Abstract: A variable inlet guide vane arrangement for a compressor includes a case defining an inlet of the compressor; at least one vane support coaxially disposed within the case; a plurality of vanes circumferentially disposed around the circumference of the case, each vane being pivotally mounted between the case and the at least one vane support; an actuator mechanism configured to pivot at least some of the plurality of vanes in an asymmetrical pattern around the circumference of the case. A method of controlling a variable inlet guide vane arrangement for a compressor includes pivoting at least some of the plurality of vanes in an asymmetrical pattern around the circumference of the case.

Abstract: An adjustment ring for turbocharger applications, particularly in diesel engines, is described, which consists of an iron-based alloy with an austenitic basic structure with dendritic carbide precipitations.

Abstract: One embodiment of the present invention is a unique turbine engine. Another embodiment is a unique vane actuation system. In one form, the actuation system includes a four bar linkage. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for turbine engines and vane actuation systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

Abstract: Variable elements of a turbine engine such as variable inlet guide vanes, variable bleed valves and variable stator vanes can be adjusted to provide a desired level of power and/or efficiency for the turbine engine across a range of operating conditions. The variable element settings typically determined through experimentation when the engine is new. Unfortunately, over the life cycle of the turbine engine, as wear occurs, the original variable element settings may no longer provide a desired level of power and efficiency. To correct this problem, offsets to the original variable element settings are calculated based on observable operational conditions which provide a measure of the wear that has occurred. The offsets are applied to the original variable element settings to generate corrected variable element settings. These corrected variable element settings are then used to configure the turbine engine.

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 apparatus for generating electric power from wind energy includes a blade device rotatable relative to a base to convert wind energy into a mechanical rotary power output, and having an upright rod connected with upright blades and coupled to a generator in the base to convert the mechanical rotary power output into electric power. Each blade has spaced wind-collecting ribs extending vertically from a first side surface thereof, thereby defining a wind-collecting space between any two adjacent wind-collecting ribs. A wind-collecting unit includes upright plates mounted on the base, angularly equidistant and disposed around the blade device. Any two adjacent plates define an inwardly converging wind-guiding channel therebetween. The plates are non-flat so that wind is guided by the plates to blow onto the first side surfaces of the blades via the wind-guiding channels.

Abstract: An exemplary assembly includes a component of a turbocharger that includes a bore that extends between an inner, exhaust gas side of the component and an outer, ambient side of the component; a shaft that includes a pin portion and a head portion; a sleeve positioned on the pin portion of the shaft; and a bushing positioned over at least part of the sleeve and over at least part of the head portion of the shaft where the bushing seats the shaft and the sleeve in the bore. During operation of a turbocharger that includes such an assembly, the shaft, the sleeve and the bushing restrict flow of exhaust gas from the inner, exhaust gas side of the component to the outer, ambient side of the component. Various other exemplary devices, assemblies, methods, etc., are also disclosed.

Abstract: A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and of vanes that are received in corresponding slots in the facing wall. Each vane major surface such that at a predetermined axial position of the nozzle ring relative to the facing wall the recess is in axial alignment with the slot and affords an exhaust gas leakage path through the inlet passageway. The recess is configured to reduce the efficiency of the turbine at small inlet gaps appropriate to engine braking or exhaust gas heating modes.

Abstract: A variable vane control system for use with a gas turbine engine includes a plurality of vanes, an actuation assembly, a mechanical linkage assembly, and a sensor. Each of the plurality of vanes has an airfoil portion disposed in a gas flowpath of the gas turbine engine, and a position of each of the vanes is adjustable with respect to an angle of attack of the airfoil portion of each vane. The actuation assembly is configured for generating actuation force to position the plurality of vanes. The mechanical linkage assembly operably connects the actuation assembly to at least one of the plurality of vanes. The sensor is configured to sense at least one of the position of the airfoil portions of the plurality of vanes and the mechanical linkage assembly, and to generate a position output signal.

