Abstract: The invention relates to a unit comprising a hydraulic turbine (1), a duct (5) leading a forced flow of water to the turbine, a duct (8) discharging the outgoing flow from the turbine and vanes (20) for guiding the flow through the discharge duct. Each guide vane (20) is able to rotate about an axis (x22) secant to the wall (84) of the discharge duct. Means (30) are provided for controlling the angular position of the vane (20) about its axis of rotation (x22). Each guide vane (20) can also be retracted into the wall (84) of the discharge duct (8), and means (21) are provided for adjusting the extent to which they are withdrawn into the wall.

Abstract: Several physical features on an inlet guide vane (IGV) ensure proper orientation of the IGV within a compressor during assembly. A gear with several teeth removed results in a flat surface on the gear which inhibits the gear from rotating on the rack of the compressor inlet casing. An orientation pin is located in the internal bore of the gear. The cylindrical IGV spindle has a portion formed as a flat surface and the orientation pin engages this flat surface. These features are applicable to both a one-piece IGV where the jackshaft is integrated with the IGV stem and a two-piece IGV in which the jackshaft is separate from the IGV stem. A feature applicable to a two-piece IGV is a shaped boss on the IGV stem that allows the jackshaft to be located on the IGV stem in only one orientation.

Abstract: A turbine engine locates an actuator (55) for the compressor variable guide vanes (54a, b, c) at a location remote from the variable guide vanes. The actuator is connected to the variable guide vanes through a torque rod (56) inside an inlet guide vane. The torque rod rotatably drives an activation ring (57) about the engine centerline. The activation ring is coupled to each of the variable compressor vanes via linkage, such that rotation of the activation ring about the engine centerline causes all of the variable compressor vanes to pivot. With this configuration, a tip turbine engine can be more easily provided with variable compressor vanes for the axial compressor.

Abstract: A Pelton turbine is disclosed that includes at least one needle valve injector assembly and at least one high efficiency injector assembly. The high efficiency injector assembly provides a generally unimpeded flow path for water from a distributor to a runner of the turbine. The high efficiency injector assemblies and needle valve injector assemblies are operated in cooperation to provide the overall desired flow rate through the turbine and to increase the efficiency of the turbine. A high efficiency injector assembly may be retrofitted for a needle valve injector assembly to improve the efficiency of existing turbine systems.

Abstract: A variable geometry turbine of the kind used in a turbocharger has a variable geometry element such as a nozzle ring that is operated by an actuator. The actuator comprises a motor which drives a cross-shaft in rotation. The cross-shaft in turn drives a pair of guide rods on which the nozzle ring is supported in translation so as to move the nozzle ring and control the width of the inlet passage of the turbine. The cross-shaft and guide rods are drivingly engaged by a rack and pinion or thread or another toothed or threaded formation suitable for converting rotational movement into translational movement. The cross-shaft can be located in close proximity to the guide rods and the output of the motor shaft so as to provide a compact package. Moreover, the torque required to resist movement of the nozzle ring in operation is much reduced in comparison to existing designs.

Abstract: A method for operating a gas turbine engine system under baseload and/or a high part load conditions is disclosed, the gas turbine engine system includes a gas turbine engine with at least one compressor with at least one row of adjustable variable vanes for control of the inlet air mass flow; at least one combustor; at least one turbine. A control system is provided, which, on the basis of and as a function of at least one measured temperature value measured upstream of the compressor or a measurable quantity directly functionally related thereto, controls the position of the variable vanes such that at least one measured pressure value varying with the angular position of the variable vanes is at a predefined target pressure which is a function of said first temperature.

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

Abstract: A load absorption arrangement 40 for absorbing loads in a variable stator vane positioning system of a gas turbine engine includes a valve 42 which has a first operating condition to enable the load absorption arrangement 40 to transmit load, and a second operating condition, which is operable above a predetermined load, in which the valve 42 can release to enable the load absorption arrangement 40 to absorb the load thereon. The arrangement 40 is particularly suitable for absorbing shock loads which may arise under engine surge.

