstract: A convertible ducted fan engine having a shroud, a drive shaft connected to a mechanical fan, and a rotational drive motor configured to rotate the mechanical fan. An embodiment includes a linear drive motor configured to translate the drive shaft and mechanical fan in a direction parallel to a longitudinal axis of the shroud. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis.

Abstract: An internal combustion engine has first and second combustion chambers, first and second exhaust gas line elements, and an exhaust gas turbocharger which has a first flood, a second flood, and a third flood. A bypass device has a bypass line that can be flowed through by exhaust gas from the first and second exhaust gas line elements and via the bypass line a turbine wheel is bypassed by a first part of the exhaust gas from the first and second exhaust gas line elements. A valve device includes a first valve element, via which an amount of the exhaust gas flowing through the bypass line and bypassing the turbine wheel from the first and second exhaust gas line elements is settable. A third exhaust gas line element opens out into the third flood.

Abstract: The invention relates to an inner ring for a guide vane assembly for mounting adjustable guide vanes of a turbomachine, of a compressor stage or turbine stage of a gas turbine, a guide vane assembly for a turbomachine having an inner ring, a turbomachine having an inner ring, and a method for producing an inner ring, wherein the inner ring has a plurality of guide vane bearing mounts, which are each arranged spaced apart in the peripheral direction, recesses, which are each formed for receiving a bearing element, a bearing journal, of a guide vane, wherein, between at least two adjacent guide vane bearing mounts, the inner ring has at least one depression with a wall thickness in a radial direction that is reduced in comparison to a region that abuts the depression and is outside of the depression.

Abstract: A sealing-coupled apparatus of a turbocharger may include a vane cover installed in front of a turbine vane set in a turbine housing, the vane cover configured to cover the turbine vane and to define a fluid passage through which a fluid may be fed to an outlet hole extending in the turbine housing, and a sealing member having a tubular shape with a predetermined thickness, the sealing member being engaged with a front end of the vane cover and having an annular groove formed around an outer circumferential surface of the sealing member, with a sealing ring fitted over the groove and spacing the vane cover apart from the turbine housing in a radial direction.

Abstract: A centrifugal compressor that includes an impeller, a diffuser and a shroud. One of the diffuser and shroud includes a plurality of recesses and the other of the diffuser and shroud includes a plurality of radial vanes. The shroud covers the impeller and diffuser such that each radial vane projects into a respective recess.

Abstract: In an internal combustion engine comprising a turbocharger which includes a turbine which is located in an exhaust tract of the internal combustion engine and to which exhaust gas of the internal combustion engine is applied via an exhaust pipe system of the exhaust tract, the turbine comprises volute passages distributed along the circumference of the turbine wheel and the exhaust gas flows are combined and divided upstream of the turbine into at least two exhaust gas part-flows each of which part-flows is fed to one of the volute passages.

Abstract: In an adjusting device for a charger device, in particular an exhaust gas turbocharger, with a holding ring on which a plurality of guide vanes is mounted in an operative connection with an actuating ring via a respective connecting element and whose respective angle of attack is adjustable by rotation of the actuating ring, the respective connecting elements are in an operative connection with the actuating element via at least one effective area which extends slant to the axial direction of the adjusting device so as to bias the connecting elements and the guide vanes associated therewith in a predetermined axial direction.

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

Abstract: The invention relates to a turbocharger (1) with variable turbine geometry (VTG), having a turbine housing (2) with a supply duct (9) for exhaust gases, having a turbine rotor (4) which is rotatably mounted in the turbine housing (2); and having a guide grate (18), which surrounds the turbine rotor (4) radially at the outside, which has a blade bearing ring (6), which has a multiplicity of guide blades (7) which have in each case one blade shaft mounted in the blade bearing ring (6), which has an adjusting ring (5) which is operatively connected to the guide blades (7) by means of associated blade levers (20) fastened to the blade shafts (8) at one of their ends, with each blade lever (20) having, at the other end, a lever head (23) which can be placed in engagement with an associated engagement recess (24) of the adjusting ring (5), and which has a stop (25) at least for setting the minimum throughflow through the nozzle cross sections formed by the guide blades (7), wherein the stop (25) is formed as a part

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: A drive ring bearing has a body with a generally cylindrical outer peripheral surface, and a generally u-shaped cross-section, with over a circumferential portion of the body. A web defines the outer peripheral surface. Radially inwardly extending legs define the u-shape in combination with the web. A plurality of circumferentially spaced feet extend from the outer peripheral surface of the body to an inner peripheral surface of the body. In addition, a diffuser assembly incorporating the drive ring bearing, a compressor assembly including the diffuser assembly, and a method of mounting the drive ring bearing are also disclosed.

