Abstract: A variable-nozzle turbocharger includes a variable-vane mechanism that has an annular nozzle ring supporting an array of rotatable vanes connected to vane arms whose distal ends engage recesses in the radially inner periphery of a rotatable unison ring. Rotation of the unison ring causes the vane arms to pivot about their respective pivot axes at the proximal ends of the arms. The vanes are locked in their fully open position by a locking arrangement that includes locking tongues that extend radially inwardly from the inner periphery of the unison ring and contact the vane arms intermediate their distal and proximal ends.

Abstract: An anti-press fan structure includes a fan frame and a fan impeller. The fan impeller has a support shaft supporting the fan impeller disposed in the fan frame. The support shaft has a protrusion section protruding from the fan frame to bear and connect with an external unit positioned above the fan impeller so as to keep an axial space between the fan impeller and the external unit. Accordingly, the fan impeller is prevented from being compressed by the external unit and the pressure applied to the fan frame is dispersed.

Abstract: A turbocharger has a meridionally divided turbine housing defining a first scroll and a first nozzle, and a second scroll and a second nozzle. The first and second nozzles are divided from each other by a shroud plate mounted within the nozzle, for isolating the exhaust gas streams flowing through the two nozzles from each other. A plurality of first vanes are disposed in the first nozzle, and plurality of second vanes are disposed in the second nozzle. A nozzle ring rotatably supports a plurality of vane shafts that extend across the first and second nozzles, passing through openings in the shroud plate. A first vane and a second vane are affixed to each vane shaft. Rotation of the vane shafts causes the first vanes and the second vanes to pivot for regulating the two streams of exhaust gas flowing through the first and second nozzles.

Abstract: A turbocharger has a meridionally divided turbine housing defining a first scroll and a first nozzle, and a second scroll and a second nozzle. The first and second nozzles are divided from each other by a shroud plate mounted within the nozzle, for isolating the exhaust gas streams flowing through the two nozzles from each other. A plurality of circumferentially spaced vanes are rotatably mounted at a radially inner side of the nozzles. Leading-edge portions of the vanes are slotted to receive the shroud plate when the vanes are pivoted open. Trailing-edge portions of the vanes are unslotted. A radially inner periphery of the shroud plate includes cutouts for abutting the trailing-edge portions of the vanes in the closed position, and includes contour portions for influencing a flow separation ratio of the turbine.

Abstract: This turbocharger (10) comprises a turbine wheel (12), a compressor wheel (13), and a scroll flowpath (34) formed in a turbine housing (31), continuing in the circumferential direction on the radially outer side of the turbine wheel (12), and having gas flowing therethrough that rotates and drives the turbine wheel (12). The scroll flowpath (34) is formed such that: an inner circumferential inside wall surface (34c) on the turbine wheel (12) side is gradually displaced radially outwards, along the direction of gas flow; and the cross-sectional area of the flowpath gradually decreases.

Abstract: An assembly for use with a gas turbine engine includes a block housing, a main bell crank, a bell crank, and a sync rod. The main bell crank extends between a main bell crank first end and a main bell crank second end that is connected to an actuator. The bell crank extends between a bell crank first end and a bell crank second end that is pivotally supported by the block housing. The sync rod is connected the main bell crank first end and the bell crank first end. The sync rod defines a first tab disposed proximate a first side and extends beyond a face of the sync rod.

Abstract: A variable displacement supercharger includes a turbine having: a turbine housing that forms a scroll flow passage disposed around a turbine impeller; a variable nozzle unit that includes a second nozzle ring that faces the scroll flow passage and forms a part of an inner wall of the scroll flow passage; and an annular seal member that seals the gap between the turbine housing and the second nozzle ring. The seal member has a disc spring structure that is inserted into the gap and biases the turbine housing and the second nozzle ring in an axial direction of rotation, and is arranged further inside than the scroll flow passage in the radial direction of the turbine impeller.