Abstract: A compressor has an impeller and an inlet delivering air to the impeller. A variable diffuser is positioned downstream of the impeller and includes a plurality of pivoting vanes. A drive arrangement pivots the vanes, and includes an electric motor causing a pinion gear to rotate. The pinion gear has gear teeth engaging gear teeth on a rack section. Rotation of the rack section causes the vanes to pivot.

Abstract: A gas-turbine engine includes stator vanes (1) angularly variable about their longitudinal axes by actuating elements in order to control airflow supplied to downstream rotor blades (6). The actuating elements are arranged in the most confined downstream stages of the compressors and/or turbines, with these stages being exposed to high temperatures, so that stable and efficient operation is ensured. The actuating elements (8) fixed to the inner or the outer casing (4, 12) are made of a material expanding, contracting or deforming in dependence of the temperature and transmit the respective deformation to the swivellably borne stator vanes (1).

Abstract: Control device of variable pitch vanes in a turbomachine, including a ring (14) surrounding a casing (10) of the turbomachine and connected by links to the variable pitch vanes, and a jack (16) connected to the ring in order to displace it in rotation around the casing, the jack being mounted pivoting on the casing and its piston rod (18) being connected to the ring by a connecting rod (24), the piston and connecting rods being articulated on an axis (20) which is connected to the casing by guiding means (33) maintaining it at a substantially constant distance from the casing.

Abstract: The present invention is directed to a turbine comprising a plurality of blades that rotate in a single direction when exposed to fluid flow, wherein the plurality of blades are joined to the central shaft by a plurality of radial spokes disposed substantially perpendicular to the central shaft such that the rotating plurality of blades causes the shaft to rotate. The plurality of blades has a uniform airfoil-shaped cross section, where the airfoil cross section presents a non-zero angle of attack to the current. The plurality of blades wind in a spiral trajectory, rotating around the central shaft and having a variable radius along the length of the central shaft such that a distance measured from the plurality of blades to the center shaft is greater near the center of the turbine than at either end.

Abstract: A turbocharger of variable turbine geometry, comprising: a vane bearing ring assembly including a vane bearing ring and a disk which can be fixed to the vane bearing ring for creating a flow channel; and at least one support pin which is connected with a first end to the vane bearing ring and which is welded with a second end to the disk which comprises recesses for the support pin end to be welded, the recesses being surrounded by a heat throttle.

Abstract: An exemplary controller includes a control valve that includes an electric actuator operatively coupled to a valve stem, a piston operatively coupled to one or more hydraulic fluid paths controlled by the control valve and including a piston shaft, a rotatable shaft operatively coupled to the piston shaft and mechanically isolated from the valve stem and capable of adjusting geometry of the variable geometry turbine, and an electronic sensor capable of sensing an angular position of the rotatable shaft. Various other exemplary systems, methods, devices, etc., are also disclosed.

Abstract: A diffuser includes multiple vanes rotatable about pivot pins between multiple positions. A mounting plate supports a backing plate. The vanes are arranged between the backing plate and the shroud. The pivot pins are in a slip fit relationship with the backing plate, vanes and shroud and are threadingly received by bosses in the mounting plate. The mounting plate and pivot pin arrangement better enables the backing plate and shroud to remain parallel with one another during deflection of the backing plate and/or shroud. Structure, such as integral protrusions and/or bolts, extend from between the backing plate and shroud through apertures in the vanes to better contain the vanes in the event of a catastrophic failure.

Abstract: Centrifugal compressor flow stabilizing devices and methods of operation thereof are disclosed that act upon the flow field discharging from the impeller of a centrifugal compressor and modify the flow field ahead of the diffuser vanes such that flow conditions contributing to rotating stall and surge are reduced or even eliminated. In some embodiments, shaped rods and methods of operation thereof are disclosed, whereas in other embodiments reverse-tangent air injection devices and methods are disclosed.

Abstract: A variable nozzle device comprises a wall member 10, a unison ring 12, and a plurality of vanes 1 rotatable about a pivot axle 8 by the unison ring 12. Each vane 1 has a tab member 9 comprising a shaft portion 6 and a tab portion 5 for holding the vanes 1 on the wall member. The nozzle device further comprises an insert 11 for supporting the vanes 1 rotatably about said pivot axle 8.

