Abstract: A wicket gate for a hydraulic turbine or pump contains a blade being defined by a pressure surface, an oppositely facing suction surface, a leading edge and a spaced apart trailing edge, a first trunnion, a second trunnion, an air inlet aperture, an air passage and at least one air outlet aperture. The profile of the suctions side surface of the blade along a cross section through a point P1 and a point P2 is concave. Whereas point P1 is located on the suction side surface of the trailing edge where an air outlet aperture is located and point P2 is spaced apart from point P1 by less than 10% of the wicket gate length D and point P2 is located upstream of point P1 on a line perpendicular to the trailing edge starting at point P1.

Abstract: A vane assembly for a turbomachine includes a variable vane (10-15), the vane having at least one first, in particular plane or curved, engagement surface (11; 11?) for clamping, in particular without play, an actuator (20) of the vane assembly for adjustment of the vane, this first engagement surface not being inclined toward a longitudinal axis (L) of the vane or being inclined toward it by no more than 15°, and/or the vane assembly including a clamp (30; 31) for clamping the actuator against the first engagement surface by at least partially elastically compressing the clamp transversely to the longitudinal axis of the vane and/or by advancing the clamp in a clamp direction (S) that forms an angle of at least 45° with the longitudinal axis of the vane.

Abstract: A variable guide vane assembly has: variable guide vanes having airfoils extending from inner ends to outer ends, the variable guide vanes pivotable about respective spanwise axes between one or more open positions and a closed position, in the closed position, trailing edge regions of the airfoils sealingly engage leading edge regions of adjacent ones of the airfoils to block an air flow; an outer wall extending around the central axis, the outer ends of the variable guide vanes pivotably engaged to the outer wall; and an inner wall extending around the central axis, the inner ends of the variable guide vanes pivotably engaged to the inner wall, the inner wall defining inner faces distributed about the central axis, a shape of the inner faces complementary to a shape of the inner ends of the airfoils to form a seal when the variable guide vanes are in the closed position.

Abstract: An impeller rotatable about a rotation axis, has a hub, blades extending from the hub to tips circumferentially distributed around the rotation axis, the blades having pressure sides and suction sides, the blades including splitter blades interspersed between full blades, a chord length of the splitter blades less than a chord length of the full blades, first flow channels defined between pressure sides of the splitter blades and suction sides of the full blades, second flow channels defined between suction sides of the splitter blades and pressure sides of the full blades, respective widths of the first and second flow channels at a given rotor location defined between adjacent splitter and full blades at the given rotor location, a width of the first flow channels increasing from the hub to the tips of the splitter blades along at least a portion of the chord length of the splitter blades.

Abstract: An adjustable guide apparatus for a turbine, comprising a bearing ring with a plurality of guide vanes, wherein the guide vanes are rotatably mounted on the bearing ring with the aid of guide vane shafts, wherein in order to position the guide vane, the guide vane shaft is allocated an adjusting lever which engages in a rotatable rotating ring of the adjustable guide apparatus, and wherein, in order to be held in an exhaust gas guiding section of the turbine, the adjustable guide apparatus has a support ring, and wherein the support ring serves to mount the rotating ring. The rotating ring is radially and/or axially guided with the aid of at least one guiding element, wherein the guiding element is received on the support ring. Furthermore, the invention relates to a turbine with an adjustable guide apparatus and to an exhaust turbocharger.

Abstract: Provided is a turbocharger, including: a turbine impeller (impeller); nozzle vanes provided on a radially outer side of the turbine impeller; a nozzle ring to which the nozzle vanes are provided; a heat-shielding member including: an outer contact portion, which is arranged between a back surface of the turbine impeller and a wall portion of a bearing housing (housing), and is brought into contact with the nozzle ring from a side opposite to the nozzle vanes; and an inner contact portion, which is at a position on an inner side in a radial direction of the shaft with respect to the outer contact portion, and is brought into contact with a wall portion of the bearing housing from the turbine impeller side; and a separation portion, which is formed on the wall portion of the bearing housing, and is recessed toward a side of separating from the heat-shielding member with respect to a contact portion to be brought into contact with the inner contact portion of the heat-shielding member.

Abstract: A mixed-flow turbine wheel is proposed which, compared to existing mixed-flow turbine wheels, has reduced mass and moment of inertia because radially-outer portions of existing mixed-flow turbine wheels are omitted. In a first possibility, the omitted material may be scalloping of the back face of the turbine wheel at a radial position outward of a base line which is a circle on the back surface of the wheel which indicates the minimum radius of the back surface. In a second possibility, part of the webbing of each blade is omitted to one side of the blade. Thus, viewing the turbine wheel in the axial direction, the area of the webbing outside the baseline and to one side of a radial line through the inducer tip, may be at least 20% less than that on the other side.

