Abstract: A turbomachine module with a longitudinal axis comprising an unducted propeller rotated about the longitudinal axis and at least one straightener. The module includes a plurality of unducted variable-pitch stator blades extending along a radial axis, perpendicular to the longitudinal axis, from a fixed casing. The module includes a first stator blade pitch-changing system. The pitch-changing system includes at least one first control that includes a first fixed body connected to the fixed casing and a first body which is axially mobile in relation to the first fixed body and at least one first joining mechanism joining each stator blade to the first mobile body of the first control. The first joining mechanism includes: a joining ring centered on the longitudinal axis, joined to the feet of each stator blade and at least one lever joined, on one hand, to the joining ring and, on the other hand, to the first mobile body of the first control.

Abstract: A system includes a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an inner exhaust wall radially disposed along the exhaust flow path and an outer exhaust wall disposed along the exhaust flow path and radially outward from the inner exhaust wall. The turbine exhaust section includes an inner flow control vane configured to selectively extend radially outward from the inner exhaust wall. An inner radial extent of the inner flow control vane is less than a radial distance between the inner exhaust wall and the outer exhaust wall. The inner flow control vane is disposed downstream of a last stage blade of a turbine and upstream of an exhaust diffuser strut of the turbine exhaust section.

Abstract: A system includes a turbine exhaust section having an exhaust flow path, an inner exhaust wall radially disposed along the exhaust flow path, an outer exhaust wall disposed radially outward of the inner exhaust wall and along the exhaust flow path, and a flow control vane extending between a first end and a second end. The first and second ends are circumferentially offset from one another. The flow control vane is configured to move between a retracted position along the outer exhaust wall and an extended position extending from the outer exhaust wall toward the inner exhaust wall. The second end is disposed radially inward from the first end while the flow control vane is disposed in the extended position.

Abstract: Example variable geometry systems with split actuation are disclosed herein. In one example, a compressor is provided that includes a compressor stage and an actuation system. The compressor stage includes a plurality of variable stator vanes arranged along a circumference of the compressor stage. The actuation system is to actuate a first variable stator vane of the compressor stage according to a first schedule and to actuate a second variable stator vane of the compressor stage according to a second schedule.

Abstract: Variable geometry turbines having a turbine housing with an inlet and an outlet, a turbine wheel rotatably mounted between the inlet and the outlet, a movable wall member having an inlet passageway between the inlet of the turbine housing and the turbine wheel, and a plurality of vanes circumferentially spaced and extending across the inlet passageway, the plurality of vanes having a specified shape. Methods for designing configurations of vanes for variable geometry turbines.

Abstract: A centrifugal compressor assembly is provided. The centrifugal compressor assembly includes a scroll assembly having a suction plate defining an inlet fluid passage, a suction plate housing, a diffuser plate, and a collector. The suction plate is detachably coupled to the suction plate housing, the suction plate housing is detachably coupled to the collector, and the diffuser plate is detachably coupled to the collector. The centrifugal compressor assembly further includes an impeller rotatably mounted in the scroll assembly for compressing fluid introduced through the inlet fluid passage, and a variable geometry diffuser system.

Abstract: The present invention relates to an adjustment assembly for the adjustment of adjustable blades or vanes of a turbomachine, having an adjustment ring for coupling to the adjustable blades or vanes of a blade or vane ring and having an adjusting mechanism, which has a coupling rod for coupling to a further blade or vane ring as well as a lever and a push rod, wherein the lever is rotatably mounted at a pivot and has a load arm as well as a force arm, wherein the load arm of the lever is coupled to the push rod and its force arm is coupled to the coupling rod, on different sides of the lever, so that an offset of the coupling rod via the lever and the push rod is converted to a rotation of the adjustment ring around the ring axis thereof.

Abstract: An inlet guide vane assembly for a centrifugal compressor includes a plurality of guide vanes, a drive structure coupled to the plurality of guide vanes, an actuator; and an actuation mechanism. Rotation of the drive structure is transitions the plurality of guide vanes from a first position to a second position. The actuation mechanism causes the drive structure to transition the plurality of guide vanes between the first and second positions based on operation of the actuator. The actuation mechanism imparts a first amount of rotational force to drive the drive structure when the guide vanes are in the first position, and a second amount of rotational force when the guide vanes are in the second position. The actuation mechanism provides a mechanical advantage to the actuator when the guide vanes are in the first positions as compared to when the guide vanes are in the second position.