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 turbocharger with a variable turbine geometry device has one or two blade bearing rings. At least one or more fastening elements are provided for fastening the one or two blade bearing rings. The respective fastening element has at least one section formed with a knurl and/or at least one section formed with at least one or several notches.

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 turbocharger with a variable turbine geometry, includes at least one rolling body element respectively disposed on an associated fixing element for the variable turbine geometry. A device for adjusting the variable turbine geometry can roll off on the respective rolling body element.

Abstract: This relates to a nozzle blade in which the leading edge shape has a curved-line shape that is formed by the distance from the rotation axis of the nozzle blade to the leading edge changing depending on the nozzle blade height position, and the trailing edge shape has a straight-line shape that is formed by the distance from the rotation axis of the nozzle blade to the trailing edge being constant irrespective of the nozzle blade height position.

Abstract: A system for controlling at least two sets of variable geometry equipment of a gas turbine engine including at least one first body and a second body, the first set of equipment being a stage of variable stator vanes of a compressor of the first body moving between a closed position during idling and an open position at high speed, and the second set of equipment being at least one bleed valve of a compressor of the second body moving between an open position during idling and a closed position at high speed. An actuator actuates the two sets of equipment.

Abstract: A vane (234) is provided which reduces leakage of gas in a variable geometry turbocharger (210) from the high pressure side of the vane (234) to the low pressure side of the vane (234). The vane (234) can have a channel (330, 430) along a gas bearing surface (325, 425) for reducing the leakage. The channel (330, 430) can be defined at least in part by sideplates (300, 350). The sideplates (300, 350) can be integrally cast with the rest of the vane (234). At least one of the sideplates (300, 350) can have a hole therein for a vane shaft (228) which allows movement of the vane (234) for gas flow control. The sideplates (300, 350) can have edges (301, 351) that conform to the shape of the gas bearing surface (325, 425).

Abstract: A variable-vane assembly for a variable nozzle turbine comprises a nozzle ring supporting a plurality of vanes affixed to vane arms that are engaged in recesses in the inner edge of a unison ring. The unison ring is rotatable about the axis of the nozzle ring so as to pivot the vane arms, thereby pivoting the vanes in unison. The unison ring is radially restrained by a combination of radial guide rollers and fixed axial-radial guide pins secured to the nozzle ring, and is axially restrained by one or more axial stops affixed to the nozzle ring.

Abstract: A turbomachine comprises a flow duct with coaxially arranged radially inner and outer endwalls, first and second sets of axially spaced rotor stages arranged between the inner and outer endwalls, and a plurality of variable endwall segments arranged along the inner endwall. The first set of rotor stages rotates in a first direction, and the second set rotates in a second direction. The first and second sets alternate in axial series along the flow duct, such that axially adjacent rotor stages rotate in different directions. The variable endwall segments are radially positionable, in order to regulate loading on the first and second sets of rotor stages by changing a cross-sectional flow area between the inner and outer endwalls.

Abstract: A multipurpose rotary device includes a rotor configured to include a plurality of blades in a circumferential direction; and a load guide body configured to guide a flow of fluids flowing into the inside of the rotor, wherein the load guide body includes an upper support member and a lower support member configured to be disposed to face each other at the upper and lower sides thereof and connected to one another such that the rotor is rotatably installed; load guide plates configured to correspond to the blades and are rotatably installed between the upper and lower support members in a longitudinal direction; and stop pins configured to be formed on inner surfaces facing the upper and lower support members to control a rotational angle of the load guide plates.

Abstract: The invention relates to a charging device (1), more preferably an exhaust gas turbocharger for a motor vehicle, which turbine geometry comprises guide blades (5) rotatably mounted in a blade bearing ring (4), wherein the blade bearing ring (4) with a side is directly exposed to a hot gas flow (12) while the side of the blade bearing ring (4) facing away from this is only indirectly exposed to the hot gas flow (12). It is substantial to the invention that the blade bearing ring (4) on its side directly exposed to the hot gas flow (12) is produced of a different material than on its side only indirectly exposed to the hot gas flow (12) wherein the two materials with regard to their heat expansion coefficients are selected in such a manner that the blade bearing ring (4) at preferentially all occurring operating temperatures expands evenly without warping.