Abstract: A fluid flow engine comprises: a turbine housing including at least one supply channel for supplying a driving fluid; at least one turbine rotor rotatably supported in the turbine housing about an axis of rotation; and a guiding grid of variable turbine geometry radially outside and surrounding the turbine rotor. The guiding grid comprises a nozzle ring forming one end limitation of a vane space and a plurality of guiding vanes each being pivoted about a pivoting axis and being supported by the nozzle ring so as to supply an adjustable amount of fluid from the supply channel to the turbine rotor. At least one spacer is connected to the nozzle ring for securing an axial distance for enabling the vanes to wove freely. The spacer includes at least one bolt or pin tat penetrates into the nozzle ring.

Abstract: A multi-modal forced vortex device is described having a top plate and a side wall creating a partially enclosed volume. The top plate includes one or more adjustable fluid openings to permit, or restrict, fluid flow into and out of the partially enclosed volume. Rotating blades housed within the partially enclosed volume are manipulated (through control of their pitch and, possibly, their speed) in conjunction with the adjustable fluid openings to generate a variable magnitude attractive force in a first mode, a variable magnitude down or pushing force in a second mode, a variable magnitude up or lifting force in a third mode or variable magnitude yaw, pitch and roll forces in a fourth mode.

Abstract: Stator (1) for a gas turbine including a stator structure (2) having a continuous through-duct (3) for a gas through-flow, a circumferential member (6), which is arranged at a radial distance from the stator structure and is operatively coupled to the stator structure, and at least one member for maintaining the distance between the stator structure and the circumferential member. The spacing member has resilient characteristics in the radial direction of the stator.

Abstract: A dishwasher includes a number of spray arms, a circulation pump with a pump housing, an impeller, a suction port, and a number of discharge ports on the pump housing. The discharge ports are associated with the spray arms. A water diverter is located on a delivery side of the pump and generates a flow leading from the suction port selectably to one or more of the discharge ports. The water diverter includes a blocking element having a number of diaphragm openings positionable to one or more outlet positions by a drive via a rotation of the blocking element in a circumferential direction.

Abstract: An electromechanical inlet guide vane actuation system includes one or more electric motor driven actuators that are used to appropriately position the inlet guide vanes in a gas turbine engine. The actuation system includes a control circuit that supplies guide vane actuation control signals in response to guide vane position command signals it receives. The guide vane actuation control signals are supplied to one or more electric motors, which position actuators, and thus the inlet guide vanes, to the commanded position.

Abstract: A position control method by motor drive including of rotating a rotor of the motor drive according to the given target opening, and detecting the opening of a movable vane by an encoder, the motor drive opening and shutting a passage of an intake air pipe to a turbo charger of the automobile by the movable vane, and controlling the movable vane in the passage of the intake air pipe so that it reaches the target opening. The rotational position of the motor drive is controlled to the stop position in the direction where the movable vane is closed and the stop position in the direction where the movable vane is opened. The motor drive is controlled so that the passage of the intake air pipe becomes the target opening by setting the stop position as an operation reference position of the motor drive, and setting between the stop positions as the driving dynamic range motor drive.

Abstract: In an exhaust gas turbine for a turbocharger of an internal combustion engine with a casing and a rotor rotatably supported in the casing, the casing includes an inlet duct with a guide vane structure supported so as to be movable into and out of a flow inlet area to the rotor by means of an electric motor.

Abstract: A turbocharger having a variable geometry turbine inlet incorporates a piston movable to vary the area of the inlet nozzle into the turbine. Vanes extending from the heat shield for flow control in the nozzle are engaged by the piston in a first closed position. In a second open position, the piston is spaced from the vanes increasing the inlet nozzle area.

Abstract: Improved actuation assemblies are used with variable geometry turbochargers comprising a plurality of movable aerodynamic vanes attached to a movable unison ring that is coupled to an actuator. The actuation assembly includes a crank arm that is attached at a first end to the actuator, and at a second end to the unison ring. A first gear member is attached to the crank arm second end and includes teeth. The unison ring includes a second gear member attached thereto that also comprises teeth. The teeth of the first and second gear members are cooperatively engaged with one another. The second gear member is movably attached to the unison ring to maintain predetermined distance between the first and second gear members during operation of the turbocharger and related thermal movement of the unison ring.