Abstract: A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan includes blades adapted to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air received from the blades. The outlet guide vane assembly includes a first plurality of outlet guide vanes including a first outlet guide vane configured to rotate to a first angle so as to redirect the fan exit air in a first direction and a second outlet guide vane configured to rotate to a second angle so as to redirect the fan exit air in a second direction. The second outlet guide vane is located at a different circumferential position than the first outlet guide vane.

Abstract: A fan assembly includes a fan duct, an inlet fan, and an outlet guide vane assembly. The inlet fan includes blades adapted to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air received from the blades. The outlet guide vane assembly includes a first plurality of vanes configured to rotate to redirect the fan exit air in a first direction, and a second plurality of vanes located downstream of the first plurality of vanes. The second plurality of vanes are configured to rotate to redirect the fan exit air flowing in the first direction in a second direction to minimize losses created by distortions in fan inlet air and created by the first vanes.

Abstract: A centrifugal compressor assembly is provided. The centrifugal compressor assembly includes a scroll assembly having a suction plate defining an inlet fluid passage, a suction plate housing, a diffuser plate, and a collector. The suction plate is detachably coupled to the suction plate housing, the suction plate housing is detachably coupled to the collector, and the diffuser plate is detachably coupled to the collector. The centrifugal compressor assembly further includes an impeller rotatably mounted in the scroll assembly for compressing fluid introduced through the inlet fluid passage, and a variable geometry diffuser system.

Abstract: A turbine which uses fluid pressure to turn a shaft in a manner that does not allow for cavitation to be created.

Abstract: A method of maintaining at least one gas turbine engine includes monitoring a compressor of the gas turbine engine. The compressor includes a compressor case at least partially defining a flow path, a plurality of stages and a vane actuator system configured to move at least one of the stages. The vane actuator system includes a vane mover having one or more slots formed therein and configured to actuate the at least one stage. The vane mover may be replaced after the gas turbine engine has experienced engine degradation.

Abstract: Centrifugal compressors can incorporate a side stream flow of intermediate pressure vapor between stages of that compressor. The side stream flow can be controlled by a side stream injection port controlled by a throttle ring disposed between stages of the compressor. The throttle ring can allow or obstruct flow through the side stream injection port. The throttle ring can extend and retract in a direction substantially perpendicular to the direction of flow from the first stage impeller to the second stage impeller. A method of operating a centrifugal compressor can include actuating a throttle ring by rotating a drive ring to adjust a flow of interstage fluid into the second stage impeller.

Abstract: A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The vanes are formed with a leading portion which is arranged to contact a leading portion of a corresponding slot, and a trailing portion which is shaped, when the leading portion of the vane and slot are together, to be spaced from a corresponding trailing portion of the slot with a substantially constant spacing at room temperature. The contact may be a point contact, e.g. close to the leading edge of the vane. Alternatively, the vane may include a leading surface portion which conforms closely with the shape of a corresponding leading surface portion of one of the slots.

Abstract: A lamination forming system includes a melt extruder, a nozzle head and a carrier unit. The melt extruder is configured to melt a plastic raw material into a plastic melt and to deliver the same. The nozzle head includes a sprue channel that has an inlet connected to the melt extruder for entry of the melt plastic into the sprue channel, and an outlet disposed distally from the inlet to deliver the plastic melt from the sprue channel. The carrier unit includes a slide table controllable to move relative to the nozzle head. The slide table is configure to carry the plastic melt outputted from the nozzle head.

Abstract: A centrifugal compressor for an aircraft engine is disclosed, having an impeller mounted for rotation about an axis. The impeller has impeller blades extending from an inducer end to an exducer end. A shroud extends over the impeller blades. A main flow passage is defined between the shroud and the impeller, a cavity fluidly communicates with the main flow passage via at least one extraction port and at least one reinjection port. The reinjection port is fluidly connected to the main flow passage upstream of the extraction port relative to a flow direction through the main flow passage. The reinjection port is disposed upstream of the exducer end of the impeller blade, in an exducer portion of the shroud.