Abstract: A compressor performance adjustment system includes a compressor chassis defining an inlet passageway, a diffuser passageway coupled to the inlet passageway, and a return passageway extending from the diffuser passageway. At least one inlet vane is located in the inlet passageway. At least one diffuser vane is located in the diffuser passageway. At least one return vane is moveably coupled to the compressor chassis and located in the return passageway. The return vanes may be adjusted without disassembling the compressor chassis in order to adjust the flow incident on compressor components and adjust the performance of a compressor.

Abstract: An axial flow turbine is described having a casing defining a flow path for a working fluid therein, a rotor co-axial to the casing, a plurality of stages, each including a stationary row of vanes circumferentially mounted on the casing a rotating row blades, circumferentially mounted on the rotor, with within a stage n vanes have an extension such that at least a part of the trailing edge of each of the n vanes reaches into the annular space defined by the trailing edges of the remaining N-n vanes and the leading edges of rotating blades of the same stage.

Abstract: The present invention relates to a turbomachine comprising at least one bladed disk, be it mobile or static, and vortex generators (17) positioned upstream of the blading (1) of said disk, wherein the vortex generators (17) are of variable pitch.

Abstract: A method and a device to counteract wear about a guide vane (16) from a particle bearing drive water, the guide vane (16) being arranged in a guide vane housing (14) in a water turbine (1), and where the method comprises: —routing a supply channel (36) for water cleaner than the drive water to the attachment point area between the guide vane (16) and the guide vane housing (14); and—leading water cleaner than the drive water to flow through a slit (28) where the slit (28) at least partly encircles the guide vane (16).

Abstract: A variable geometry turbine comprises: a turbine wheel mounted within a housing assembly for rotation about a turbine axis, the housing assembly defining a radial gas flow inlet passage; an annular wall member defining one 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; and a linkage mechanism comprising at least one actuating member operably connected to the annular wall member to control displacement of the wall member. The actuating member extends in a direction substantially parallel to the turbine axis through an aperture defined by a retaining member such that a first bearing surface defined by the actuating member extending transverse to the turbine axis is contacted by a surface of the retaining member so as to connect the actuating member to the annular wall member.

Abstract: A control system for controlling at least two variable-geometry devices of a turbomachine, and a turbomachine including such a control system, the system including an actuator that actuates both devices; one of the devices including at least one stage of variable-pitch stator vanes, and the other device being an air-bleed valve for a turbomachine body. The system is configured to control progression opening of the vane stage and progressive closing of the air-bleed valve as an actuation parameter of the actuator increases. As a result, the control system serves advantageously to control two devices using a single control system.

Abstract: A turbocharger with a variable nozzle includes a pin mounted in the center housing and extending axially therefrom and engaged in a hole in the nozzle ring to orient the nozzle ring rotationally relative to the center housing. A portion of a length of the pin has a substantially greater compliance than the remainder of the length such that the pin has a flexible tip that engages the hole in the nozzle ring. The flexible tip reduces constraint of thermal deformation of the nozzle ring. The pin portion of greater compliance can be a section of the tube that is slit and expanded. The turbocharger can also include a one-piece locator and heat shield having a locating portion abutting the center housing and the nozzle ring for radially locating the nozzle ring relative to the center housing, and having a shield portion shielding the center housing from hot exhaust gas.

Abstract: A variable geometry turbocharger employs multiple vanes in the turbine inlet with a unison ring and integral cast wall in the turbine housing forming the nozzle walls. An actuator rotates the unison ring through a rack and pinion driven crank shaft to move the vanes through a range of vane positions that extends between a hard-stop closed position and a hard-stop open position, and that includes a reference position corresponding to a desired flow condition. A variable geometry turbine controller uses a sensor indicating the actuation position of the actuator to guide the operation of the vanes to the reference position. The controller intermittently directs the actuator to force the vanes to the hard-stop closed and hard-stop open positions, and uses sensor information from those positions to reestablish the reference-position information that the actuator uses to guide the actuation of the vanes.

Abstract: A vane (234) is provided which reduces leakage of gas in a variable geometry turbocharger (210) from the high pressure side of the vane (234) to the low pressure side of the vane (234). The vane (234) can have a channel (330, 430) along a gas bearing surface (325, 425) for reducing the leakage. The channel (330, 430) can be defined at least in part by sideplates (300, 350). The sideplates (300, 350) can be integrally cast with the rest of the vane (234). At least one of the sideplates (300, 350) can have a hole therein for a vane shaft (228) which allows movement of the vane (234) for gas flow control. The sideplates (300, 350) can have edges (301, 351) that conform to the shape of the gas bearing surface (325, 425).

