Abstract: A turbocharger having a variable turbine nozzle that includes an array of vanes whose setting angle is adjustable by rotation of a crank shaft coupled with a unison ring that pivots the vanes. The crank shaft is rotated by an actuation system made up of a piston contained in a bore formed in the center housing, and a hydraulic system for supplying pressurized hydraulic fluid to the bore selectively on one side or an opposite side of the piston for causing the piston to move in one direction or the other. The piston is connected to the crank shaft by a mechanical linkage that converts reciprocating movement of the piston to rotational movement of the crank shaft. A spring is arranged between the piston and a surface of the bore and continuously exerts a spring force on the piston toward the fully open position of the piston.

Abstract: A vane ring assembly which includes a lower vane ring (23), an upper vane ring (31), one or more guide vanes (80) positioned at least partially between the vane rings, and a plurality of spacers (49, 50 or 59) positioned between the lower and upper vane rings (23, 31) for maintaining a distance between the lower and upper vane rings, the vane ring assembly being retained in a turbine housing (102) by a retaining ring (400) which is located in a groove (510) in the turbine housing.

Abstract: A variable nozzle for a turbocharger includes a plurality of vanes rotatably mounted on a nozzle ring and disposed in a nozzle flow path defined between the nozzle ring and an opposite nozzle wall. Either or both of the faces of the nozzle ring and nozzle wall include(s) at least one step that defines sealing surfaces positioned to be substantially abutted by airfoil surfaces of the vanes in the closed position of the vanes and to be spaced from the airfoil surfaces in positions other than the closed position. This substantial abutment between the airfoil surfaces and the sealing surfaces serves to substantially prevent exhaust gas from leaking past the ends of the airfoil portions. At the same time, clearances between the nozzle ring face and the end faces of the airfoil portions can be sufficiently large to prevent binding of the vanes under all operating conditions.

Abstract: A variable-nozzle turbocharger includes a turbine housing and a center housing, and a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes are rotatably adjustable for regulating exhaust gas flow to the turbine wheel. An elastically deformable member is disposed between a radially inwardly facing surface of the nozzle ring and a radially outwardly facing surface of the center housing, the elastically deformable member having a radially inner surface contacting the radially outwardly facing surface of the center housing and having a radially outer surface contacting the radially inwardly facing surface of the nozzle ring so as to radially center the nozzle ring relative to the center housing.

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: A nozzle for radial inflow turbines having an outer surface having a concave shape, and an inner surface having a non-concave, i.e. straight or convex, shape. Also a leading edge may have a hole that is capable of receiving a fastener to secure the nozzle vane to an assembly housing.

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.

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 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: 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 actuation system is disclosed herein. The variable vane actuation system includes a first vane having a first vane axis. The variable vane actuation system also includes an actuator operably engaged with the first vane to selectively pivot the first vane about the first vane axis. The variable vane actuation system also includes a ring member operably connected with the first vane. The ring member is disposed for pivoting movement about a centerline axis transverse to the first vane axis. The variable vane actuation system also includes a second vane having a second vane axis spaced from the first vane axis about the centerline axis. The second vane is operably connected with the ring member. Forces moving the second vane are generated by the actuator and transmitted first through the first vane and then through the ring member before being applied to the second vane.

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: The guide blades provided for the variable turbine geometry are adjustably arranged within a radial gap through which gases can flow on a moveable carrier ring, which is axially clamped against stops on or in the radial gap with a thrust spring device. According to the invention, the thrust spring device loads the carrier ring on the positions closely adjacent to the stops. The thrust spring device is designed open without sealing function and if applicable combined with a separate seal without thrust function.

Abstract: An apparatus for adjustment of inlet guide vanes of a compressor includes a ring having a plurality of slots spaced around a circumference thereof; a plurality of lever arm assemblies each having a pin that includes a body with a first end and a second end and a lever arm extending perpendicularly from the second end of the body of the pin; a plurality of vanes each coupled to an end of one of the plurality of lever arms by a shaft; and a rack and pinion drive mechanism. The pin of each of the lever arm assemblies is configured to be positioned within each of the plurality of slots such that the first end of the pin extends into the slot. The rack and pinion drive mechanism includes a pinion coupled to the shaft of one of the plurality of vanes, thereby creating a drive vane; and a driven rack operationally coupled to the pinion. The drive vane is configured to rotate the ring via the rack and pinion drive mechanism, thereby adjusting an angular position of the plurality of vanes.