Abstract: An exhaust turbocharger includes an air-guiding section. A spiral channel is formed downstream of a wheel chamber in the air-guiding section. Between the wheel chamber and the spiral channel, a diffuser channel is formed in the air-guiding section. Upstream of the wheel chamber, an inlet channel is formed in the air-guiding section for the inflow of fluid to be compressed. In the inlet channel, a cross-section-changing unit. The cross-section-changing unit comprises an operating element with at least two movable element parts to produce a baffle which can protrude, with the aid of an adjusting unit, into the inlet cross-section rotationally and/or in a translational manner or can be removed from the inlet cross-section. The two element parts are fixedly disposed at one element end jointly in the air-guiding section. A relative movement of the element parts can be brought about in particular in an opposing direction.

Abstract: One aspect of an electric actuator of the disclosure includes: a motor having a motor shaft rotating about a central axis; a speed reduction mechanism connected to a portion on one side in an axial direction of the motor shaft; a case accommodating the motor and the speed reduction mechanism; an output part to which rotation of the motor shaft is transmitted via the speed reduction mechanism; a rotation detector having a rotation sensor detecting rotation of the output part; and a wiring member electrically connected with the rotation sensor. The case has a first concave part located on an outer surface of the case. One end part of the wiring member penetrates the case from inside the case and protrudes inside the first concave part. The rotation sensor is located inside the first concave part and connected with one end part of the wiring member.

Abstract: A link setting assembly according to an exemplary aspect of the present disclosure includes, among other things, a fixture including at least one platform mount and at least one linkage mount. The at least one linkage mount is spaced-apart from the platform mount by a distance corresponding to a predetermined link length.

Abstract: A steam turbine exhaust chamber defining therein an exhaust passage through which steam having passed through a last-stage blade of a steam turbine is introduced to a condenser includes: a casing including an outer peripheral wall portion formed on an outer peripheral side of the exhaust passage; a bearing cone disposed on a radially inner side of the outer peripheral wall portion; and at least one bypass passage carrying a part of steam flowing through the exhaust passage from a high-pressure portion of the exhaust passage to a low-pressure portion of the exhaust passage or to the condenser, The at least one bypass passage includes a high-pressure-side opening formed in the bearing cone and a low-pressure-side opening facing steam having a lower pressure than steam facing the high-pressure-side opening.

Abstract: A gravitational vortex variable flow energy system (GVvFES) is disclosed. An example embodiment includes: a turbine basin having an inlet portion and an outlet portion, the turbine basin having a hybrid conical shape; a generator installed adjacent to the turbine basin; a turbine blade hub having turbine blades attached thereto, the turbine blade hub being coupled to the generator with a turbine blade axle, the turbine blade hub being configured to achieve a variable and configurable height relative to a top of the turbine basin; and a diffuser installed beneath the outlet portion of the turbine basin, the diffuser being configured to achieve a variable and configurable height relative to a bottom of the turbine basin. An example embodiment also includes linkage to vary an angle or pitch of the turbine blades.

Abstract: A variable turbine and/or compressor geometry for an exhaust gas turbocharger may include an adjusting ring for simultaneously adjusting a plurality of guide vanes. The adjusting ring may be operatively connected to an articulated lever via a first contact surface and to an associated adjusting lever of the plurality of guide vanes via a second contact surface. The adjusting ring may include, at least in a region of the first contact surface, an additional component which is pressed into the adjusting ring and which increases the first contact surface operatively connected with the articulated lever.

Abstract: A cam isolation system for a gas turbine engine compressor actuator includes a torque tube. The system also includes a cam bracket operatively coupled to an engine case structure, the cam bracket defining a slot. The system further includes an actuator bracket operatively coupled to the torque tube at a first end of the actuator bracket, the actuator bracket having a pin disposed within the slot of the cam bracket.

Abstract: An alignment apparatus for aligning inlet guide vanes in a turbine having a turbine axis includes a tool body, a positioning block secured to the tool body, and a plurality of alignment pieces secured to the tool body. The positioning block may be affixed to the tool body such that when the positioning block is engaged with a leading edge of one of the inlet guide vanes, at least a portion of the alignment pieces is parallel to the turbine axis. The alignment pieces may be manually displaceable from the OFF position to the ON position into engagement with the inlet guide vanes to align one or more of the inlet guide vanes.