Abstract: A variable-vane cartridge mechanism for a turbocharger is assembled from a nozzle ring, an insert that engages a turbine housing bore, and a plurality of spacers. Holes larger in diameter than the spacers are formed in the nozzle ring and a nozzle portion of the insert, such that the spacers fit loosely in the holes. A locating fixture is engaged with the nozzle ring and insert for precisely locating these parts radially (and optionally also axially) with respect to each other; the spacers can move within the holes as needed to allow the positions of the parts to be adjusted. Once located relative to each other, the nozzle ring and insert are fixed in the desired relative positions by affixing the spacers to them, such as by welding.

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: A variable stator vane assembly for a gas turbine engine has a projection protruding from the upper stem of the vane and which engages an aperture in the vane lever to provide a visual indication of correct alignment between the lever and the vane.

Abstract: A variable nozzle for a turbocharger (10) has a nozzle ring (138) supporting an array of vanes (134) that are variable in setting angle. The nozzle ring (138) is rotationally oriented and fixed in position by a plurality of circumferentially spaced, radially outwardly extending locating members (170) that engage corresponding locating grooves (159) in a flange member (157) of the turbocharger.

Abstract: The invention relates to an exhaust-gas turbocharger (1) as well as in particular a guide apparatus (13) for an exhaust-gas turbocharger (1). The guide apparatus (13) can have a ring of guide vanes (8), which are pivotable on a vane bearing ring (12) by vane studs (18). The vane studs (18) can be each attached to a vane lever (11). The vane levers (11) can have vane-lever-connectors (17, 10, 46, 47), which interact with unison-ring-connectors (16, 10, 57) of a unison ring (9) which is pivotable with respect to the vane bearing ring (12) in a way, that pivoting the unison ring (9) with respect to the vane bearing ring (12) results in a synchronous movement of one or more of the vane levers (11) and guide vanes (8). The unison ring (9) can be radially supported on axial bosses (14) of several vane levers (11).

Abstract: A circulation structure for a turbo compressor, in particular for a compressor of a gas turbine, is disclosed. The circulation structure includes at least one annular chamber that can be traversed in a circumferential direction, is concentric with a shaft of the turbo compressor in the region of the free blade ends of a blade ring, and radially borders a main flow channel. Several chambers that can be traversed in an axial direction are situated upstream of the or each annular chamber, when viewed from the main flow direction of the main flow channel.

Abstract: A variable geometry compressor for use in, for example, a turbocharger. A swing-vane diffuser is provided down-stream of the centrifugal compressor wheel. A nozzle ring is adjustable mounted on a center housing, and defines the nozzle face for the compressor diffuser. No spacers are deployed in the diffuser thereby improving efficiency, yet by stacking only the vanes and the nozzle ring, the diffuser clearances are maintained within strict tolerances. Further, seals, such as O-rings, are situated between the nozzle ring and the compressor housing and back plate to eliminate deleterious gas leaks between the diffuser and the spaces behind the nozzle ring.

Abstract: An inner shroud assembly includes an aft core segment mountable to a forward core segment to support a multiple of vanes for rotational movement relative thereto. A shroud backing plate segment engageable with the aft core segment and at least one fastener which passes through the shroud backing plate, the aft core segment and the forward core segment.

Abstract: A gas turbine generally exhibits a substantial deterioration in efficiency against fluctuation of gas flow rate. A variable nozzle turbine is a solution for this disadvantage; however, it has also another disadvantage of low efficiency under partial load conditions and a large number of heat-resistant moving components. A variable nozzle number turbine according to this invention overcomes these disadvantages. The turbine includes nozzles for injecting gas to rotor blades. The nozzles include inlet ports circumferentially arranged so as to be grouped into a group and an opening and closing valve disposed thereover so as to be commonly functioned therefore. This arrangement realizes a gas turbine with no deterioration of efficiency against fluctuation of gas inflow rate by only one heat-resistant moving component additionally installed. The variable nozzle number turbine according to this invention also realizes a turbine compressor with no surge limit when used as a regenerator.

