Abstract: Various methods and systems are provided for an open vane nozzle for a turbine. In one example, the turbine may include at least one bias device arranged at an interface between a nozzle ring and a turbine shroud. The at least one bias device may be configured to exert an axial force on the nozzle ring to maintain contact between vane tips of the nozzle ring and a volute wall.

Abstract: A turbocharger includes a turbine housing accommodating a turbine wheel, a bearing housing rotatably supporting a rotating shaft to which the turbine wheel is fixed, a variable geometry mechanism accommodated in the turbine housing, surrounding the turbine wheel, and configured to guide a fluid to the turbine wheel, and a spring member held by the variable geometry mechanism and the bearing housing in an axial direction along the rotating shaft. The variable geometry mechanism has an inner circumferential portion surrounding a through hole in which the turbine wheel or the rotating shaft is disposed, and an outer circumferential portion located between the spring member and the turbine housing. The outer circumferential portion is distanced further away from a rotational axis of the rotating shaft than the inner circumferential portion. The outer circumferential portion includes a first end face contacting the spring member, and a second end face contacting the turbine housing.

Abstract: An adjustment lever adjusts a stator vane of a turbomachine. The adjustment lever has: a first connection site, of a plurality of connection sites, the first connection site being configured to join to an adjustment ring; a second connection site, of the connection sites, the second connection stie being configured to join to the stator vane; and a joining member arranged between the first connection site and the second connection site. The joining member is shaped having at least two struts which adjoin at least one of the connection sites.

Abstract: A variable geometry turbine includes: a turbine rotor; a scroll passage forming part which forms a scroll passage; an exhaust gas passage forming part which forms an exhaust gas passage for introducing an exhaust gas from the scroll passage to the turbine rotor; and a variable nozzle unit including a plurality of nozzle vanes disposed in the exhaust gas passage and configured to be rotatable about respective rotation centers. The exhaust gas passage forming part includes: a first plate member having an annular first plate part; and a second plate member having an annular second plate part which defines the exhaust gas passage between the first plate part and the second plate part and is disposed closer to a turbine outlet than the first plate part in an axial direction of the turbine rotor.

Abstract: A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment plate. The adjustment plate includes a main plate portion arranged on the ring and including a first adjustment region defined between two walls and a first elongated opening formed through the first adjustment region, and an adjustment fastener removably arranged in the first adjustment region between the first and second walls and including an adjustment head and a fastening pin eccentrically coupled to the adjustment head and removably coupled to the annular ring. The adjustment fastener can be selectively arranged at rotational positions within the first adjustment region so as to selectively arrange the fastening pin at distinct circumferential positions relative to the first and second walls such that the main plate portion can be positioned at distinct circumferential positions.

Abstract: A system and method for improving efficiency of vertical axis wind turbines for all wind directions, comprising an inlet convergent section, a wind turbine section adjacent to exit of convergent section and an outlet divergent section. The system provides an air passage through the inlet section, the wind turbine and the outlet section, and allows for variation of the inlet and outlet depending on wind direction, in order to maximize efficiency harnessed within a time interval in accordance to wind direction and wind speed.

Abstract: A variable mechanical automotive coolant pump includes a rotatable rotor shaft, an impeller wheel which is co-rotatably connected with the rotor shaft, a static guiding cylinder, a control sleeve, and at least one guiding device. The impeller wheel has a discharging radial outside. The control sleeve has a hollow-cylindrical control sleeve body having a radial outside. The control sleeve does not rotate and is guided axially slidable within the static guiding cylinder so as to regulate a flow rate of the variable mechanical automotive coolant pump by closing or opening the discharging radial outside of the impeller wheel. The at least one guiding device guides the radial outside of the control sleeve within the static guiding cylinder.

Abstract: An entryway system includes a divided volute turbocharger having variable turbine geometry (VTG). The turbocharger includes a turbine housing, first and second volutes separated by a wall having a first and second tongue, and a turbine housing outlet. The system also includes a turbine wheel disposed in the turbine housing and a vane ring disposed in the turbine housing between the turbine wheel and the volutes. The system includes design modifications of one or more of the VTG components and/or locations of such components to manipulate the aerodynamic forces and/or subsequent mechanical loads in the VTG mechanism of the entryway system to mitigate VTG component wear during normal usage.