Abstract: A variable diffuser comprises a passage, at least two vanes disposed within the passage, and at least two pennies. The passage is defined between opposing disk faces of a hub and a tip. Each of the vanes comprises a body having a leading edge and a trailing edge. The body extends between the hub face and the disk face. Each of the pennies is coupled to a respective vane body near an edge of the penny and an actuator. Rotation of at least one penny changes the orientation of the respective vane relative to the hub face.

Abstract: A system for operating a turbo machine is generally provided, the system including a variable vane assembly including a first plurality of vanes coupled together by a first unison member and a second plurality of vanes coupled together by a second unison member. An actuation system is coupled to each of the first unison member and the second unison member and a solenoid actuator is coupled to the variable vane assembly and the actuation system.

Abstract: A motor stator frame including two plates in cast iron; at least one steel bar connecting both plates, each bar having two threaded ends; and at least one threaded bushing. Where each of the plates has at least one orifice being used as a seat for each threaded bushing the threaded ends of each bar being engaged into the threaded bushings.

Abstract: A turbine engine is provided. The turbine engine includes a plurality of first stator vanes, a plurality of second stator vanes, and a pitch adjustment system coupled to the first stator vanes and the second stator vanes. The pitch adjustment system includes a pivot shaft, a first linkage, and a second linkage. The pivot shaft has a first side and a second side opposite the first side. The first linkage is coupled to the first stator vanes on the first side of the pivot shaft. The second linkage coupled to the second stator vanes on the second side of the pivot shaft.

Abstract: A variable stator guide vane system for a gas turbine engine comprises a set of vanes circumferentially distributed around a central axis and rotatably mounted for rotation about respective spanwise axes. A ring gear is rotatably mounted about the central axis. Pinion gears are operatively coupled to respective ones of the vanes and in driving engagement with the ring gear. Biasing members individually bias the pinion gears in meshing engagement with the ring gear.

Abstract: A system for controlling the geometry of a variable geometry compressor. The system having: a mechanical linkage operable to vary the compressor geometry; a first fluid-powered actuator arranged to operate the linkage and configured to be powered by a pressurized supply of an incompressible fluid; and a second fluid-powered actuator arranged to operate the linkage and configured to be powered by a pressurized supply of a compressible fluid. Wherein the first and second actuators are further arranged to operate in combination on the mechanical linkage such that a first actuator force exerted by the first actuator on the mechanical linkage sums with a second actuator force exerted by the second actuator on the mechanical linkage.

Abstract: A turbine 28 for an exhaust-gas turbocharger, having a turbine housing 2, a drum 11 arranged in the turbine housing 2 and rotatable about an axis of rotation 12, a turbine wheel 5 arranged rotatably in the drum 11, at least one volute 16, 17 formed in the turbine housing 2, at least one aperture 14, formed in the drum 11, for conducting a gas flow from the at least one volute 16, 17 to the turbine wheel 5, an inlet cross-sectional area Av of the volute 16, 17 being variable by changing an angle of rotation v of the drum 11 relative to the turbine housing 2, and the drum being mounted in the turbine housing 2 by way of bearing elements 19.

Abstract: In a variable nozzle unit, at a position located away from and opposed to a first nozzle ring in a right-left direction, a second nozzle ring is provided integrally with the first nozzle ring through multiple connecting pins arranged in a circumferential direction. An inner edge portion of a support ring is connected to the first nozzle ring by riveting of one end portions of the multiple connecting pins. Each pin hole in the support ring is formed into such a shape extending in a radial direction of the support ring. A washer is provided between a rim of each pin hole in the support ring and a rivet head brought about by joining of the end portion of the corresponding connecting pin.

Abstract: Systems and methods include an actuation system of turbomachinery includes a first actuator configured to control pitch of vanes of the turbomachinery and a first positioner configured to position the first actuator to control the pitch of the vanes. The actuation system also includes a second actuator configured to control the pitch of the vanes of the turbomachinery and a second positioner configured to position the second actuator to control the pitch. The actuation system also includes a controller system communicably coupled to the first and second positioners where the controller system is configured to drive the first positioner in an operation mode based at least in part on a set point. The controller system is also configured to set the second positioner in a diagnostic mode and obtain data from the first positioner and the second positioner where the data indicates operating conditions of the turbomachinery.