Abstract: A variable nozzle for a turbocharger includes a plurality of vanes rotatably mounted on a nozzle ring and disposed in a nozzle flow path defined between the nozzle ring and an opposite nozzle wall. Either or both of the faces of the nozzle ring and nozzle wall include(s) at least one step that defines sealing surfaces positioned to be substantially abutted by airfoil surfaces of the vanes in the closed position of the vanes and to be spaced from the airfoil surfaces in positions other than the closed position. This substantial abutment between the airfoil surfaces and the sealing surfaces serves to substantially prevent exhaust gas from leaking past the ends of the airfoil portions. At the same time, clearances between the nozzle ring face and the end faces of the airfoil portions can be sufficiently large to prevent binding of the vanes under all operating conditions.

Abstract: The invention relates to a variable turbine geometry (12) of a supercharging device, in particular an exhaust gas turbocharger for an internal combustion engine. The variable turbine geometry (12) comprises guide vanes (30) that are assigned to the circumference of a turbine rotor and are operated by means of a control ring (22) that is accommodated on journals (16) of the guide vanes (30). The control ring (22) is locked on these supporting journals (16) of the guide vanes (30).

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: A turbocharger comprising a turbine housing where at least one supply channel supplies an exhaust gas. The exhaust gas is fed through a guide grid that forms passages of variable cross-section between the supply channel and a turbine rotor. This guide grid comprises a plurality of vanes of predetermined width in a vane space of about the same width. A vane support ring defines one axial end of the annular vane space and an opposite ring is spaced from the vane support ring by about the width of the vanes to define the other axial end of the annular vane space. To maintain this width, at least two spacers are integrally formed on at least one the rings.

Abstract: An exhaust turbocharger equipped with a nozzle throat area varying mechanism can be provided in which brazing welding is achieved with a small number of man-hour and at low cost, and which is stable in quality without danger of fracture of brazing-welded parts of constituent members. The variable-throat exhaust turbocharger equipped with a nozzle throat area varying mechanism for varying the blade angle of a plurality of nozzle vanes supported rotatably by members including turbine casing, is characterized in that members having at least one through-hole with at least one shaft member to be inserted into the through-hole(s) to be fixed therein among constituent members of the nozzle throat area varying mechanism are connected by means of brazing welding.

Abstract: The invention relates to a turbocharger (1) with a variable turbine geometry (VTG), comprising a turbine housing (2) that has a supply channel (9) for exhaust gases, a turbine rotor (4), which is rotatably mounted in the turbine housing (2) and a guide baffle (18), which radially surrounds the exterior of the turbine rotor (4) and has a blade bearing ring (6) with a plurality of guide blades (7), each of the latter having a blade shaft (8) that is mounted on the blade bearing ring (6). The guide baffle also has an adjusting ring (5), which interacts with the guide blades (7) by means of associated blade levers (20), which are fixed to the blade shafts (8) by one of their ends (21). The other end (22) of each blade lever (20) is provided with a lever head (23), which can be engaged in an associated engagement recess (24) of the adjusting ring (5).

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.

Abstract: Vane, fin, and hole arrangements establish a predetermined reduced swirl at the inlet of mechanical seals and the inlet of a variable axial orifice gap which act in harmony as an axial thrust equalizing system for use in liquid cryogenic turbines and pumps. In said establishment the stiffness, damping, and inertia in said seal in conjunction with said variable orifice gap is manipulated, including the destabilizing cross-coupled stiffness which is reduced. Said seal is of either labyrinth annular type formed by a plurality of teeth, annular smooth, or a plurality diamond annular surface pattern. Said variable orifice gap is smooth. Liquid for the axial thrust equalizing seal is initially bled from the main to pass through a preset deswirl mechanism. The deswirl mechanism consists of either a plurality of vanes, fins, grooves, or circular holes that guide liquid radial inward before passing through said mechanical seal.

Abstract: There is provided an adjustable vane turbine and turbine generator using the same, in which hydrodynamic properties are employed to adjust adjustable vanes automatically in response to flow condition such as the flow rate of the working fluid, thereby simplifying the system using the adjustable vanes and reducing cost. In the adjustable vane turbine, a turbine wheel is installed in a turbine housing and rotatably supported by a shaft, and a plurality of adjustable vanes are movably installed between the turbine housing and the turbine wheel, wherein each of the adjustable vanes includes an adjustable vane member having one end portion rotatably fixed to the turbine housing, a vane control element attached on one side of the adjustable vane member at a set angle, and a guide element attached on the other side of the adjustable vane member, the plurality of adjustable vanes being connected using links between neighboring vanes.