Abstract: A turbine housing for an exhaust turbocharger is configured for receiving a turbine wheel rotatable about an axis. The housing includes an exhaust gas inlet, an exhaust gas outlet pointing in an outlet direction, and a single-flow, spiral exhaust gas routing. The routing has a volute and a volute outlet gap configured so that exhaust gas flows from the volute to the wheel. The routing is fluidically connected to the inlet and is defined by an internal wall of the housing. The volute has a portion which encircles the axis and has a convexity of the internal wall. The convexity, counter to the outlet direction, extends beyond the volute outlet gap. Further, sectional faces, through which the axis runs, each have a volute contour with a straight linear portion. The linear portion, conjointly with the axis, defines an angle facing the outlet that is less than or equal to 90°.

Abstract: A method and system are provided for repairing a nozzle ring having a defect adjacent a transition between a ring plate and an inner skirt of the nozzle ring, comprising: forming at least one cut to detach at least one of a portion of the inner skirt, a portion of the transition, and a portion of the ring plate, thereby forming a joint surface and removing at least a portion of the defect; providing a replacement ring including replacement components for the detached at least one of a portion of the inner skirt, a portion of the transition, and a portion of the ring plate; and attaching the replacement ring to the nozzle ring at the joint surface using one of brazing or welding.

Abstract: A variable nozzle device includes: a nozzle mount; a plurality of nozzle vanes; a drive ring being having a plurality of receiving portions disposed at different positions along a circumferential direction; and a plurality of lever plates each having a fixed portion to be fixed to corresponding one of the plurality of nozzle vanes and an engaging portion to be engaged with corresponding one of the plurality of receiving portions of the drive ring. The receiving portions include a first-side guide surface and a second-side guide surface. The engaging portions each include a first-side roll surface which is to be in contact with the first-side guide surface and a second-side roll surface which is to be in contact with the second-side guide surface. The first-side roll surface includes a lever-plate-side linear portion extending linearly in at least a part of a range which is to be in contact with the first-side guide surface.

Abstract: A nozzle device according to some embodiments includes an annular nozzle plate, an annular nozzle mount defining a nozzle flow passage between the nozzle mount and one surface of the nozzle plate, at least one nozzle support coupling the nozzle plate and the nozzle mount, and fixed to at least the nozzle plate by caulking, and at least one nozzle vane supported between the nozzle plate and the nozzle mount. The nozzle plate has a through hole into which an end portion of the at least one nozzle support is inserted.

Abstract: An annular disk comprises a front surface, a rear surface, an outer surface, and an inner surface. The front surface has a front opening within a front plane. The rear surface has a rear opening within a rear plane. The rear opening, which has a diameter that is smaller than a diameter of the front opening, communicates with the front opening to define a bore for guiding an exhaust stream flowing from a turbocharger to an exhaust outlet. The outer surface connects the front surface to the rear surface and includes an outer angled portion, an outer radial portion, and an outer axial portion. The inner surface includes an inner angled portion, an inner axial portion, and an inner radial portion extending between the inner angled portion and the inner axial portion. The inner radial portion is configured to obstruct a portion of the exhaust stream to increase back pressure.

Abstract: A reversible pump-turbine and also a guide vane for a reversible pump-turbine with a guide vane body, a pivot for rotating the guide vane body around an axis of rotation and two end faces. The guide vane body has a turbine leading edge facing the turbine flow and a turbine trailing edge facing away from the turbine flow, where the individual guide vanes come into contact with one another along closing edges when the wicket gate is closed, where the guide vanes each have two flow-guiding surfaces on either side of the axis of rotation and opposite one another that are limited by the two end faces. These two flow-guiding surfaces have different flow profiles.