Abstract: A turbocharger includes a waste gate valve, a compressor, a turbine, a turbine housing which houses the turbine, a bypass channel which bypasses the turbine, a bypass channel section arranged in the turbine housing, an actuator housing which has a separate coolant channel, an electric motor arranged in the actuator housing, a transmission which has an output shaft, a control body coupled to the output shaft, and an actuator cover. The transmission is arranged in the actuator housing. The actuator housing is detachably secured to the turbine housing. The control body controls an opening cross-section of the bypass channel. The separate coolant channel of the actuator housing surrounds a circumference of the transmission and is closed axially by the actuator cover.

Abstract: A variable geometry turbine has annular inlet passageway defined between a first surface of a radial wall of a movable wall mounted within a cavity and a facing wall of the turbine housing. The radial wall defines a second surface that opposes the first surface. The moveable wall member comprises an annular flange that extends axially into the cavity and supports a radial flange defining opposing third and fourth surfaces. The radial flange seals against an annular sleeve in the cavity to define a first area within the cavity which includes the radial second and third surfaces and a second area within the cavity which includes the radial fourth surface. The first and second areas are in fluid communication with regions of the annular inlet passageway which are respectively upstream and downstream of a radial vane passage.

Abstract: A measuring system for sensing vane positions that comprises a turbine, a target, and a sensor. The turbine includes a plurality of articulating vanes, with each vane being coupled to a sync ring that is configured to position the plurality of articulating vanes in accordance with a degree of rotation by the sync ring. The target is coupled to a first position of the turbine within a first region that is associated with a first vane of the plurality of articulating vanes. The sensor is coupled via a bracket to a second position of the turbine within the first region. The sensor is configured to detect an orientation of the target that corresponds to a vane position of the first vane.

Abstract: A gas or steam turbine is disclosed herein. The turbine may include a throat area formed between adjacent buckets. The turbine also may include a variable throat device associated with at least one of the adjacent buckets. The variable throat device may be configured to vary the throat area between the adjacent buckets for improved part load performance.

Abstract: An exhaust-gas turbocharger (1) having a turbine (2) which has a turbine wheel (3) surrounded by an inflow duct (4), and having a VTG cartridge (5), which VTG cartridge has a disk and a vane bearing ring (7) which delimit the inflow duct, and which VTG cartridge has a multiplicity of vanes (6) which are arranged in the inflow duct (4) and which are mounted in the vane bearing ring (7) by way of rotatable vane shafts (9), which vane shafts are connected to vane levers (10), the lever heads (11) of which engage into associated grooves (12) in an adjusting ring (13). The adjusting ring (13) is guided by at least one bearing (8) which is arranged on one of the vane shafts (9).

Abstract: A bearing housing (1) of an exhaust-gas turbocharger, having a compressor-side housing flange (2), a central housing section (3) which is integrally connected to the housing flange (2) and in which a first partial section (4) of an oil chamber (5) is arranged; and a turbine-side housing section (6) which has a turbine-side housing flange (7) and in which a second partial section (8) of the oil chamber (5) is formed. The central housing section (3) and the turbine-side housing section (6) are formed in one piece. A bearing housing (9) which forms a separate component is inserted into the central housing section (3) and into the turbine-side housing section (6), with these delimiting the oil chamber (5).

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: Systems and methods involve controlling a variable-speed blower in a heating, ventilating, and air conditioning (HVAC) system to ensure the setting of a blower-proving switch to confirm airflow in a building. In one instance, a method involves ramping up the variable-speed blower so that the associated static pressure reaches a making point pressure of the blower-proving switch and then reducing the power to a desired power level. The method may also include maintaining the power level above a breaking point pressure. Other systems and methods are presented.