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: Rotor and stator assemblies that utilize magnetic bearings for supporting the rotor shaft during operation can be suitably used in corrosive environments, such as sour gas. The rotor and stator assemblies include NACE compliant magnetic bearing arrangements for sour gas applications. In one embodiment, a rotor shaft assembly for a magnetic bearing arrangement comprises a rotor shaft formed of a ferromagnetic material comprising a plurality of rotor laminations disposed on the rotor shaft; and a barrier layer formed on selected exposed surfaces of the rotor shaft, wherein the barrier layer is effective to resist corrosion relative to the surface without the barrier layer.

Abstract: An apparatus and method are provided for permitting free rotation of turbine nozzle vanes, while minimizing or eliminating leakage on the vane side-walls. The device incorporates a plurality of nozzle vanes arranged around the circumference of a radial or mixed inflow turbine. Each of the nozzles is individually attached to a rod positioned perpendicular to the flow direction. The nozzle rods in the circumferential array protrude through a movable annular back-wall, and are rotated by a linkage or gear. Between discrete movements of the vane mechanism, a bellows device is used to provide pressure-actuated force in the movable back-wall, thereby clamping the nozzle between the two surfaces. Prior to rotating the nozzles, pressure within the bellows interior is decreased via venting to cause a retraction of the back wall.

Abstract: A ratio of cross sectional area A of a scroll passage to a scroll radius R (A/R) can be increased without increasing the size of a turbine casing and with very simple construction. An exhaust turbine capacity can thus be increased, so that a variable-throat exhaust turbocharger in which the engine output can be increased results. The turbocharger has a nozzle throat area varying mechanism of which a nozzle assembly unit is composed. A plurality of nozzle vanes are supported rotatably by an annular nozzle mount and an annular nozzle plate is connected to the nozzle mount by a plurality of nozzle supports to sandwich the nozzle vanes. The nozzle plate is located in the scroll chamber by attaching the nozzle assembly unit to the turbine casing to allow the nozzle plate to form part of the inside sidewall face of the scroll chamber and a wall face of the annular flow passage.

Abstract: The present invention is directed to an oscillating vane machine where the vanes can be operated at high speed with a minimum of vibration and with minimum mechanical loads accomplished with sinusoidal motion of the vanes utilizing an improved continuously rotating input/output which is naturally balanced.

Abstract: A turbine unit having a rotor housing (2) having at least one admission channel (9) for a fluid, as well as a turbine rotor (4) which is supported in a turbine space (23) of the rotor housing (2) and wherein fluid is led into the turbine space (23) at its periphery through a VTG mechanism (5-8) of variable turbine geometry. The VTG mechanism (5-8) has a nozzle ring (6) having a plurality of vane shafts (8) which are arranged in the form of a crown on the nozzle ring (6) and which carry on one of their ends vanes (7) which can be moved from a substantially tangential position (relative to the crown) into a substantially radial position, as well as at least one control element (19) in order to pivot the orientation of the vanes (7).

Abstract: Exemplary vanes for a turbocharger having variable nozzle geometries are disclosed. In one aspect, each of the vanes includes two axial surfaces that are on opposite sides of the vane. The opposite axial surfaces include two corresponding chambers. These chambers are partially exposed to each other through an aperture. Such an aperture allows for some degree of equalization of the pressures in the chambers and, thereby, reduces the axial load exerted by a vane, for example, on the unison ring. In another aspect, each of the vanes includes two opposite airfoil surfaces. At least one of the airfoil surfaces includes a notch that allows a chamber in the nozzle to be pressurized by the exhaust gas. The pressure in the chamber creates a counteracting force that reduces the axial load exerted by a vane.

Abstract: A wastegated turbocharger includes a turbine wheel mounted to a shaft for rotation within a turbine housing and a compressor wheel mounted to the shaft for rotation within a compressor housing. The compressor housing has mounted thereto a wastegate actuator command valve. A secondary boost air outlet passage is disposed in fluid flow communication with the wastegate actuator command valve and the compressor outlet volute. The secondary boost air outlet passage extends into the compressor outlet volute so that an inlet opening of the passage is spaced from the surface of the compressor outlet volute.

Abstract: A diffuser is provided having a spaced apart shroud and backing plate. A diffuser vane is provided between the backing plate and shroud. The vane includes first and second sealing surfaces opposite from one another and adjacent to the backing plate and shroud. Leading and trailing surfaces are arranged opposite from one another and adjoin the first and second sealing surfaces. The first sealing surface includes a first protrusion extending therefrom approximate to the leading surface with a gap extending from the trailing surface to the first protrusion. The second surface includes a second protrusion extending therefrom proximate to the trailing surface with a second gap extending from the leading surface to the second protrusion. The surfaces provide four corners such that the protrusions are arranged on opposite corners from one another to create a pressure differential between the first and second sealing surfaces.