Abstract: A startup method of a Francis turbine according to an embodiment includes: a bypass-valve opening step of opening the bypass valve with the inlet valve closed; an inlet-valve opening step of opening the inlet valve after the bypass-valve opening step; and a first rotation-speed increasing step of increasing a rotation speed of the runner by opening the guide vane at an opening that is 50% or more of a maximum opening before a flow velocity of a swirling flow flowing around the runner reaches 90 m/sec.

Abstract: The invention relates to a distributor for a turbomachine radial turbine, comprising an annular grill (26) extending about a central axis (10) and comprising a plurality of variable-pitch blades (31), defining between them an air passage cross section, characterized in that each blade is rotatably mounted about a pivot shaft (32), itself moveable in a translation direction, comprising at least one radial component, such that said blade may, upon actuation of control means (40), be pivoted about the pivot shaft and/or moved in relation to the central axis in said translation direction so as to be able to modify the air passage cross section by respectively controlling the metal angle (?3) and the radial spacing (?R).

Abstract: A compressor has a rotor. The rotor includes a plurality of impellers that include a disk having a solid structure having a buried center, and are adjacent to each other in an axial direction, and a plurality of bolts for fixing the plurality of impellers together. The disk has a disk surface facing the axial direction and a bolt hole penetrating the disk at a position deviated outward from an axis in a radial direction. The disk surface includes a contact surface of which at least a part is located outside the bolt hole in the radial direction, and a non-contact surface which is a region inside the contact surface in the radial direction.

Abstract: A startup method of a Francis turbine according to an embodiment includes: a first rotation-speed increasing step in which a rotation speed of the runner is increased by opening the guide vane at a first opening; a second rotation-speed increasing step in which the increase in the rotation speed of the runner is accelerated by opening the guide vane at a second opening that is larger than the first opening after the first rotation-speed increasing step; and a rotation-speed regulating step in which the rotation speed of the runner is regulated to a rated rotation speed by opening the guide vane at a no-load opening after the second rotation-speed increasing step. The first opening is an opening that is half or less than the no-load opening.

Abstract: The invention relates to a sprayer of the type comprising a turbine that generates an air current, a nozzle that channels the air current and an outlet of this current to the outside, carrying with it the product dosed by a series of nozzles arranged in the area of influence of the air current, the sprayer being special in that both the air outlet opening and the turbine can be configured and act in a coordinated manner to obtain the desired air flow for each type of crop and spray application, where the optimum air flow for each spray application and the configuration of the turbine and opening are determined by the actual sprayer by means of a processor and auxiliary means.

Abstract: A vane assembly includes a fixed airfoil portion that extends between a radially inner platform and radially outer platform and has a pressure side and a suction side. A rotatable airfoil portion is located aft of the fixed airfoil portion and has a pressure side and a suction side. A cover extends from the pressure side of the fixed airfoil portion to the pressure side of the rotatable airfoil portion.

Abstract: A turbocharger or turbocharger component is disclosed herein. The turbocharger or turbocharger component may comprise an annular unison ring, and a first nozzle ring having an annular groove. The annular unison ring may be rotatably disposed in the annular groove. A partial circular recess may be disposed in an outer annular nozzle ring surface of the first nozzle ring adjacent to the annular groove. A unison crank having a circular body may be rotatably disposed in the partial circular recess. A plurality of vane assemblies may be rotatably disposed in a respective vane aperture within the first nozzle ring.

Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.

Abstract: A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud.

Abstract: An exhaust-gas turbocharger for an internal combustion engine includes an intake duct for air, an exhaust-gas duct, a turbine arranged in the exhaust-gas duct, and a compressor impeller arranged in the intake duct, which turbine and compressor impeller are both arranged on a common shaft, wherein the exhaust-gas duct has a spiral housing which coaxially surrounds the turbine, and wherein, between the spiral housing and the turbine, a ring-shaped gap is provided through which the exhaust-gas flow flows circumferentially to the turbine, and wherein, in the ring-shaped gap, guide vanes are arranged which are rotatable about an adjustment axis by an adjustment mechanism for controlling the flow resistance. To compensate thermal expansions and shrinkages of the guide vanes under different operating conditions, the adjustment mechanism additionally has a displacement mechanism for displacing the guide vanes in the ring-shaped gap. The displacement mechanism is directly coupled to the adjustment mechanism.