Abstract: A variable geometry turbocharger assembly employing the present invention includes a center housing, a compressor housing attached to one side of the center housing, and a turbine housing attached to another side of the center housing. A plurality of movable vanes is disposed within the turbine housing, and a unison ring is rotatably disposed within the turbine housing to move the vanes in unison. The turbocharger includes a unison ring assembly of this invention that includes an insert that is separate from and attached to the center housing. The support has one or more surfaces to carry the unison ring, and the unison ring is rotatably positioned on the support. The support further provides a space that isolates the unison ring from making contact with contacting the center housing. A heat shroud optionally extends radially inwardly along the center housing and is retained into position by the support.

Abstract: The invention concerns an exhaust gas turbocharger for an internal combustion engine, with at least one turbine arranged in the exhaust gas stream downstream of the internal combustion engine, wherein the turbine includes at least one flow channel with at least one radial flow cross-section, with a nozzle ring bordering the radial flow cross-section, wherein for the variable adjustment of the radial flow cross-section a variable guide vane is provided in this area.

Abstract: One of the swing shafts 32 of the nozzle vanes 31 is selected so as to operate as swing drive shaft 33 that projects to the outside. As the swing drive shaft 33 is driven to revolve, all the nozzle vanes 31 are driven to turn by a same angle by way of the driving lever 21 and the coupling ring 18 linked to it. Therefore, it is only the swing drive shaft 33 that projects to the outside, the projecting part can be sealed in a simple and reliable manner to improve the sealing effect and the durability of the variable geometry turbocharger. Additionally, since the rotary motion of the swing drive shaft 33 is directly used to driven the nozzle vanes 31 to swing, the mechanism for transmitting the driving force is simplified.

Abstract: In a nozzle vane driving control apparatus of a variable nozzle turbocharger including an actuator for carrying out a driving operation for opening and closing a nozzle vane of a variable nozzle and an ECU for controlling the opening degree of the nozzle vane which is obtained by the actuator, an actuator cover for covering a pinion and reduction gears by interposing a base provided integrally with a motor case portion therebetween, a unit body accommodating each of control boards, a position sensor for detecting the rotating position of an output shaft and a connector having a terminal connecting a motor and each of the control boards, and a unit cover for covering the unit body are removably fastened and fixed with a bolt and are thus integrated with each other.

Abstract: An exhaust gas turbocharger for an internal combustion engine, which has an exhaust gas turbine in the exhaust system and a compressor in the induction system, comprises a variable turbine geometry, associated with the turbine, for adjustably setting a radial inlet cross section for the flow to the turbine rotor. The variable turbine geometry is configured as a guide cascade ring, which has guide vanes distributed over the periphery and encompasses the turbine rotor. The minimum distance between two adjacent guide vanes obeys a specified relationship with respect to the diameter of the turbine rotor and the number of guide vanes of the guide cascade ring. In addition, a flow edge is provided on the radially inner surface of each guide vane.

Abstract: A vaned diffuser for a centrifugal compressor has provision for selectively adjusting the pitch of the vanes in order to accommodate variable load conditions. Each of the vanes is rotatable about a pivot pin near its leading edge and is engaged with an actuation member near its trailing edge. The actuation members are attached to a common ring which can be selectively rotated to move to the vanes in unison. The ring is supported by rollers at its outer periphery and is positioned at the outer periphery of a diffuser wall such that there is no forward facing step projecting into the flow stream. A throat is defined between adjacent vanes, and the pivot pin for each vane is located downstream of the throat on the pressure side of the vane to reduce turbulence in the flow at the throat.

Abstract: An actuator for adjustable stator vanes in a gas turbine engine. A torque tube is rotatable about its axis, and supports devises which connect to links. The links are connected to rings, and rotate the rings when the torque tube rotates, thereby adjusting stator vanes connected to the rings. A linear actuator, having a motion axis parallel to the torque tube, drives the torque tube, through a linear-rotary convertor. The invention occupies less space on the engine, and requires no adjustment of the linear-rotary convertor after installation.

