Abstract: A variable guide vane (VGV) assembly for a gas turbine engine, has: variable guide vanes circumferentially distributed about a central axis, the variable guide vanes rotatable about respective spanwise axes; and a unison member rollingly engageable to a casing of the gas turbine engine for rotation about the central axis, the unison member operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, the unison member having: a first ring extending around the central axis, a second ring spaced apart from the first ring and extending around the central axis, and connecting members connecting the first ring to the second ring.

Abstract: A gas turbine engine has: an annular gaspath extending around a central axis and defined between a first casing and a second casing; and a variable guide vane (VGV) assembly having: variable guide vanes, the variable guide vanes having airfoils extending between first and second stems at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes; a unison ring rotatable about the central axis, the unison ring operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, and a segmented bushing having bushing segments circumferentially distributed around the central axis, the bushing segments radially supported and axially constrained by the first casing, the unison ring rollingly engaged to the first casing via the bushing segments, the unison ring axially and radially constrained to the first casing via the bushing segments.

Abstract: A variable guide vane (VGV) described herein includes an airfoil for interacting with a fluid inside a gas path of a gas turbine engine. The airfoil is mounted to a button and rotatable with the button about an axis. The button includes a platform surface defining part of the gas path adjacent the airfoil during use. The platform surface of the button includes a depression for receiving therein part of an adjacent VGV and providing clearance between adjacent VGVs at aggressive vane angles.

Abstract: A radial inflow turbine includes a scroll flow passage, a turbine wheel disposed radially inward of the scroll flow passage, a plurality of variable nozzle vanes disposed on a flow passage extending from the scroll flow passage toward the turbine wheel, at a radial position between the scroll flow passage and the turbine wheel, a nozzle mount rotatably supporting each of the plurality of variable nozzle vanes, a nozzle plate arranged to face the nozzle mount and forming the flow passage with the nozzle mount, and a swirl generating member disposed, radially outward of the plurality of variable nozzle vanes, on the nozzle plate in a height range which is smaller than that of a vane height of each of the plurality of variable nozzle vanes. A position of an end part of the swirl generating member on a side of the nozzle mount is farther away from the nozzle mount than a position of an end part of each of the plurality of variable nozzle vanes on the side of the nozzle mount in an axial direction.

Abstract: Methods and systems are provided for a condensation mitigation device. In one example, a system may include a vortex generator arranged in a flow channel of a compressor along with a condensate collection device configured to direct condensate away from compressor blades of the compressor.

Abstract: A fan module includes a fan body and metal plates. The fan body has a fan seat, and the fan seat is provided with coupling holes. The metal plates enclose the fan body and expose an outlet side. The position assembly includes a position frame and position members. The position frame has an air outlet and is fixed on the outlet side. The airflow shielding structure includes shutter plates and a connection rod. One side of the shutter plates are pivoted at the position frame, and the shuttle plates are capable of turning simultaneously for opening and closing the air outlet so as to maintain the normal operation of the server fan.

Abstract: The proposed solution relates to a stator vane assembly for an engine, having at least one stator vane of a stator vane row and a casing for the at least one stator vane row, wherein the at least one stator vane is mounted adjustably on the casing by means of a bearing journal, which is rotatably mounted in a bearing opening in the casing and passes through this bearing opening along a longitudinal axis. A section of a sealing element, on which at least one sealing ridge extending radially in relation to the longitudinal axis is formed and/or which has a nonlinear slot passing longitudinally through the section, is provided within the bearing opening.

Abstract: A turbine assembly includes a turbine casing, a turbine wheel, vanes, and link plates. The turbine casing defines a center chamber and a volute configured to transport exhaust gas to the center chamber. The turbine wheel is disposed within the center chamber and is rotatably coupled to the turbine casing. The driving ring extends around a periphery of the center chamber and is rotatably coupled to the turbine casing. The vanes are disposed within the center chamber and are configured to adjust a flow rate of exhaust gas from the volute to the turbine wheel. The link plates couple the vanes to the driving ring such that the vanes pivot when the driving ring rotates. When the ring is rotated to a given position, the link plates are configured to pivot one of the vanes to one position while pivoting another one of the vanes to another position.

Abstract: A turbocharger includes: a nozzle drive mechanism for driving a plurality of nozzle vanes; and a support ring for holding the nozzle drive mechanism, the support ring having a main body portion having a heat shielding portion facing a turbine impeller in a direction of a rotational axis of the turbine impeller.

Abstract: In some examples, the disclosure describes an accelerometer including a proof mass, and a housing enclosing the proof mass. The accelerometer includes a cold temperature sink defining a condensing surface. In some examples, the disclosure describes a technique for making an accelerometer. The example technique includes forming a cold temperature sink defining a condensing surface, and enclosing a proof mass in the housing. The condensing surface is configured to promote at least one of condensation or ice formation in an interior of the housing. The condensing surface is spaced from the proof mass to divert at least one of condensate or ice away from the proof mass.

Abstract: A turbine having variable turbine geometry for use in a combustion engine. The turbine includes a bearing housing, a turbine housing and a cartridge, which features a vane bearing ring for supporting a plurality of adjustable vanes. The turbine further includes at least one of a separator disc and a shield ring arranged radially outward of the vane bearing ring.