Abstract: Accordingly, in one aspect, the invention relates to a variable guide vane for an axial flow compressor comprising: a first radially outer vane section; and a second radially inner vane section; the first and second vane sections angularly adjustable relative to each other about a longitudinal radial axis of the vane.

Abstract: A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a movable nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway. A substantially annular rib is provided either on the face of the nozzle ring (such that the minimum width of the inlet passageway is defined between the rib and the facing wall of the housing) or on the facing wall of the housing (such that the minimum width of the inlet passageway is defined between the rib and the nozzle ring).

Abstract: A pivot ring arrangement for a stage of variable stator vanes (VSVs) (38) in a gas turbine engine comprises a plurality of segments (12) secured in a segment carrier (22). The segments are injection molded from self-lubricating material, obviating the need for separate bushes for the VSV spindles (36).

Abstract: In one embodiment a transition section for a turbine engine is provided that includes one or more components constructed of a ceramic matrix composite. The transition section may fluidly connect a high-pressure turbine and a low-pressure turbine within the gas turbine engine. The transition section may include a transition duct and a variable area turbine nozzle. One or both of the transition duct and the variable area turbine nozzle may be constructed of the ceramic matrix composite.

Abstract: A variable vane shroud for a gas turbine engine comprises a cylindrically shaped body, a hole arranged at a circumference of the body, and a counterbore arranged concentrically around the hole on a radially inward facing surface of the body. The hole is for receiving a trunnion from a variable vane and the counterbore is for receiving a hub from the variable vane. A liner is inserted into the hole and counterbore such that the trunnion and hub are provided with a contact surface. The invention also provides a method for repairing a damaged counterbore in a variable vane shroud. A liner having a shape corresponding to a layer of material removed from the shroud is inserted into the void left by removing damaged material such that the counterbore is restored to pre-damaged dimensions.

Abstract: An ultra-high power density wind turbine system for producing energy from a wind including a structure having a shape adapted to produce a positive wind pressure on a high-pressure portion of a surface that faces into the wind and to produce a vacuum on two low pressure portions of its surface and one or more shrouded wind turbine systems mounted in the structure and comprising turbine stator vanes, turbine rotor blades and a turbine discharge duct adapted to channel turbine exhaust to exit the structure at the two low-pressure portions of the structure surface. In preferred embodiments the structure is a vertical tower that is generally cylindrical and the turbine is a horizontal axis axial flow shrouded wind turbine.

Abstract: A variable nozzle device including an annular nozzle passage formed by a gap between two opposing wall members and at least one vane rotatably supported in the nozzle passage. The vane is formed by a strip of sheet metal contoured to have an outer aerodynamic profile, and having a hollow interior with surfaces mimicking the outer profile. The vane is affixed to a shaft having a wind-stream portion forming two contact surfaces that conformingly receive opposing portions of the interior surfaces.

Abstract: A turbocharger is provided having a turbine wheel (4, 4?) with a plurality of extended tips (400, 400?); and a variable turbine geometry assembly in fluid communication with the turbine wheel and having a nozzle ring (6) with a plurality of vanes (7) movably attached thereto. One or more of the extended tips are non-parallel with an edge of one or more of the plurality of vanes. The incidence angle can vary and can be from 1 to 60 degrees. The extended tips can extend into an inlet of the vane space housing the vanes.

Abstract: A hydraulic servo drive device for driving a swing mechanism of a variable geometry turbocharger includes a servo piston connected to a driveshaft of the swing mechanism and a pilot spool that is accommodated in a center hole of the servo piston and slides by pilot pressure. A first hydraulic chamber to and from which pressure oil flows are provided in a housing. The servo piston separately includes a pressure port for introducing pressure oil from an outside, a first piston port for intercommunicating the center hole and the first hydraulic chamber, a second piston port for intercommunicating the center hole and the second hydraulic chamber, and a return port for exiting pressure oil.