Abstract: A turbine, intended to be used in a plant of the geothermal type, comprises an apparatus for the choking of the control stage. The latter provides closure means for closing at least one nozzle of the first stage of the turbine, the said nozzles facing a final section of a feed pipe of the said turbine. Also provided are control means for controlling the said closure means, capable of causing the said closure means to assume at least one position of rest and one working position in which they are disposed to close the at least one nozzle in the vicinity of the final section of the said feed pipe.

Abstract: A non-contacting electromagnetic coupling device comprised of an electromagnetic coupling rotor (30) and an electromagnetic ring (32) is applied to control and actuate the wicket gates of a hydro turbine. This electromagnetic coupling device extracts mechanical power directly from the rotating hydro turbine/generator and uses the extracted power to close the wicket gates (12) and remove the water loading on the turbine runner (10) during the emergency shutdown event. The electromagnetic coupling device is excited by a direct current power source (36), the output of which is varied to vary the power extracted from the hydro turbine/generator.

Abstract: A vaned diffuser for a centrifugal compressor has provision for selectively adjusting the pitch of the vanes in order to accommodate variable load conditions. Each of the vanes is rotatable about a pivot pin near its leading edge and is engaged with an actuation member near its trailing edge. The actuation members are attached to a common ring which can be selectively rotated to move to the vanes in unison. The ring is supported by rollers at its outer periphery and is positioned at the outer periphery of a diffuser wall such that there is no forward facing step projecting into the flow stream. A throat is defined between adjacent vanes, and the pivot pin for each vane is located downstream of the throat on the pressure side of the vane to reduce turbulence in the flow at the throat.

Abstract: A vane actuator for use in a turbine engine, comprising a carrier member carrying a plurality of vanes which is angularly movable, in use, so as to vary the position of the vanes relative to an airflow through the engine. The actuator includes an electrical drive arrangement comprising an input shaft which is arranged to drive an output shaft coupled to the carrier member. The electrical drive arrangement includes a brake arrangement arranged to apply a braking load to the input shaft in the event that an interruption occurs in the electrical drive arrangement.

Abstract: A nozzle adjustment mechanism for a variable-capacity turbine has a connection between a connecting lever, for connecting a nozzle drive component driven by a actuator to a nozzle vane, and an edge of a nozzle shaft on the nozzle vane. The connection has a high degree of strength and does not experience deformation. A connecting hole of the connecting lever has a stopper surface which is flat or curved. The connecting edge of the nozzle shaft also has a stopper surface which corresponds to the stopper surface of the connecting hole. When the connecting edge of the nozzle shaft goes into the connecting hole of the connecting lever, the stopper surface of the connecting edge is brought into contact with the stopper surface of the connecting hole. After contact is made, a fixing process is applied to the connecting edge. The connector lever and the connecting edge of the nozzle shaft are thus effectively locked together in such a way that neither can rotate with respect to the other.

Abstract: An actuator for adjustable stator vanes in a gas turbine engine. A torque tube is rotatable about its axis, and supports devises which connect to links. The links are connected to rings, and rotate the rings when the torque tube rotates, thereby adjusting stator vanes connected to the rings. A linear actuator, having a motion axis parallel to the torque tube, drives the torque tube, through a linear-rotary convertor. The invention occupies less space on the engine, and requires no adjustment of the linear-rotary convertor after installation.

Abstract: An electronically controlled actuator for controlling a turbocharger is provided. A motor (130), a speed change mechanism (140) and a position sensor (150) are contained in a case consisting of a body (110) and a cover (120). The driving force of the motor (130) is transmitted through the speed change mechanism (140) to an output shaft (145) to drive the movable vanes of a turbocharger for turning. A first bearing (146A) supporting the output shaft for rotation is held on the cover (120), and a second bearing supporting the output shaft for rotation is held on the body (110). The position sensor (150) is mounted on the output shaft of the motor (130). The reliability of the actuator is improved.

Abstract: A column airflow power apparatus for creating mechanical power is provided. The column airflow power apparatus comprises a column structure having an open first end and an open second end with airflow moving through the column structure from the first end to the second end. A rotatable blade is mounted within the column structure with the airflow rotating the rotatable blade. A power shaft is connected to the rotatable blade with the power shaft rotating with the rotatable blade. A rotatable turret device is mounted to the second end of the column structure and an adjustable airfoil mounted to the rotatable turret. An air concentrator can be mounted within the column structure between the first end and the rotatable blade.