Abstract: A projecting portion is formed on a nozzle ring, projects to a radially outer side with respect to a cylindrical portion, extends in a circumferential direction, and is held in abutment against a housing from a side of a link plate. A plate is faced to the nozzle ring on a side of a nozzle vane, and is configured to form a flow passage in a clearance to the nozzle ring. A pin is inserted into a first insertion portion formed in the nozzle ring and a second insertion portion formed in the plate, and to which the nozzle ring and the plate are mounted while the clearance is maintained. A counter bore groove is formed in the first insertion portion of the nozzle ring on the side of the link plate, and cut out the projecting portion.

Abstract: An impeller comprises a hub and blades extending therefrom. The blades include splitter blades interspersed between full blades. First flow channels are defined between pressure sides of the splitter blades and suction sides of the full blades. Second flow channels are defined between suction sides of the splitter blades and pressure sides of the full blades. A width of the first flow channels at leading edges of the splitter blades and at the hub is less than a width of the second flow channels at the leading edges of the splitter blades and at the hub. The width of the first flow channels at the leading edges of the splitter blades and at the tips is more than the width of the second flow channels at the leading edges of the splitter blades and at the tips.

Abstract: A variable turbine geometry may include guide blades mounted rotatably in a blade carrier via one blade bearing pin for each guide blade, a blade lever arranged at an end of the blade bearing pin that faces away from the respective guide blade, and an articulated lever for a simultaneous adjustment of the guide blades via an adjusting ring arranged between two adjacent blade levers. The articulated lever may be provided with a stop contour, and when one of a maximum flow position or a minimum flow position is reached, the stop contour may lie against one of the two adjacent blade levers to define the one of the maximum flow position or the minimum flow position.

Abstract: A turbocharger having a variable-nozzle turbine formed by pivotable vanes supported by a nozzle ring includes a locator that is radially elastically deformable and is disposed between a radially outwardly facing surface of the center housing and an opposing surface of the nozzle ring for radially locating the nozzle ring relative to the center housing. At least one vent is defined in either a radially outermost surface of the locator or the surface of the nozzle ring to allow pressure communication between spaces on axially opposite sides of the locator.

Abstract: A turbocharger (10) including variable turbine geometry has a turbine wheel (24) with a turbine axis of rotation (R1) that extends in an axial direction. The turbocharger (10) also has a plurality of guide vanes (34) that is selectively movable between a range of angular positions. Each one of the guide vanes (34) is supported for pivotal movement about a guide vane axis of rotation (R2) and each guide vane axis of rotation (R2) is non-parallel to the turbine axis of rotation (R1).

Abstract: A variable turbine geometry turbocharger (100) with an adjustment ring assembly (45) having an adjustment ring (50) and a series of pivotable guide vanes (30) that are operably connected to the adjustment ring (50). A spring-biased retention clip (60) is between adjacent vane levers (36) and is attached to the adjustment ring (50). The retention clip (60) applies a force against the adjacent vane levers (36) and dampens and reduces movement of corresponding components.

Abstract: A vane pack assembly (14) for a variable turbine geometry turbocharger is a stand-alone assembly and can be assembled and transported apart from the turbocharger. The vane pack assembly (14) includes a plurality of guide vanes (16) spaced apart in a circumferential direction and a plurality of pivot centers (38). Each one of the pivot centers (38) corresponds with one of the guide vanes (16). A location of the pivot centers (38) relative to the guide vanes (16) changes as an angular position of the guide vanes (16) is adjusted.

Abstract: A device for controlling a gas flow through a passage includes a plurality of pivotable gas flow control vanes. The pivot axes of a first and a second adjacent vane are spaced so that a trailing edge of the first vane overlaps a leading edge of the second vane when the first and second adjacent vanes are positioned in a first mutual end state for substantially restricting the gas flow through the passage. The second vane includes a recess with such a shape that the trailing edge of the first vane is at least partly received in the recess when the first and second adjacent vanes are positioned in the first mutual end state.

Abstract: A turbocharger turbine section is disclosed. The turbine may include a first swing vane rotatably coupled with a first pin that may include a first leading edge, a first trailing edge, a first exhaust side edge extending between the first leading edge and the first trailing edge and a first bearing side edge extending between the first leading edge and the first trailing edge. Furthermore, the turbine may include a second swing vane rotatably coupled with a second pin that may include a second leading edge, a second trailing edge, a second exhaust side edge extending between the second leading edge and the second trailing edge and a second bearing side edge extending between the second leading edge and the second trailing edge. Moreover, the turbine may include an exhaust side nozzle wall, a bearing side nozzle wall opposite the exhaust side nozzle wall and a turbine wheel.