Abstract: A method of operating a turbine engine, wherein the turbine engine includes at least three successive axially stacked rows of airfoils in one of a compressor and a turbine: a first airfoil row, a second airfoil row, and a third airfoil row. The first airfoil row and the third airfoil row both may comprise one of a row of rotor blades and a row of stator blades, and the second airfoil row comprises the other. The method includes: configuring the airfoils of the first airfoil row and the airfoils of third airfoil row such that at least a portion of the airfoils of the first airfoil row and at least a portion of the airfoils of the third airfoil row comprise a clocking relationship of between 25% and 75% pitch.

Abstract: A variable vane mechanism comprises a variable vane, an inner diameter shroud and a synchronizing mechanism. The variable vane comprises a vane body, an inner diameter trunnion extending radially inwardly from the vane body, and a button connected to the inner diameter trunnion and displaced radially inwardly from the inner diameter trunnion. The shroud comprises a shroud body, a socket extending into the shroud body for receiving the inner diameter trunnion, a flange extending into the socket for engaging the button and inhibiting radial movement of the variable vane, and a synchronizing channel extending through the inner diameter shroud aft of the socket so as to be bounded by the shroud body and opening to the socket. The synchronizing mechanism is disposed inside the synchronizing channel and connects to the inner diameter trunnion.

Abstract: A variable stator vane in a gas turbine engine has a journal provided with a circumferential recess. An aperture extends from the recess to a face of the journal directed towards the aerofoil portion of the vane. In operation of the engine, heated air, for example from a downstream compressor stage of the engine is admitted to the recess and flows through the aperture to, for example, the pressure surface of the aerofoil portion. The aerofoil portion is thereby heated, so preventing ice accretion on the vane.

Abstract: A gas-turbine axial compressor has a casing 3 and a rotatable shaft 5, which form an annular duct, in which at least one stator 2 and one rotor 4 are arranged. A shroud 21 is arranged at a free end of the stator 2 vanes, which extends over part of the axial length of the stator 2. A further part of the axial length of the stator 2, at which no shroud 21 is arranged, radially adjoins a rotor platform 28 formed by a rotor hub 8.

Abstract: The invention relates to an adjusting shaft arrangement (1) of a variable turbine geometry turbocharger or waste gate turbocharger having an adjusting shaft (2) which has a fastening section (3); having a lever (4) which is connected to the adjusting shaft (2) via the fastening section (3); having a sleeve (5) which is arranged on a base body (6) of the adjusting shaft (2); and having a seal (7) which is arranged in the region of the base body (6) between the sleeve (5) and the adjusting shaft (2); the main body (6) of the adjusting shaft (2) having a stepped outer contour; and the sleeve (5) having an inner contour with a stepped inner contour which complements the design of the base body (6).

Abstract: A variable-nozzle assembly comprises a nozzle ring and an array of vanes circumferentially spaced about the nozzle ring and rotatably mounted to the nozzle ring such that the vanes are variable in setting angle, and an insert having a tubular portion and an annular nozzle portion extending generally radially out from one end of the tubular portion. A plurality of axially extending holes extend through a thickness of the nozzle portion. A plurality of spacers have first ends joined to the nozzle ring, opposite second ends of the spacers being engaged in the holes and secured to the nozzle portion by welds formed at the second surface. An annular groove is defined in the second surface of the nozzle portion radially inward of and proximate to the holes. Alternatively or additionally, discrete recesses are formed in the second surface adjacent the holes. The groove and/or recesses facilitate weld penetration.

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: A novel method of manufacturing a turbine frame for rotatably holding adjustable blades in a VGS turbocharger is provided, which method is capable of manufacturing the turbine frame while almost eliminating a time-consuming cutting operation, whereby mass production of the turbine frame and the like can be realized. The method includes: a blank which is punched out from a metal material having a substantially constant thickness in such a manner as to integrally include a boss forming portion (24a) and a flange forming portion (23a) is used as a shaped material (W) serving as an original member for the turbine frame; when the shaped material (W) is processed, the boss forming portion (24a) is formed into a projecting state by a press forging tool; receiving holes for rotatably holding the respective adjustable blades are formed in the flange forming portion (23a) by punching; and when the shaped material (W) is processed, some or all of the manufacturing processes are carried out in a warm condition.