Abstract: A variable stator blade operating device is a variable stator blade operating device that manipulates the mounting angle of a stator blade of an axial compressor. The variable stator blade operating device includes: an arm which is connected to the stator blade; a rotating ring which is connected to one end of the arm and is externally fitted to a casing of the compressor with an interval between the rotating ring and an outer wall of the casing; a drive mechanism which turns the stator blade via the arm by rotating the rotating ring; and a plurality of elastic bodies arranged in the circumferential direction around the casing, between the rotating ring and the outer wall of the casing. Each of the plurality of elastic bodies is mounted to one of the rotating ring and the outer wall of the casing and contacts the other to energize the rotating ring radially outward.

Abstract: An inner peripheral edge of a first annular member includes a plurality of first inner edge portions belonging to an angular range in which support holes exist in the circumferential direction of a turbine rotor and a plurality of second inner edge portions belonging to an angular range in which the support holes do not exist in the circumferential direction of the turbine rotor. At least one second inner edge portion of the plurality of second inner edge portions comprises a recess portion recessed outward in a radial direction of the turbine rotor, the recess portion extending in an axial direction of the turbine rotor from the side of exhaust gas.

Abstract: A stator of an aircraft turbine engine, comprising an annular row of fixed vanes and an annular row of arms, wherein the trailing edges of the fixed vanes are positioned substantially in a first transverse plane that is positioned downstream of a second transverse plane that passes substantially through the leading edges of the arms.

Abstract: A centrifugal compressor is disclosed. The centrifugal compressor comprises an inlet and an impeller comprising a hub and blades. The inlet is for conveying flow to the impeller comprising guide means and is arranged to guide the flow through the inlet to induce swirl in the flow adjacent tips of the blades, the direction of swirl being the direction of rotation of the blades, without substantially disturbing flow adjacent the hub.

Abstract: An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis. The stator vane body extends axially between a first end and a second end. The stator vane body includes an airfoil, a cavity, and a body surface located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially around the inlet and the shaft, and radially from the stator vane body.

Abstract: A variable turbine geometry turbine turbocharger (1) includes vanes (30) configured to control flow of exhaust gas to a turbine wheel (12), and an adjustment ring (40) connected to each vane (30) that controls the angular orientation of all the vanes (30) in unison. The adjustment ring (40) is supported on the bearing housing (16) and is supported on, and piloted relative to, an axially extending nose portion (17) of the bearing housing (16) by surface features (60) formed along an inner edge (43) of the adjustment ring (40).

Abstract: A centrifugal rotation machine includes a rotation shaft, a plurality of impellers rotating along with the rotation shaft, a casing defining a return flow channel configured to guide the fluid from the front-stage impeller to the rear-stage impeller, and a plurality of return vanes installed in the return flow channel, the return flow channel includes a return bend section guiding the fluid G, which has been sent from the front-stage impeller to the outside in the radial direction, to the inside in the radial direction, the return bend section includes a first curved portion and a second curved portion connected to the downstream side of the first curved portion, and the radius of curvature of an inside wall surface of the second curved portion in the radial direction is greater than the radius of curvature of an inside wall surface of the first curved portion in the radial direction.

Abstract: A device for controlling positioning of variable-geometry equipment of a turbomachine, including a computer, an actuator of variable geometry driven by the computer, and a drive train, the actuator including moving parts including a sensor for measuring its elongation, the drive train being connected at one of its ends to a point of attachment of the moving parts and at another end to a point of attachment of the equipment, the point of attachment moving under action of the actuator along a travel limited by an end stop and the drive train being elastically deformable under the action of the actuator when the point of attachment is against the end stop. An elongation instruction supplied by the computer to the moving parts is defined as a difference with respect to the value of the elongation of the moving parts that corresponds to contact between the point of attachment and the end stop.

Abstract: A platform seal assembly for a gas turbine engine with a turbine disk and a plurality of turbine blades is disclosed. The platform seal assembly includes a platform seal and a validation tab. The platform seal includes a first end, a second end, opposite and distal to the first end, and a body extending between the first end and the second end. The validation tab includes an attachment portion affixed to the platform seal and an observable indicator portion extending from the attachment portion.

Abstract: A variable geometry turbo system that controls a flow of exhaust gas introduced into a turbine of a turbo charger may include a vane base ring in which the turbine may be positioned at a center thereof, a fixed vane which may be fixed onto a first surface of the vane base ring to guide the exhaust gas introduced into the turbine, a variable vane which may be pivotally positioned on the first surface of the vane base ring and adjacent to the fixed vane so as to vary a flow path of the exhaust gas introduced into the turbine, a vane cover ring fixed to the vane base ring with the fixed vane and the variable vane interposed therebetween, and an actuating module coupled to the variable vane and selectively actuating the variable vane.