Abstract: A variable geometry turbocharger is simplified yet able to reliably operate in a robust, cost effective manner. The adjusting ring assembly has a reduced number of parts in the vane adjusting assembly but still operates as it did with the parts in the conventional assembly, but at lower part and capital cost. The adjusting ring is constrained axially and radially by interaction with an inner diameter and an abutment provided in the upper vane ring of the vane pack.

Abstract: An oscillating water column (OWC) turbine and method of extracting energy therefrom is provided. The OWC turbine includes a shaft (101) rotatable about a central axis (103), and first and second ports (112, 114) disposed around the central axis. A flow passage (104) extends radially-inward from the ports and extends axially therebetween. Rotor blades (120) are coupled to the shaft, intersect the flow passage, and are offset from the central axis by a first distance. First guide vanes (116) intersect the flow passage and are disposed proximal the first port. The first guide vanes (116) include first and second stators (116a, b), the first stators (116a) being positioned between the first port (112) and the second stators (116b). Second guide vanes (118) intersect the flow passage and are disposed proximal the second port. The first and second guide vanes are offset from the central axis by a second distance that is greater than the first distance.

Abstract: In an adjustable guide vane mechanism for a turbine, comprising a bearing ring with a plurality of guide vanes rotatably supported on the bearing ring by means of guide vane shafts provided with actuating levers which are engaged by a rotatable ring, the rotatable ring comprises axially spaced radial inner and outer sections with a radially inclined center section joining the spaced radial inner and outer sections, the radially inner section being rotatably supported and the radially outer section extending around the actuating levers and having recesses in which the actuating levers are received for pivoting the actuating levers and the guide vanes upon rotation of the rotatable ring.

Abstract: An exhaust-gas turbocharger which has a radial bearing with a simple design which can quickly and easily be mounted. A pin/rolling roller arrangement is provided as the radial bearing. The pin is in this case fixed on the vane bearing ring. The rolling roller is placed onto the pin and, in the mounted state, an inner wall region of the unison ring is supported on the rolling roller mounted rotatably on the pin.

Abstract: The propensity for gas leakage around a shaft, which connects volumes of differing pressures, in, e.g., a turbocharger is minimized in a simple cost-effective manner. The addition of a complementary pair of frusto-spherical, conical, or other profiles to the interface of the shaft and its bearing maintain concentricity of the shaft in its bore and thus improve the efficacy of existing sealing protocols.

Abstract: A system, in certain embodiments, includes a centrifugal compressor diffuser that includes an elliptical plate including multiple vane receptacles disposed about an axis of the plate and multiple detachable vanes attached to the plate. Each vane receptacle includes a first two dimensional (2D) projection along a plane of the elliptical plate and each detachable vane includes a second two dimensional (2D) projection along a base portion of the vane, where each detachable vane is disposed in a respective vane receptacle with the first and second 2D projections blocking movement of the detachable vane in at least a first axial direction relative to the elliptical plate. In certain embodiments, the first and second 2D projections may include a first tab to fit in a recess between a pair of second tabs, respectively, or vice versa. However, in other embodiments, the first and second 2D projections may include alternative mating surfaces.

Abstract: A turbine and method of operating the same includes a housing having a volute and an outlet and an impeller rotatable coupled to the housing. The turbine includes a nozzle ring having a plurality of primary nozzles and a plurality of secondary nozzles. The plurality of primary nozzles and the plurality of secondary nozzles direct fluid toward the impeller. An auxiliary valve assembly selectively communicates fluid from the volute to the plurality of secondary nozzles. An actuator is coupled to the valve auxiliary assembly moving the auxiliary valve assembly from a first position communicating fluid from the volute into the secondary nozzles to a second position blocking flow of fluid to the secondary nozzles.

Abstract: A variable geometry turbine includes a fluid space formed by a nozzle mount and a nozzle plate; and a plurality of nozzle vanes arranged in the fluid space at certain intervals in the circumferential direction so as to partition the fluid space. The nozzle vanes are supported by shafts on the nozzle mount, in such a manner as to be capable of turning. The flow rate of the discharged fluid can be adjusted by opening or closing the cross-sectional area of a flow path formed by the adjacent nozzle vanes. The nozzle plate is provided with plate projections protruding toward the nozzle vanes further than, at least, end surfaces of the nozzle vanes, so as to cover the spaces between leading edges of the nozzle vanes and trailing edges of the nozzle vanes adjacent thereto, when the nozzle vanes are at a closed position.