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, and a plurality of spacers connected between the nozzle portion of the insert and the nozzle ring. The turbine housing has a surface that directly contacts a surface of the nozzle ring that axially faces the insert for axially locating the nozzle ring relative to the turbine housing. A radial gap is defined between the turbine housing and the nozzle ring to allow radial movement of the nozzle ring relative to the turbine housing.

Abstract: An instability mitigation system is disclosed, comprising a stator stage located axially proximate to a rotor, the stator stage having a row of a plurality of stator vanes arranged around a centerline axis, and a mitigation system comprising at least one plasma actuator mounted on the stator vane that facilitates the improvement of the stability of the rotor, and a control system for controlling the operation of the mitigation system. An instability mitigation system further comprising a detection system for detecting an onset of an instability in a rotor and a control system for controlling the detection system and the mitigation system are disclosed.

Abstract: A tip turbine engine (30) includes a low pressure compressor (22) having a plurality of inlet guide vanes (55) that are mounted at an inlet to the compressor case (50). Each inlet guide vane (55) includes at least one fluid outlet (56) proximate a trailing edge of the inlet guide vane (55), such that fluid flow through the fluid outlet (56) modulates and controls the air flow into the compressor (22). A supply of pressurized fluid may be supplied from compressed air from the compressor (22).

Abstract: A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and of vanes that are received in corresponding slots in the facing wall. Each vane major surface such that at a predetermined axial position of the nozzle ring relative to the facing wall the recess is in axial alignment with the slot and affords an exhaust gas leakage path through the inlet passageway. The recess is configured to reduce the efficiency of the turbine at small inlet gaps appropriate to engine braking or exhaust gas heating modes.

Abstract: The invention relates to an adjusting ring (1) for adjusting the blades of the VTG distributor of exhaust gas turbochargers, comprising a bearing ring (2) and a lever engagement ring (3) connected to said bearing ring (2), the bearing ring (2) and lever engagement ring (3) being separately manufactured individual parts which are connected to each other by means of a separate connection device (4).

Abstract: The invention relates to a turbocharger for a combustion engine, in particular of a motor vehicle, with at least one variable turbine geometry turbine, which exhibits a rotor disk and vanes arranged on a vane support, which are spaced apart from each other around the rotor disk in at least one circumferential area, and with an adjuster to select the angular setting of the vanes. It is provided that the vanes (6) are fixed securely to the vane support (5), and exhibit different angular settings (?1, ?2, ?3) relative to the rotor disk (3) in varying sectors (8, 9, 10) of the circumferential area (7), wherein the turbine (2) exhibits a cover device (12) that can rotate relative to the vane support (5) with at least one opening (14, 20) in its jacket surface (16) for purposes of sector selection.

Abstract: The invention relates to a radial compressor having a suction-side opening and a pressure side. A swirl generator is placed upstream of the radial compressor. The swirl generator, has an inlet portion which is angularly configured relative to the outlet opening, the outlet opening facing the suction-side opening of the swirl generator. The swirl generator further has adjustable baffle plates arranged concentrically around the outlet opening.

Abstract: Variable geometry turbine, in particular a gas turbine, comprising a housing (2, 22), a turbine rotor (4), a fluid inlet scroll (1) that surrounds said turbine rotor, a vaned nozzle interposed between said inlet scroll and said turbine rotor conceived to accelerate the flow of fluid, said nozzle comprising an axially adjustable ring (5, 25) conceived to vary the nozzle gap (3, 23) and having a wall (19) delimiting said nozzle gap, said wall having balance holes (6, 26, 26?) connecting the nozzle gap with a chamber (12) delimited by said housing and said ring, characterised in that the edges (16), formed by said holes with the surface (18) of said wall facing the nozzle gap, are rounded in the portion (17, 17?) located downstream the holes with respect to the fluid flow. Turbocharger and supercharged engine comprising said turbine.