Abstract: In a turbine for an exhaust gas turbocharger with a turbine casing having a receiving chamber for accommodating a turbine wheel and at least one volute through which the exhaust gas is guided via a feed passage into the receiving chamber and wherein at least one guide element is provided in the turbine casing so as to project into the feed passage in a guide region for guiding the exhaust gas onto the turbine wheel, the guide element comprises a first length region in the axial direction of the turbine, in which the guide element is designed with respect to its aerodynamic properties differently from its aerodynamic design in a second length region adjoining the first length region.

Abstract: A variable turbine geometry (VTG) exhaust-gas turbocharger in which guide vanes are adjusted by means of a unison ring, the structure of which has a simpler and thus more cost-effective design. The number of components is reduced, for example for rollers on pins as are provided in the case of known bearings. A very beneficial relationship between friction radius and rolling radius in the given installation space is obtained.

Abstract: The present application provides a variable stator vane control system. The variable stator vane control system may include a variable stator vane positioned by an actuator and a trimmer motor, a resolver to determine a position of the variable stator vane, and a controller in communication with the resolver, the actuator, and the trimmer motor to prevent over travel of the variable stator vane.

Abstract: A variable turbine geometry (VTG) exhaust-gas turbocharger in which guide vanes are adjusted by means of a unison ring, the structure of which has a simpler and thus more cost-effective design. The number of components is reduced, for example for rollers on pins as are provided in the case of known bearings. A very beneficial relationship between friction radius and rolling radius in the given installation space is obtained.

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: An exhaust-gas turbocharger (1) having a turbine (2), with a turbine wheel (3) surrounded by an intake duct (4), and a VTG cartridge (5), with a washer (6) and a vane bearing ring (7), which delimit the intake duct (4), and with a plurality of vanes (8), arranged in the intake duct (4) and mounted in the vane bearing ring (7) by way of rotatable vane shafts (9), which are connected to vane levers (10), the lever heads (11) of which engage into associated grooves (12) in a unison ring (13), which surrounds the vane bearing ring (7); and having a radial bearing between the unison ring (13) and the vane bearing ring (7). The vane levers (10) for forming the radial bearing are in the form of cam levers, the lever heads (11) of which are supported in the grooves (12).

Abstract: A variable geometry turbocharger includes a vane pack having rotatable vanes constrained by a pair of vane rings held together by a plurality of pins. A first end of each pin can be configured with a head. Each pin is received in a pair of aligned apertures in the vane rings such that the head of each pin engages one of the vane rings. A second end of each pin is deformed (e.g., by orbital riveting) such that it engages the other vane ring. Thus, a clamp load is applied to the vane rings, which can control the parallelism and distance between the vane rings so that the vanes can rotate with a minimum clearance without jamming. Also, the pins can maintain vane axle apertures in the vane rings in the correct angular position relative to each other. Such a vane pack configuration can reduce process time and cost.

Abstract: A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first vane segments that extend radially between an inner rotor platform and an outer rotor platform, and a plurality of first flow apertures that extend axially through the duct blocker rotor. Each first flow aperture also extends circumferentially between respective adjacent first vane segments. The duct blocker stator includes a plurality of second vane segments that extend radially between an inner stator platform and an outer stator platform, and a plurality of second flow apertures that extend axially through the duct blocker stator. Each second flow aperture also extends circumferentially between respective adjacent second vane segments. The first vane segments move circumferentially relative to the second vane segments to regulate fluid flowing between the first flow apertures and the second flow apertures.

Abstract: A turbine wheel mounted within a housing rotating about a turbine axis; a gas flow control passage upstream of the turbine wheel between a radial first surface of a movable wall member and a facing wall of the housing, the movable wall member comprising second and third surfaces opposing the first surface. The movable wall member moves in an axial direction to vary the size of the gas flow control passage. A first gas region of the turbine, being upstream of the gas flow control passage, includes a portion of the gas flow control passage; a second gas region of the turbine downstream of the gas flow control passage containing the turbine wheel; and a third gas region of the turbine downstream of the turbine wheel. The first gas region comprises the first and second surfaces, and the second gas region or third gas region comprises the third surface.