Abstract: A variable geometry turbine comprises: a turbine wheel in a housing assembly defining a radial gas flow inlet passage; an annular wall member which is displaceable to control gas flow through the inlet passage; and a linkage mechanism comprising at least one actuating member operably connected to the annular wall member to control displacement of the wall member. The actuating member has a terminal portion defining a radially extending flange and extends in a direction substantially parallel to the turbine axis through an aperture defined by a retaining member to locate the radially extending flange in between said retaining member and annular wall member. The terminal portion is contacted by the retaining member to connect the actuating member to the annular wall member. The aperture defines a clearance to accommodate displacement of the retaining member relative to the actuating member.

Abstract: A sensor assembly includes a first structure and a second structure disposed radially outwardly of the first structure. Also included is a sensor body extending through the first and second structures, the sensor body having first and second ends, the second end disposed in an ambient environment. Further included is a first sealing assembly configured to couple the sensor body to the second structure and to accommodate movement of the sensor body due to relative movement between the first and second structures. Yet further included is an interior cavity defined by an interior wall of the sensor body and a rotary position sensor mounted to the sensor body proximate the second end of the sensor body, the rotary position sensor configured to detect an angular position of a target disposed within the first environment, the rotary position sensor coupled to the target with a sensor linkage assembly.

Abstract: An inlet guide vane device having a central axis comprises a first base, a guide sleeve, a blade, a second base, a transmission disk, and an actuator. The first base has at least one first support groove and at least one guide groove. The first support groove extends along a radial direction of the central axis, and the at least one guide groove is located in the first support groove. The guide sleeve is disposed on the first support groove in a manner that the guide sleeve is capable of moving along the radial direction. The guide sleeve has a sliding sleeve, an upper guide post and a lower guide post, the sliding sleeve has a through hole extending along the radial direction. The upper guide post and the lower guide post pass through the sliding groove, and the lower guide post is movably disposed on the guide groove.

Abstract: Embodiments related to wind turbines and methods of guiding a flow of a fluid using a wind turbine. In one embodiment, a wind turbine includes a framework including an annular upper guide means and an annular base guide means; and an annular rotor assembly surrounding a central space, the rotor assembly comprising a plurality of rotor vanes, each rotor vane being held in position between the upper guide means and the base guide means.

Abstract: A variable geometry turbine for turbochargers in exhaust gas recirculation engines incorporates a turbine housing having an exhaust inlet with a first side receiving exhaust from cylinders having exhaust gas recirculation (EGR) and a second side receiving exhaust from non-EGR cylinders. The first side has a first EGR-driving passage and a second EGR-driving passage and the second side having a first non-EGR-driving passage and a second non-EGR-driving passage. A first control valve is associated with the second EGR-driving passage and a second control valve is associated with the second non-EGR-driving passage. A controller is adapted to control the first and second control valves.

Abstract: An assembly including an intermediate case of a bypass turbojet engine and of an inter-jet case extending upstream of the intermediate case to separate a primary air jet of the turbojet engine from its bypass air jet, the inter-jet case including, passing through it, a closable duct for diverting part of the primary flow to the bypass flow thereby forming a blow-off valve for the LP compressor, the intermediate case including arms passing across the bypass flow and the inter-jet case in its internal cavity including a first chamber situated upstream of the arms and a second chamber situated level with the arms, the duct being open or closed off by an annular component capable of axial movement set in motion by an arm that can rotate about a fixed pivot under action of a control cylinder, the cylinder being positioned in the second chamber.

Abstract: A variable-vane assembly has a nozzle ring supporting an array of pivotable vanes, and a unison ring for pivoting the vanes in unison. A crank mechanism rotatably drives the unison ring, and includes an external crank assembly positioned radially outward of the unison ring, a non-round drive block disposed in a non-round recess in an outer periphery of the unison ring, and a crank arm having a forked end connected to the drive block and an opposite end connected to the external crank assembly. The forked end defines two legs and the drive block is disposed between the legs and is pivotally connected to the legs such that the drive block is pivotable relative to the crank arm about a pivot axis. The crank mechanism is arranged such that the crank arm is caused to swing through an arc of movement, thereby rotating the unison ring.

Abstract: An assembly includes a synchronizing ring, a vane arm, and a multi-axis joint. The multi-axis joint connects the synchronizing ring to the vane arm and provides the vane arm with movement about a first pivot axis and a second pivot axis.