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

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

Abstract: 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: A proportional moving air power transmission and energy collection and control system includes a fixed vertical spindle, a vertical rotational hub and a plurality of wings being supported around the vertical hub in 360°. Each of the wings has a blunt leading end and a pointy trailing end and defining an outer surface and an inner surface. In a fully opened position, the trailing end of each wing is moved away from the vertical hub to a diameter of the wing assembly to drive the vertical hub to rotate. In a fully closed position, the wings are overlapped with each other end-to-end to form a hollow cylinder-like structure to furl, such that the diameter of the wing assembly is minimized for facing the wind at all direction.

Abstract: An exhaust gas turbocharger includes a waste gate valve and an adjusting device for adjusting the waste gate valve. The adjusting device is connected to the waste gate valve and disposed on a housing of the exhaust gas turbocharger. The adjusting device is fastened to the housing of the exhaust gas turbocharger via an adjusting template.

Abstract: A turbocharger includes a variable-nozzle assembly that includes an insert having a tubular portion received into a stepped bore of a turbine housing and having a nozzle portion extending radially out from one end of the tubular portion, and a generally annular nozzle ring axially spaced from the nozzle portion and an array of vanes rotatably mounted to the nozzle ring. Sealing of the interface between the tubular portion of the insert and the turbine housing is provided by a sealing ring formed as a generally annular body having a U- or V-shaped cross-section oriented such that an open side of the U- or V-shaped cross-section faces in a radial direction. The U- or V-shaped cross-section defines two opposing legs, one of the legs being engaged against an end face of the tubular portion of the insert and the other leg being engaged against an upstream-facing step surface of the turbine housing bore.

Abstract: An exhaust gas turbocharger, comprising: a turbine rotor rotatably mounted in a housing, which is associated with at least one guide apparatus forming a radial inlet channel, wherein the guide apparatus includes at least one of a guide vane bearing ring, a plurality of guide vanes radially surrounding the turbine rotor and located in the inlet channel and a guide vane cover ring. The inlet channel is axially delimited by the guide vane bearing ring and the guide vane cover ring wherein the guide vane bearing ring and the guide vane cover ring are moveably mounted at least one of axially and radially relative to each other and to the housing. The guide apparatus is subjected to at least one of an axial and radial preload, wherein a line of axial preload flux runs through the guide apparatus substantially parallel to the rotational axis of the turbine rotor.

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

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

Abstract: A variable geometry turbine comprising 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: According to the present invention, it is possible to achieve improved durability by improving the connection structure of operation links and a control ring to reduce friction and wear between the operation links and the control ring, facilitate manufacturing by simple configuration and structure, and achieve silent and stable operation by making it possible to set the gaps between the parts relatively small.

Abstract: A variable vane system includes a plurality of vanes each being pivotal about an axis. A mechanical linkage drives the plurality of vanes to rotate about the axis. The mechanical linkage includes a ring gear to rotate, and in turn drive the plurality of vanes. There is at least one rod to drive the ring gear to rotate. The rod is driven by a hydraulic servo motor. A spring bias force is provided in the mechanical linkage to resist either translational or rotational oscillation.

Abstract: A method of assembling a crank arm (100, 200, 300) and vane assembly for a variable nozzle without requiring metallurgical bonding. In accordance with one aspect of the invention, the method comprises the steps of providing a vane assembly comprising a vane (120, 220, 320) joined to a vane shaft (110, 210, 310) that extends from the vane and terminates in a distal end (112, 212, 312), providing a recess (114, 214, 314) in an outer surface of the vane shaft at a location between the vane and the distal end, providing a crank arm (100, 200, 300) having an aperture (102, 202, 302) therein, inserting the distal end (112, 212, 312) of the vane shaft into the aperture (102, 202, 302) until the recess (114, 214, 314) in the vane shaft is inside the aperture, and causing a retaining member (104, 204, 304) associated with the crank arm (100, 200, 300) to engage the recess (114, 214, 314) in such a manner as to fasten the crank arm to the vane shaft in a substantially immovable manner.

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

Abstract: A 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: The present invention includes a pivotable vane having an airfoil with a vane spindle or stem extending toward a distal end thereof. The vane stem has a head with a pair of tapered flats having an outwardly extending angle as defined from the distal end of the head towards the airfoil. A vane arm having a substantially C-shaped connector with a pair of contact ends is constructed to maintain a gap with the tapered flats at an initial assembly step and positively engage the tapered flats at a final assembly step.