Abstract: A turbocharger arrangement for a variable geometry turbocharger including pivotable vanes (34) with each vane (34) having a respective vane bore (38) for receiving a vane post (28) into a vane first planar surface (80) and a respective actuation post (36) projecting outwardly from the first planar surface (80).

Abstract: A hydraulic turbine has a distributor located between the scroll of the turbine and its runner. The distributor has upper and lower stay ring portions with stay vanes extending therebetween. A plurality of movable wicket gates control flow of liquid through the distributor. The lower and upper stay ring portions have built up fish friendly projections adjacent sweep areas defined where the wicket gates sweep across the lower and upper stay ring portions. The projections also extend outwardly of the upper and lower stay ring portions adjacent the sweep areas and act as barriers preventing fish from being trapped between the wicket gates and the stay ring. Each projection has a sill portion projecting outwardly at least coextensive with, and adjacent to, one sweep area and a first apron portion extending from the sill portion to an appropriate one of the upper and lower stay ring portions.

Abstract: In a variable exhaust gas turbocharger for an internal combustion engine having an exhaust gas turbine and a compressor with a variable vane structure wherein the exhaust gas turbocharger comprises a housing and a compressor wheel which is connected to an exhaust gas turbine wheel via a shaft, the compressor has a radial inflow flow passage in which a variable vane structure or throttle device is arranged upstream of the compressor wheel and another vane structure is arranged in the radial flow passage downstream of the compressor wheel in the direction of flow.

Abstract: A variable geometry turbocharger includes vanes disposed therein having an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite and parallel to the inner airfoil surface. The vane includes first and second axial surfaces that are each positioned perpendicular to and interposed between the inner and outer airfoil surfaces. A vane leading edge is positioned along a first inner and outer airfoil surface junction, and a trailing edge is positioned along a second inner and outer airfoil surface junction. One or more of the first and second axial surfaces have a composite construction comprising a solid section that extends a distance from the leading edge towards the trailing edge, and a cored-out section that extends a distance from the trailing edge towards the leading edge.

Abstract: A guide device for an exhaust gas turbocharger has a geometry which is variable. The guide device includes guide blades, blade levers which are connected to particularly assigned guide blades in a rotationally fixed manner, and a setting ring in which the blade levers are mounted via a spring element.

Abstract: An improved design for turbines increases efficiency while reducing potential for fish kill. In an embodiment of the present invention as relates to Kaplan turbines, the gap between stay vanes and their corresponding wicket gates is reduced or eliminated by provision of an extension to the trailing edge of the stay vane. In alternative embodiments, the extension may be added to the wicket gate or affixed to both in an arrangement that permits free movement of the wicket gate. To facilitate eliminating the gap altogether, the extension may be made of a pliable material or be fabricated in a telescoping or accordion arrangement to permit contact with opposing parts without damage thereto. By designing extensions using accepted hydraulic principles, a better fit of the stay vane to its associated wicket gate, and possibly to the turbines runners may be effected, further improving operational efficiency and possibly even extending maintenance intervals.

Abstract: In an exhaust gas turbocharger for an internal combustion engine comprising a radial flow exhaust gas turbine and a compressor, which is connected to the turbine via a shaft, the turbine having a radial inflow duct and a radial inlet flow passage, which leads to the turbine wheel and in which a variable geometry vane structure for changing the cross-section of the radial inlet flow passage is supported between two support walls fixed to the turbine casing, one of the support walls projects into the inflow duct, in such a manner that the rear side of this support wall is spaced from the inner wall of the inflow duct wall so that the exhaust gas within the inflow duct is in contact also with the rear side of this support wall.

Abstract: Improved cambered vanes comprise an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. A cambered vane leading edge or nose is positioned along a first inner and outer airfoil surface junction, and a vane trailing edge positioned along a second inner and outer surface junction. The vane airfoil surfaces, in conjunction with the vane leading edge, are specifically configured to provide a vane camberline, measured between the airfoil surfaces and extending along a length of the vane, having a gradually curved section and a substantially flat section.

Abstract: Exemplary turbine blade outer edges, exemplary vane inner edges, exemplary systems and exemplary methods are disclosed that help to reduce noise in variable geometry turbines and optionally other turbines wherein a turbine blade interacts with an object. Other exemplary turbine-related technologies are also disclosed.