Abstract: A variable nozzle system can comprise a gas inlet ring, an opposing gas outlet ring, an actuation ring, guides, and vanes circumferentially spaced about and disposed between the gas inlet ring and the gas outlet ring. The gas inlet ring, the gas outlet ring, and the vanes can form nozzles, the nozzles being variable by rotation of the vanes about a pivot axis. The plurality of guides can extend from the gas inlet ring, the gas outlet ring, or the actuation ring, and the vanes can be connected to the actuation ring, so that each vane can be rotated by rotation of the actuation ring and by sliding against a respective guide from the plurality of guides. The actuation ring can have a gear rack and can be rotated by rotatable engagement of the gear rack with a pinion attached to the end of a rotatable gear shaft.

Abstract: A sealing device for prevention of exhaust gas in a scroll passage from leaking via a gap to a turbine impeller is arranged upstream, in a travel direction of the exhaust gas, of through-holes via which the vane shafts extend through a rear exhaust introduction wall, whereby pressure in a gap communicating with the through-holes of the rear wall is kept lower than pressure in an exhaust nozzle so as to displace nozzle vanes to the rear wall.

Abstract: A variable geometry turbocharger assembly comprises a unison ring which rotates about a longitudinal axis defined by a shaft on which a turbine wheel and compressor wheel are attached in order to pivot a plurality of vanes and thereby control a flow of exhaust gas to the turbine wheel. The unison ring rotates on at least one guide pin which is secured to the turbocharger. The guide pins may be press-fit into apertures in a center housing at an outer pilot surface. In other embodiments the guide pins may be press-fit into a different part of the turbocharger such as a nozzle ring. The guide pins may each have a wear surface which defines a circumferential radius of curvature which is substantially equal to a circumferential radius of curvature of a radially inner surface of the unison ring.

Abstract: In an exhaust gas turbocharger for an internal combustion engine, including a turbine housing and a rotor, the housing having an exhaust gas guide section and the rotor including a turbine wheel and a shaft connected to the turbine wheel which is driven by exhaust gas, and a control device for controlling the exhaust gas flow to the turbine wheel comprising an annular guide vane structure and an axial slide supported on a contour sleeve mounted to the turbine housing remote from the rotor and extending toward the rotor and forming also the turbine exhaust gas discharge duct, the axial slide includes a cavity accommodating the guide vane structure.

Abstract: A variable-capacity exhaust turbocharger is provided which is equipped with a variable-nozzle mechanism having a lever plate and a peripheral structure capable of ensuring regular operability of a nozzle vane and of preventing an occurrence of local excessive stress by increasing rigidity of the lever plate without increasing a thickness of the lever plate.

Abstract: When changing a nozzle blade angle by rotating a drive ring, a contact load generated between an inner circumferential surface of the drive ring and an outer circumferential surface of a mount can be reduced, allowing the drive ring to rotate smoothly and reducing the amount of wear and a driving force. It is also possible to reduce an impact force, such as engine vibrations, generated at the drive ring when an external force acts, reducing the risk of damage. A plurality of notches (19) are provided at an inner rim of the drive ring (14), and, among inner circumferential surfaces (14a, 14b, 14c, 14d, 14e, 14f, 14g, and 14h) located between the notches (19), when a driving force for rotating the drive ring (14) is applied, the inner diameters of the inner circumferential surfaces (14e, 14f, 14g, and 14h) where the contact load with the outer circumferential surface of a mount becomes large are made larger than the outer diameter of the outer circumferential surface.

Abstract: A system for controlling at least two variable-geometry equipments of a gas turbine engine is disclosed. The engine includes at least a first core rotating at a first speed and a second core rotating at a second speed. The first equipment includes at least one variable-pitch stator blade of a compressor of the first core and the second equipment includes at least one air bleed valve of a compressor of the second engine core moving between an open position at idle speed and a closed position at high speed. The system includes an actuator which actuates both equipments.

Abstract: A system for controlling at least two variable-geometry equipments of a gas turbine engine is disclosed. The engine includes at least a first core rotating at a first speed and a second core rotating at a second speed. The first equipment includes at least one variable-pitch stator blade of a compressor of the first core and the second equipment includes at least one air bleed valve of a compressor of the second engine core moving between an open position at idle speed and a closed position at high speed. The system includes an actuator which actuates both equipments.