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: An actuation system includes a driving ring configured to rotate and having a groove on an internal face facing a central point of the driving ring; at least a linkage attached with a first end to an inside of the groove; and at least a lever arm attached to a second end of the at least a linkage. At least a portion of the at least a linkage stays inside the groove when the driving ring rotates.

Abstract: An axial compressor includes: a spray nozzle (32) that supplies droplets to a working fluid before compression or being compressed; a variable stator vane (56) having a stem section (94) inserted in an insertion hole (73) in a casing (54), the variable stator vane (56) having an angle of attack varied through sliding motion relative to the casing caused by rotation of the stem section; a sealing groove (93) provided in a sliding portion between a thrust washer (82) slid relative to the casing during rotation of the stem section and the casing; and a sealing member (92) housed in the sealing groove.

Abstract: Various systems and methods are described for a variable geometry turbine. In one example, a turbine nozzle comprises a central axis and a nozzle vane. The nozzle vane includes a stationary vane and a sliding vane. The sliding vane is positioned to slide in a direction substantially tangent to an inner circumference of the turbine nozzle and in contact with the stationary vane.

Abstract: Embodiments may provide variable geometry turbine, a nozzle vane for a variable geometry turbine, and a method. The variable geometry turbine that may include a turbine wheel and a plurality of adjustable vanes radially positioned around the turbine wheel. The turbine may also include a flow disrupting feature on one or more outside surfaces of one or more of the plurality of adjustable vanes.

Abstract: Embodiments of the present invention may include a variable nozzle turbocharger having a variable nozzle mechanism. The variable nozzle mechanism has a unison ring and a drive arm. The unison ring adjusts a degree of opening of variable nozzles having nozzle vanes through rotation of the unison ring. The unison ring has a first fit-engagement groove. The first fit-engagement groove has a closing side surface of a concave arcuate shape and an opening side surface of a convex arcuate shape facing the closing side surface with a fixed groove width therebetween. A drive arm has a first fit-engagement portion engaged with the first fit-engagement groove so that the first fit-engagement portion is rotatable and movable in the radial direction of the unison ring. The first fit-engagement portion has a closing side contact surface of a convex arcuate shape that is able to contact the closing side surface.

Abstract: Embodiments of the present invention may include a variable nozzle turbocharger having a variable nozzle mechanism for controlling a flow velocity of exhaust gas to a turbine wheel. The variable nozzle mechanism includes a plurality of variable nozzles, a unison ring and a biasing member. The variable nozzles each have a nozzle vane. The unison ring is configured to adjust a degree of opening of the variable nozzles through rotation of the unison ring. The biasing member biases the unison ring so as to open the variable nozzles.

Abstract: Three or more attachment pins are arranged on a right lateral surface of a nozzle ring at intervals. All the attachment pins are placed outside support holes in the nozzle ring in radial directions of the nozzle ring. A guide ring is provided across right lateral surfaces of the attachment pins. A first side guide member to support a right lateral surface of a drive ring in away that allows the right lateral surface to be in sliding contact therewith is provided to the right of the guide ring. A second side guide member to support a left lateral surface of the drive ring in a way that allows the left lateral surface to be in sliding contact therewith is provided to the left of the guide ring.

Abstract: A centering device includes a pivoting part configured to pivot around a first axis that extends along an axial direction of a hole formed in the pivoting part; a roller attached to a first end of the pivoting part and configured to rotate; a rod attached to a second end of the pivoting part and configured to move along a second axis; a spring mechanism enclosing a part of the rod and configured to apply a biasing force to the pivoting part; and a rod housing configured to receive an end of the rod and to allow the rod to freely move through the rod housing.

Abstract: A synchronization ring for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a synchronization ring for a variable vane assembly. A plurality of rollers are attached to the synchronization ring for engaging a case on the gas turbine engine.