Abstract: A guiding grid of variable geometry comprises a plurality of guiding vanes in a housing in angular distances around a central axis in an axially extending vane space of a predetermined axial distance. Each vane is pivotal about an associated pivoting axis to assume different angles in relation to the central axis and, thus, to form a nozzle of variable cross-section between each pair of adjacent vanes. A nozzle ring supports the vanes around the central axis and forms a first axial limitation of the vane space. A unison ring is displaceable relative to the nozzle ring and is connected to the vanes to pivot them. An annular disk is fixed to the housing and faces the nozzle ring in an axial distance to form a second axial limitation of the vane space and a central opening. Into this opening, a sleeve may be inserted. A fixing arrangement determines the axial position of the annular disk with respect to the housing.

Abstract: Improved cambered vanes comprise an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. A cambered vane leading edge or nose is positioned along a first inner and outer airfoil surface junction, and a vane trailing edge positioned along a second inner and outer surface junction. The vane airfoil surfaces, in conjunction with the vane leading edge, are specifically configured to provide a vane camberline, measured between the airfoil surfaces and extending along a length of the vane, having a gradually curved section and a substantially flat section.

Abstract: A manufacturing method for manufacturing a component part for a variable capacity turbine, and the structure of a nozzle driving member, will simplify the structure of the component parts for the adjustable nozzle mechanism, the manufacturing work, which results in lowering the manufacturing count and cost as well as the number of component parts, and in lightening the weight of the variable capacity turbine. In order to manufacture the component parts for a radial-flow variable capacity turbine, in which actuating gas is forced to flow from a spiral scroll formed in a turbine casing to a turbine rotor in a radial direction through multiple nozzle vanes, of which the angle is adjustable by an adjustable nozzle mechanism, for rotating a turbine rotor, this manufacturing method has a column shaped connecting pin formed as a single structure with a plate member by pressing, or by precision molding by partially forcing the surface of the plate member to protrude in a column shape.

Abstract: A support pin (24) is disposed at a position in front of a front edge (19a) of a movable nozzle blade (19) in a state in which the movable nozzle blade (19) is located at a rating opening position B, set between a maximum opening position A and a minimum opening position C. The aerodynamic effect of the support pin when the flow rate is small is thus reduced, and the turbine efficiency when the flow rate is small is enhanced.

Abstract: Variable geometry turbochargers include a turbine housing having an exhaust gas inlet and outlet, a volute connected to the inlet, and typically a nozzle wall adjacent the volute. The turbine housing includes a bypass exhaust gas flow port disposed internally therein having an inlet opening positioned upstream from the turbine wheel, and a outlet opening positioned downstream from the turbine wheel. The inlet opening is exposed for facilitating bypass exhaust gas flow through the turbocharger when a respective vane is actuated or moved into an open position. The turbine housing may also include a specially configured nozzle wall terminal edge designed to work with vanes having a recessed underside surface to permit additional bypass exhaust gas flow within the turbocharger when the vanes are actuated in an open position.

Abstract: Improved cambered vanes are constructed for use within a vaned turbocharger and comprise an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. A cambered vane leading edge or nose is positioned along a first inner and outer airfoil surface junction, and a vane trailing edge positioned along a second inner and outer surface junction. The vane inner and outer airfoil surfaces, in conjunction with the vane leading edge, are specifically configured to provide a vane camberline, measured between the airfoil surfaces and extending along a length of the vane, that has a gradually curved section and a substantially flat section.

Abstract: Improved cambered vanes of this invention are constructed for use within a vaned turbocharger and comprise an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. A cambered vane leading edge or nose is positioned along a first inner and outer airfoil surface junction, and a vane trailing edge positioned along a second inner and outer surface junction. The vane inner and outer airfoil surfaces, in conjunction with the vane leading edge, are specially configured to provide a vane camberline, measured between the airfoil surfaces and extending along a length of the vane, that has a gradually curved section and a substantially flat section.

Abstract: Improved vanes of this invention are constructed for use within a variable geometry turbocharger assembly. Each vane comprises an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. Each vane includes a leading edge positioned along a first inner and outer airfoil surface junction, a trailing edge positioned along a second inner and outer surface junction, a hole disposed within a first axial vane surface substantially parallel to an outer nozzle wall for receiving a respective post therein, and an actuation tab extending from a second axial vane surface opposite from the first vane surface. A key feature of improved vanes of this invention is that they have an airfoil thickness that is greater than 0.16 times a length of the vane as measured between the vane leading and trailing edges.

Abstract: A guide blade-adjusting device for a turbocharger has an adjusting ring that is guided in a simple manner on the guide blade carrier plate. The adjusting ring comprises noses projecting in the axial direction. At least one the noses radially guides the adjusting ring on the guide blade carrier plate.