Abstract: A variable-nozzle turbocharger includes a cartridge containing a variable vane mechanism connected between the center housing and the turbine housing. The cartridge comprises an annular nozzle ring supporting an array of rotatable vanes, an insert having a tubular portion sealingly received into the bore of the turbine housing and having a nozzle portion extending radially out from one end of the tubular portion and being axially spaced from the nozzle ring with the vanes therebetween, a plurality of spacers connected between the nozzle portion of the insert and the nozzle ring, and an annular retainer ring fastened to the center housing so as to capture the nozzle ring between the retainer ring and the center housing. The retainer ring is formed as a separate part from the insert ring and is mechanically and thermally decoupled from the insert.

Abstract: A system for controlling at least two variable-geometry equipments of a turbomachine, in which the first equipment is a variable pitch stator blade stage of a compressor of a first core moving between a closed position at idle speed and an open position at high speed, and the second equipment is at least one bleed valve of a compressor of a second core moving between an open position at idle speed and a closed position at high speed, is disclosed. The actuator operates over a portion of its travel a first branch of an angle transmission member which actuates the first equipment and leaves this branch at rest on an abutment over the rest of its travel. The actuator operates the second equipment via a sliding junction member arranging a free travel in the actuation of said second equipment.

Abstract: A turbine of a turbocharger comprises 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 means. Said floating insert is axially supported by said guiding means formed by a portion of a center housing.

Abstract: An example compressor shroud assembly includes a shroud body extending along an axis and having a hollow bore. An enlarged flange is located at one axial end of the shroud body. The enlarged flange provides a rotating surface for a retention plate on a first side and a rotating surface for a drive ring on an opposing, second side. The enlarged flange establishes a channel that receives the retention plate. The channel has a ratio of the channel depth to the channel width that is between 0.0216 and 0.0251.

Abstract: A vane for a turbine assembly of a turbocharger includes a first airfoil that includes a length between a leading edge and a trailing edge, a second airfoil that includes a length between a leading edge and a trailing edge where the length of the first airfoil optionally differs from the length of the second airfoil, and one or more intra-vane throats defined at least in part by the first airfoil and the second airfoil. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: To provide a turbocharger whose lifetime is long, which is capable of inexpensively and precisely performing nozzle vane angle synchronous control by using inexpensive and highly wear resistant components in a link mechanism for driving a rotation mechanism of nozzle vanes of an adjustable nozzle mechanism. As pins fixedly arrayed in a ring plate rotatably supported on the turbocharger, that set an angle of the nozzle vanes for controlling an amount of exhaust gas for rotating a turbine rotor, each pin in which a hard coating with a thickness of approximately 2 ?m which is formed of Al, Cr, Si, and N by physical vapor deposition is formed onto an austenitic stainless steel as a base material, is used.

Abstract: A turbocharger having a sliding piston for regulating exhaust gas flow into the turbine wheel includes a set of first vanes mounted on a fixed first wall of the turbine nozzle and projecting axially toward an opposite second wall of the nozzle, and/or a set of second vanes mounted on the end of the piston and projecting in an opposite axial direction toward the first wall of the nozzle. For the/each set of vanes, there are leakage dams formed on the wall that is adjacent the vane tips when the piston is closed. The leakage dams are closely adjacent the vane tips and discourage exhaust gas from leaking in a generally radial direction past the vane tips as the piston just begins to open from its fully closed position.

Abstract: A guide device with adjustable guide vanes is provided with a drive for the adjustable guide vanes, in which a cylindrical driving pin and an adjusting lever are provided each with one surface pair which are matched to one another and which slide on one another in operation when the guide vanes are being adjusted. To adjust the guide vanes, the adjusting ring is moved, by which the driving pin attached to the adjusting ring slides in an elongated groove of the adjusting lever and applies a force to the adjusting lever. This approach yields an economical and durable structure which is easy to install. This results in surface support with the corresponding low compressive loads per unit area and consequently greatly reduced wear.

Abstract: Disclosed are retainers for a turbocharger. In one embodiment, the retainer includes a generally annular body that defines a bore and one or more channels. The bore is generally directed along a central axis of the body and can be configured to mate with a nose of a center housing of a turbocharger. The channels can be configured to accommodate vanes associated with a cartridge assembly of the turbocharger. One or more legs may extend from the retainer body and may be configured to mate with and locate the retainer relative to a cartridge assembly for the turbocharger. The retainer can also include a concave portion disposed around a perimeter of the body. The concave portion and the body may be together configured to act as a spring when the retainer is mechanically loaded in a direction having a component parallel to the central axis. Also disclosed are corresponding turbochargers.