Abstract: Provided is a nozzle drive mechanism, including: a bearing having a bearing hole; a drive shaft which is axially supported in the bearing hole so as to be rotatable; a drive lever including: an insertion portion into which another end portion (end portion) of the drive shaft protruding from the bearing hole is inserted; and a coupling portion, which is positioned on the bearing side with respect to a center of the drive shaft in an axial direction, and projects outward in a radial direction of the drive shaft from the insertion portion; a link pin coupled to the coupling portion; and a rod member, which is connected to the link pin, is positioned on a side opposite to the bearing with respect to the coupling portion, and is provided to an actuator.

Abstract: A turbocharger can include a center housing; a bearing disposed in a through bore of the center housing where the through bore of the center housing defines a longitudinal axis; a shaft rotatably supported by the bearing; a compressor wheel operatively coupled to the shaft; a turbine wheel operatively coupled to the shaft; and a turbine housing assembly operatively coupled to the center housing where the turbine housing assembly includes: a turbine housing; and a cartridge that includes a nozzle wall component and a plate component that are spaced axially by spacers, where the nozzle wall component includes spacer bores for the spacers and where the nozzle wall component has a non-circular outer perimeter defined at least in part by arcs where adjacent arcs intersect at intersection points, and where each of the intersection points is radially outwardly from a respective one of the spacer bores.

Abstract: There is provided a variable nozzle mechanism that can suppress wear. The variable nozzle mechanism includes a plurality of nozzle vanes, a plurality of arms, and a unison ring. The plurality of nozzle vanes are provided in the nozzle path. The plurality of arms each have a pivoted end and a free end, and the pivoted end is integrally coupled with the nozzle vane by means of a pivot. The unison ring is provided with a plurality of grooves. Each groove is engaged with the respective free end of the arm. The free end of the arm has a closing-side contact surface and an opening-side contact surface each in contact with a respective one of paired walls forming the groove of the unison ring. The closing-side contact surface has a curvature different between a side closer to the pivot and a side farther away from the pivot.

Abstract: A variable turbine geometry turbine turbocharger (1) includes a vane ring assembly (29) configured to control flow of exhaust gas to a turbine wheel (12), and retainers (60, 160) that are used to secure the vane ring assembly (29) to the bearing housing (16) in a desired axial and radial position and angular orientation relative to the bearing housing (16). In some embodiments, the vane ring assembly (29) is spring biased toward an axially outward position relative to the bearing housing (16), and the retainers (60, 160) retain the vane (30) ring in the desired position against the spring bias.

Abstract: The present invention discloses a wind power generation tower. The wind power generation tower, according to various embodiments of the present invention, comprises: a wind collection unit and an energy conversion unit, wherein wind power generation can be implemented by accelerating wind speed even for low speed wind and simultaneously increasing the utilization efficiency of the wind which rotates blades, thereby improving overall power generation efficiency.

Abstract: A turbine for a supercharging device of an internal combustion engine may include a turbine wheel which is rotatably arranged about an axis of rotation in a turbine housing. A radial inflow channel may be arranged coaxially to the turbine wheel, which leads to a radial inlet region of the turbine wheel. The inflow channel may be axially bounded on one side by a blade carrier and axially bounded on the other side by a cover disc. A plurality of guide blades may be pivotably arranged on the blade carrier, and a plurality of spacer elements may axially project from the blade carrier. An axial outflow channel may be arranged coaxially to the turbine wheel, which leads from the inlet region to an axial outlet region of the turbine wheel, which may be radially bounded by an inner contour formed complementary to an outer contour of the rotating turbine wheel.

Abstract: A turbocharger (10) includes a housing (12, 14, 16) and an actuating mechanism (46) for actuating a device (40) within the housing (12, 14, 16). A pivot shaft (42) has an inside end (48) inside the housing (12, 14, 16) and an outside end (82) outside the housing (12, 14, 16). The pivot shaft (42) is rotatably mounted in a bore (64) in the housing (12, 14, 16) for transmitting an actuating movement from outside the housing (12, 14, 16) to the actuating mechanism (46). A bushing (62) is disposed in the bore (64). The bushing (62) includes an asymmetric portion (68) that extends inside the housing (12, 14, 16) to support the inside end (48) of the pivot shaft (42).