Abstract: A turbocharger comprises a center housing, and a shaft positioned therein having a first end and a second end. A turbine housing is attached to one side of the center housing and has a turbine wheel disposed therein that is coupled to the first end of the shaft. A first variable geometry member is disposed within the turbine housing between an exhaust gas inlet and the turbine wheel. A compressor housing is attached to another side of the center housing opposite the turbine housing, and includes a compressor impeller disposed therein. The compressor impeller is coupled to the second end of the shaft. A second variable geometry member is disposed within the compressor housing, and is interposed between an air outlet and the compressor impeller. An actuator assembly is disposed within the turbocharger and is connected to both of the variable geometry members to provide simultaneous actuation of the same.

Abstract: A device for controlling a variable-angle vane for a stator of a turbomachine compressor, the device comprising a link, connection means forming a hinge between a first end of the link and a control ring, and fixing means for fixing a second end of the link on a pivot of a vane to be controlled, a radial recess formed in the vane pivot for receiving the second end of the link, the recess having at least one plane edge inclined relative to a longitudinal midplane of the recess and co-operating with a corresponding inclined edge of the second end of the link, and a clamping cap bearing against the second end of the link and on which the fixing means act, the clamping cap having an inside surface providing plane contact with the outside face of the second end of the link in order to maintain the second end of the link against the vane pivot without slack by means of contact between the-inclined edges.

Abstract: A device for controlling a variable-angle vane for a stator of a turbomachine compressor, the device comprising a link, connection means forming a hinge between a first end of the link and a control ring, fixing means for fixing a second end of the link on a pivot of a vane to be controlled, and pinch means acting transversely relative to a longitudinal midplane of the link to lock the second end of the link in rotation without slack on the pivot.

Abstract: A variable-capacity turbine provided with a nozzle adjustment mechanism having a nozzle drive component, a lever and nozzle vanes, all housed at the inner side of a scroll in a turbine casing. This reduces the axial length of the turbine and makes it more compact, and thus easier to install in a car. It also avoids the problem of the center casing becoming too complex. There are fewer assembly and disassembly processes, and the turbine is easier for maintenance. This variable-capacity turbine has a nozzle drive member for the nozzles which is connected to an actuator that causes the drive member to rotate around the shaft turbine and a nozzle adjustment mechanism which includes a number of connectors to link the nozzle drive member to the nozzle vanes.

Abstract: An exhaust gas turbocharger for an internal combustion engine, which has an exhaust gas turbine in the exhaust system and a compressor in the induction system, comprises a variable turbine geometry, associated with the turbine, for adjustably setting a radial inlet cross section for the flow to the turbine rotor. The variable turbine geometry is configured as a guide cascade ring, which has guide vanes distributed over the periphery and encompasses the turbine rotor. The minimum distance between two adjacent guide vanes obeys a specified relationship with respect to the diameter of the turbine rotor and the number of guide vanes of the guide cascade ring. In addition, a flow edge is provided on the radially inner surface of each guide vane.

Abstract: An annular radially disposed split ring diffuser for a centrifugal compressor includes an inner ring and an outer ring. A drive positioning mechanism includes a pinion gear on a pinion axle driven by an actuator. A rack gear is mounted to the inner ring and adapted to engage in meshing arrangement with the pinion gear. The actuator is operable to position the inner ring between a fully open position and a partially closed position with respect to the outer ring. A travel limiter is provided to positively limit the travel of the inner ring at the fully open and the partially closed positions. A compliant mechanical stop on a side of the rack gear touches an outer ring stop on the outer ring when the inner ring is in the fully open position to prevent the gear teeth from being stripped by the actuator torque output.

Abstract: The invention provides a method and device of assembling and adjusting a variable capacity turbine, which simplifies assembling process resulting in reduction of man-hours and costs of assembling and adjustment, and makes it possible that the nozzle vane setting of the adjustable nozzle mechanism is done with high accuracy without influenced by the accuracy in dimensions of the constituent parts such as nozzle vane and annular link mechanism and that the adjustable nozzle vane mechanism is adjusted whenever necessary even after the turbine is assembled.