Abstract: A gas turbine engine includes a synchronizing ring. A cradle includes an integrally formed anti-rotation feature. The cradle is secured to the synchronizing ring and located relative thereto with the anti-rotation feature. A bumper is slidably supported within the cradle. In one example, a bushing is provided within a hole in the bumper. A fastener is inserted into the hole and a bushing to secure the bumper to the synchronizing ring.

Abstract: A turbocharger for an internal combustion engine includes a center housing, a shaft rotatably supported in the center housing, and a turbine wheel connected at one end of the shaft. A turbine housing is connected to the center housing and disposed around the turbine wheel. A bore formed in the turbine housing extends from a gas outlet end of the turbine housing to an annular stop surface of the turbine housing disposed adjacent the turbine wheel. A nozzle ring disposed in the bore surrounds a portion of the turbine wheel. An outlet cone is disposed at least partially in the bore and surrounds a remaining portion of the turbine wheel. The outlet cone is connected to the gas outlet end of the turbine housing.

Abstract: In a turbine housing for an exhaust gas turbocharger of an internal combustion engine with at least one spiral channel, which can be coupled into an exhaust gas flow of an exhaust tract of the internal combustion engine, and a receiving space for a turbine wheel which is disposed downstream of the at least one spiral channel and can be acted upon by the exhaust gas of the internal combustion engine passing through the at least one spiral channel of the turbine housing, there is at least one partial housing including the at least one spiral channel, and a housing module which is fastened to the partial housing and has a vane structure disposed upstream of the receiving space which also includes an attachment surface for a bearing section of the exhaust gas turbocharger. The invention also resides in an exhaust gas turbocharger with such a turbine housing as well as to a method for producing such a turbine housing.

Abstract: A variable geometry turbine comprises: a turbine wheel in a housing for rotation about a turbine axis; an annular inlet passage defined between respective radial inlet surfaces of first and second wall members, at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage; an array of vanes extending across the inlet passage, said vanes being connected to said first wall member; a complementary array of vane slots defined by the second wall member, said vane slots configured to receive said vanes to accommodate relative movement between the first and second wall members; the second wall member comprising at least two axially adjacent co-axial plates, a first plate defining a first array of openings which overlie a second array of openings defined by a second plate so as to define said array of vane slots, said first plate being fixed to said second plate.

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: Multiple guide claws are formed integrally on a right side surface of a first nozzle ring of a variable nozzle unit and radially at intervals in a circumferential direction. Each guide claw has a guide groove with a U-shaped cross section, which is formed by lathe turning. A projecting portion is formed at an inner edge portion on the right side surface of the first nozzle ring. The projecting portion is formed on base portions of the multiple guide claws.

Abstract: A diffuser plate for a centrifugal compressor includes an inner edge disposed at an inner diameter about a central axis; an outer edge disposed at an outer diameter, the outer edge displaced an axial distance from the inner edge; a deformable section that includes a substantially S-shaped cross-section, the deformable section disposed between the inner edge and the outer edge; and a spring constant for forced axial displacement of the outer edge with respect to the inner edge, the spring constant characterized, at least in part, by the deformable section.

Abstract: A variable geometry mechanism suitable for use in a gas turbine engine is disclosed in which movable vane segments which are coupled to a rotatable ring, or rings, are used to change an aerodynamic property of a working fluid flowing through the gas turbine engine. The movable vane segments can be rotated through the ring, or rings, between a first position associated with the first vane and a second position associated with a second vane to place the movable vane segments in proximity to one or the other of the first and second vanes of the gas turbine engine. The movable vane segments can be used to alter, among other things, camber, exit flow area, and can be used to influence and/or accommodate such properties as incidence angle, and swirl angle.

Abstract: A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft.

Abstract: A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft.

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: The present invention provides a Francis turbine or any other machine built according to the Francis principle. The machine includes a blade wheel that has multiple blades, with at least one of the blades being adjustable. A spiral housing encloses the blade wheel. A traverse ring with multiple traverses has a portion with larger traverses that extends over a portion of a circumference of the blade wheel and starts at a beginning of a spiral. The traverse ring also has a portion with smaller traverses that extends over a further circumference of the blade wheel up to an end of the spiral. An inner blade wheel ring is provided downstream of the traverse ring. Also included is an outer guide blade ring which is disposed upstream of the traverse ring.

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