Abstract: A vertical axis wind and hydraulic turbine with flow control including a regular hexagonal structure of radius R, parallelepiped-shaped, inside which a rotor rotates with three or more vanes on a vertical axis which is located in the center of the hexagon as seen from above, wherein the vanes when rotating generate a circle of radius Rt, further including six articulated deflector vanes that grab and concentrate the flow of air or liquid entering the rotor vanes, from the wind or liquid current entry side to the turbine and diffuse the flow of air or liquid exiting from the rotor vanes, from the side opposite to the wind or liquid entry side to the turbine.

Abstract: In a variable geometry turbocharger including a variable nozzle mechanism, an object is to enhance safety upon malfunction of the variable nozzle mechanism as well as to improve accuracy in the control of the variable nozzle mechanism by applying a moment that acts on the nozzle vanes in an opening direction securely and stably.

Abstract: A turbine nozzle for an air cycle machine includes a disk having a central axis and a plurality of airfoils extending from a surface of the disk. The plurality of airfoils is arranged radially about the disk section to direct a flow of a fluid passing thereby. A relief cut adjacent the airfoils, wherein the relief cut provides a channel in a least a portion of the surface of the disk.

Abstract: An asymmetric double-entry turbine is provided with a turbine housing that includes a first volute, a second volute and a turbine receiving bore. The first volute has a first exhaust gas inlet and a first exhaust gas outlet. The second volute has a second exhaust gas inlet and a second exhaust gas outlet. The turbine receiving bore is in fluid communication with the first exhaust gas outlet and the second exhaust gas outlet for conducting a flow of exhaust gas from the first exhaust gas outlet and the second exhaust gas outlet out in an axial direction. The first exhaust gas outlet has an angular opening amount of more than 180 degrees around the turbine receiving bore. The second exhaust gas outlet has an angular opening amount of less than 180 degrees around the turbine receiving bore.

Abstract: A turbocharger including a turbine housing including a gas inlet passage and a turbine wheel arranged in the turbine housing. A bearing housing is connected to the turbine housing. A nozzle ring is disposed around the turbine wheel and a shroud is arranged in surrounding relation to at least a portion of the turbine wheel. The shroud is connected to the nozzle ring and the nozzle ring and shroud are connected to a heat shield. The heat shield is secured to the bearing housing by a plurality of cross key pins, each cross key pin being inserted in a radially extending first passage in the heat shield and a complementary radially extending second passage in the bearing housing. The first passages and second passages are symmetrically arranged in a circular pattern about a rotational axis of the turbine.

Abstract: A variable geometry system turbocharger includes a variable nozzle unit, which is disposed in a turbine housing by being sandwiched between the turbine housing and a bearing housing, and which adjusts a passage area for the exhaust gas to be supplied to a turbine impeller. The bearing housing includes a container recessed portion which contains a link mechanism of the variable nozzle unit.

Abstract: A supercharged internal combustion engine may include a twin-flow turbine with variable vane geometry. One example method to operate the device permits optimized operation of the internal combustion engine at low exhaust gas flow rates.

Abstract: A cover plate for use in a cabin air compressor is a generally cylindrical body with 19 holes extending through the body and an inner bore defining an inner diameter centered on a center axis. The body has a thickness in a dimension measured perpendicular to the central axis. The inner diameter is 14.840 inches (37.693 centimeters) plus/minus .005 inch (0.013 centimeter). A diffusor housing, a cabin air compressor and a method of replacing a cover plate are also disclosed.

Abstract: The propensity for gas and soot leakage around a shaft, which extends through a bore which connects volumes of differing pressures, e.g., a turbocharger turbine housing and the ambient air, is minimized with the addition of a pair of seal rings axially biased by a spring to provide a continuous gas and soot seal. The spring may bias the seal rings apart from each other or towards each other.