Abstract: Systems and methods for altering airflow to gas turbine engines are provided. In this regard, a representative system includes a gas turbine engine inlet having a slat, the slat being movable between a retracted position and an extended position. In the extended position, the slat increases an effective diameter of the inlet compared to the diameter of the inlet when in the retracted position.

Abstract: A turbocharger having a variable nozzle mechanism, which is accommodated in an accommodating chamber, is disclosed. The variable nozzle mechanism has a nozzle ring, a nozzle vane, a nozzle vane drive mechanism, and a support ring. The nozzle ring defines a gas passage through which exhaust gas is guided to a turbine wheel. The nozzle vane is supported by the nozzle ring and varies the flow area of the gas passage. The nozzle vane drive mechanism drives the nozzle vane. The support ring is connected to the nozzle ring. The nozzle vane drive mechanism is accommodated in the accommodating chamber as spaced from the nozzle ring through the support ring. The turbocharger has a drain passage that extends through a lower portion of the support ring and reaches the gas passage. The drain passage is located downward from the nozzle vane drive mechanism.

Abstract: A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a movable nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway. A substantially annular rib is provided either on the face of the nozzle ring (such that the minimum width of the inlet passageway is defined between the rib and a the facing wall of the housing) or on the facing wall of the housing (such that the minimum width of the inlet passageway is defined between the rib and the nozzle ring).

Abstract: The invention relates to a turbocharger with a variable turbine geometry. Said turbocharger comprises a blade bearing ring assembly (1) with a blade bearing ring (2) and a disc (3), which can be fixed to the blade bearing ring (2) to create a flow channel (4) and also comprises at least one bearing pin (5), one first end (6) of which is connected to the blade bearing ring (2) and the second end (7) of which is connected to the disc (3). Both ends of the bearing pin are butt welded to the blade bearing ring (2) and the disc (3).

Abstract: The present invention is a turbocharger unit (10) incorporating variable turbine geometry. The unit (10) has a turbine for receiving exhaust gases from an engine having a turbine wheel (14) located inside a turbine housing (12), and an intermediate housing (24) connected to the turbine housing (12), having a recessed portion (28). A spring member is located in the recessed portion (28), and a heat shield (32) for receives apply force from the spring member. There is also a cartridge (36) for providing variable turbine geometry located between a first disk (34) and a second disk (40) in the turbine housing (12); the second disk (40) is held in contact with the turbine housing (12) by a contoured sleeve (26). The apply force received by the heat shield (32) from the spring member transfers through the first disk (34), the cartridge (36), and the second disk (40), locating the cartridge (36) in proximate relationship to the turbine wheel (14).

Abstract: A turbine assembly for a variable-geometry turbocharger includes a turbine housing defining a divided volute having first and second scrolls, wherein the first scroll has a substantially smaller volume than the second scroll. The first scroll feeds exhaust gas to a first portion of a turbine wheel upstream of the throat of the wheel, while the second scroll feeds gas to a second portion of the wheel at least part of which is downstream of the throat. Flow from the second scroll is regulated by a sliding piston. The first scroll can be optimized for low-flow conditions such that the turbocharger can operate effectively like a small fixed-geometry turbocharger when the piston is closed. The turbine housing defines an inlet that is divided by a dividing wall into two portions respectively feeding gas to the two scrolls, a leading edge of the dividing wall being downstream of the inlet mouth.

Abstract: A variable nozzle device comprises a wall member, a unison ring provided on a first side of the wall member, and a vane, a vane body of which is provided on a second side of the wall member, said second side being opposite to said first side, wherein said vane further having a tab member comprising a tab portion and a shaft portion, said shaft portion being movably inserted in a slot of the wall member; and said tab portion being adapted to hold the vane body by abutting against a portion of the wall member which defines the slot, wherein the vane body and the tab member are provided as separate, parts and are fixable to each other.