Abstract: A device is provided for pivoting at least one pivotable element in a gas turbine engine between a first and a second position in order to influence a gas flow in an annular gas duct in at least one of the positions. The device includes a moveable annular member which is arranged externally around the gas duct and is connected to the pivotable element in order to effect the pivoting of the pivotable element. The annular member is more specifically arranged to be displaced in a substantially axial direction and arranged to pivot the pivotable element when it is displaced axially.

Abstract: Charging equipment is disclosed, comprising a variable turbine geometry, and a plurality of guide vanes rotatably mounted between at least one of a guide vane carrier, a cover disc and a turbine housing. The guide vane carrier is positioned on at least one of the cover disc and on the turbine housing by at least one spacer. The geometry has at least two different types of flow channels, a first flow channel wherein flow is influenced by the spacer, and a second flow channel wherein flow is not influenced by the spacer. The first flow channel guide vanes have a radial distance (R1) to a turbine wheel axis, and to a distance from an adjacent guide vane are configured and adjusted such that a gas flow from the first flow channel meeting the turbine wheel corresponds to a gas flow from the second flow channel meeting the turbine wheel.

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 guide vane of a turbo-compressor has variable turbine geometry, in particular for a motor vehicle. The guide vane has a profile with a lower side, an upper side and a front edge. The guide vane is characterized by a nose which extends along the front edge of the vane, from the front edge of the vane to the upper side of the vane and forms a low pressure on the upper side of the vane when waste gas impacts the guide vane. A guide vane configuration, a turbo-compressor, a motor vehicle and a method for operating this type of turbo-compressor are further disclosed.

Abstract: An inlet guide vane is installed at a suction port into which a fluid is sucked by the rotation of an impeller so as to be rotatable about an axis, and is comprised of a rod-like shaft supported by an inner peripheral surface of the suction port so as to be rotatable about the axis, and a plate-like vane body connected to the shaft and provided so as to protrude from the inner peripheral surface of the suction port. The vane body includes a tapered portion formed such that both side surfaces approach each other toward an outer edge of the vane body in its width direction and an outer edge thereof at a tip in the direction of the axis, and a parallel portion arranged on the axis and formed such that both the side surfaces are parallel to each other along the direction of the axis.

Abstract: The invention relates to a rotational device that is to be used in a fluid in order to generate power from the moving stream of a fluid or to convert energy into a motion of a fluid. Said rotational device comprises main rotating means which is fixedly connected to a central rotary shaft of the rotational device, one or several rotational surfaces which are mounted on the main rotating means so as to be rotatable about rotational surface rotary shafts spaced away from the rotary shaft such that the main rotating means are able to perform a rotational motion about the central rotary shaft by means of at least one rotational surface, the rotational surface rotary shafts extending parallel to the rotary shaft of the main body. A device is provided which adjusts an angle of the rotational surface relative to the direction of flow of the fluid in such way that the buoyancy principle is maintained on the rotational surface.

Abstract: A device for controlling a pivot of a variable-pitch blade in a stator of a turbomachine compressor is disclosed. The device for controlling a pivot of a variable-pitch blade includes a control lever and a pivot with a bottom end and a top end. The top end is connected to the control lever. The device also includes a first swivel bearing placed at the bottom end of the pivot and a second swivel bearing placed at the top end of the pivot.

Abstract: An exemplary locating mechanism includes a bearing outer race (422) that has a central axis (z-axis) and that has a turbine end, a compressor end and a slot (421), of an axial length, disposed between the turbine end and the compressor end; and a deformable clip (430) shaped as a semi-cylindrical wall having an axial length less than the axial length of the slot, where in a tension state, the clip (430) has an inner circumference to position the clip (430) with respect to the slot (421) and where in a compression state, the clip (430) has an inner circumference that locates the clip (430) in the slot (421). Various other exemplary technologies are also disclosed.

Abstract: A method of positioning a shaft and associated seal in turbomachinery utilizing electromagnetic bearings. The method includes applying electrical power to the electromagnetic bearings' windings, the shaft center being in a first position and the shaft being in contact with the associated seal. Power adjustment to the electromagnetic bearings moves the shaft. Shaft movements can manipulate the seal, the movements being of decreasing amplitude to a position in which the seal is out of contact with the shaft when the shaft is rotated at its centered position during normal operation. The shaft is in its centered position during normal operation when the shaft axis is substantially coaxial with an axis of the electromagnetic bearings. Movements of decreasing amplitude may include oscillations of decreasing amplitude about one or more axes, or may include a spiral rotation with a decreasing radius to move the shaft center from initial to final positions.

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