Abstract: A solar-energy heat power-generating system and thermoelectric conversion device thereof, the thermoelectric conversion device comprising a power generator (5), an air compressor, a turbine and an intermediate body (12) fixedly connected between the air compressor and the turbine; the interior of the intermediate body (12) is rotatably connected to a transmission shaft (28); the transmission shaft (28) is fixedly connected to the rotating shaft of the power generator (5); the air compressor impeller (7) of the air compressor and the turbine impeller (18) of the turbine are both installed on the transmission shaft (28); the power generator (5) is also connected to a conducting wire (3) for inputting current; the solar-energy heat power-generating system comprises a heat collector and the thermoelectric conversion device; the air compressor of the thermoelectric conversion device is located upstream of the heat collector, and the turbine is located downstream of the heat collector.

Abstract: A turbine housing includes an outer housing member, which has a proximal housing portion and a distal housing portion, and an inner housing member, which is provided inside the outer housing member and has a shroud surface that faces a turbine wheel in an axial direction. A distal portion of the inner housing member serves as a slide portion slidable in the axial direction. Further, a proximal portion of the inner housing member is fixed to the proximal housing portion at a part closer to a distal side than a proximal portion of the proximal housing portion. Further, a scroll portion is formed by the inner housing member and a proximal scroll portion of the proximal housing portion located closer to a proximal side than the inner housing member.

Abstract: A bearing arrangement for supporting a shaft in a turbocharger housing. The bearing arrangement includes a sleeve element and the sleeve element is formed with a flange section at each end for fastening the bearing arrangement in the turbocharger housing.

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 (8) 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 bearing arrangement (28) for fixing the adjusting ring (5) to the blade bearing ring (6), wherein the bearing arrangement (28) is formed as a plain bearing ar

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 variable-vane assembly for a turbocharger includes 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 an annular retainer ring disposed radially outward of the nozzle ring and extending generally radially inwardly. The nozzle ring's face is stepped, and a radially inner edge of the retainer ring engages the face of the nozzle ring radially outward of the step, the radially inner edge of the retainer ring having an axial thickness that is less than the step height such that a remaining portion of the step is presented to the exhaust gas flowing through the nozzle.

Abstract: A securing element includes a head section and a shank. The cross-section of the shank changes in the axial direction in such a way that, by taking into account a qualitative and/or quantitative predetermined bending torque profile in the shank, the cross-section has a substantially uniform bending stress profile in the shank in relation to a securing element with a constant shank cross-section. An exhaust gas turbocharger having variable turbine geometry includes a VTG-guide vane configuration having at least one such securing element and being secured to a housing component of the exhaust gas turbocharger.

Abstract: A turbocharger (15) with variable turbine geometry having a blade bearing ring arrangement (1) which has a blade bearing ring (2) and a disk (3) which can be fixed to the blade bearing ring (2) to form a flow duct (4); having a spacer device (5) which is arranged between the blade bearing ring (2) and the disk (3) to set a defined width (B) of the flow duct (4), wherein the spacer device (5) is designed as a guide ring (6) which has spacer profiles (7) whose height (H) corresponds to the width (B) of the flow duct (4).

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 can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. The vanes extend between the nozzle ring and an opposite wall of the nozzle. An axially floating vane sealing ring is disposed in an annular recess formed in the face of the nozzle ring adjacent proximal ends of the vanes. The vane sealing ring is urged by exhaust gas pressure differential toward the proximal ends of the vanes, and the vanes are thus urged toward the opposite nozzle wall so that distal ends of the vanes are close to or abutting the wall, resulting in a reduction or closing of the gaps at the proximal and distal ends of the vanes.

Abstract: A supercharger device, including, at least one of a variable turbine and a compressor geometry; a guide vane device arranged in a housing, wherein the guide vane device includes at least one vane mounting ring; at least one guide vane is at least one of rotatably mounted thereon the vane mounting ring and rotatably mounted therein the vane mounting ring; and an adjusting ring arranged coaxially to the vane mounting ring and mounted on the latter, which is rotated relative to the vane mounting ring.