Abstract: An angular pitch control ring (8) of stator vanes (2), the rotations of which are controlled by a mechanism (6) applying a thrust tangent to the ring (8), is also moved in translation when it is displaced, making it touch the stator (2). According to the invention, one lateral region (13) on one side of the mechanism (6) is constructed to be stiffer than the other region to take account of the larger forces that the mechanism (6) must apply in a direction of movement. Application to turbomachines.

Abstract: A stage of variable-pitch vanes for a turbine engine includes a plurality of vanes. Each vane has a blade with a first radially internal frusto-conical surface. The cone angle of the first frusto-conical surface is radially flared inwards and is configured to interact with an internal frusto-conical surface of a first frusto-conical bushing. The vane further includes a second radially external frusto-conical surface with cone angle that is radially flared outwards and is configured to interact with an internal frusto-conical surface of a second substantially frusto-conical bushing.

Abstract: A variable vane cascade for a turbomachine, in particular for a compressor stage or turbine stage of a gas turbine, having at least one first vane, in particular guide vane that has a first distance from a circumferentially adjacent vane, at least one second vane, in particular guide vane that has at least one second distance from at least one circumferentially adjacent vane that is smaller than the first distance, and an actuating device, in particular for jointly and/or reversibly adjusting the first and second vane from a first position where at least one airfoil cross section of the first vane and an airfoil cross section of the second vane each have a first stagger angle, into a second position where these airfoil cross sections have second stagger angles, the second stagger angle of the first vane differing from the second stagger angle of the second vane, in particular being larger than the second stagger angle of the second vane.

Abstract: A centrifugal fan includes: an impeller configured to suction or discharge air; a motor configured to rotate the impeller; a housing configured to accommodate the impeller and have a suction port through which air is suctioned by rotation of the impeller and a discharge port through which air is discharged by rotation of the impeller; and a cut-off portion formed on one side of the discharge port. A flow cross-sectional area of air flowing in the housing is gradually increased from the cut-off portion to the discharge port in an air flow direction, and a distance from a lower portion of the impeller to an inner peripheral surface of the housing in a rotational axis direction of the impeller is gradually increased in at least a portion from the cut-off portion to the discharge port in the air flow direction.

Abstract: A bellcrank assembly for variable vane assembly of a gas turbine engine includes a first bellcrank segment. Also included is a second bellcrank segment. Further included is a bolt extending through respective interior barrels defined by the first and second bellcrank segments to couple the first and second bellcrank segments to each other. Yet further included is a torque frame wall defining an aperture, the bolt extending through the aperture.

Abstract: A turbofan engine includes a fan section. A core engine section drives the fan section. An outer nacelle surrounds the fan section and defines a radially outer surface of a fan duct. An inner nacelle surrounds the core engine section and defines a radially inner surface of the fan duct. A nozzle is disposed at a terminal end of the outer nacelle that defines an exit area for bypass air flow through the fan duct. The nozzle includes a convergent portion forward of a divergent portion and a turning angle for the divergent portion greater than about 12 degrees. A nacelle assembly and method are also disclosed.

Abstract: It is intended to provide a seal ring mounting method for a turbocharger and a turbocharger with the seal ring, whereby the seal ring is less likely to be affected by other parts. An annular protrusion (12j) for restricting a position of a seal ring (16) in the radial direction is provided at a tip portion (12h) of an inner peripheral wall (12b) of a turbine housing (12), and the seal ring (16) is mounted between a side surface (36c) of a nozzle plate (36) and a first step portion (12k) of the tip portion (12h) of the inner peripheral wall (12b) so that the outer periphery of the seal ring (16) is restrained by the annular projection (12j).

Abstract: An assembly for controlling variable pitch vanes in a turbine engine, the assembly comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes. The actuating ring is configured to rotate around the casing. The assembly further includes a passive element including a first end sliding connected to a second end. The first end is connected by a sliding pivoting link on the actuating ring, and the second end is connected by a ball-joint link to the casing.

Abstract: A device and method for imparting a negative pre-whirl to an airstream entering a compressor wheel of a turbocharger. Using a plurality of radially positioned vanes through which the airstream to the compressor wheel communicates, a negative pre-whirl is imparted to the airstream entering the compressor wheel from an intake passage. This pre-whirl is imparted by positioning the vanes radially within an engageable ring and curving the vanes in a direction opposite the direction of rotation of the compressor wheel. Performance is further enhanced by a hub centrally positioned with the vanes where the hub includes a cavity sized to encapsulate a compressor nut and eliminate air turbulence therefrom.

Abstract: A method of controlling settings of one or more actuatable gas turbine engine components includes: providing a first matrix which relates reduction in the operational parameter maximum value during the transient manoeuvre to settings of the component(s); providing a second matrix which relates the operational parameter maximum values attained during the transient manoeuvre: time to attain the maximum value after transient manoeuvre initiation, and operational parameter rate of change at the time of the maximum value; monitoring the engine in operation to identify a start of a transient manoeuvre; predicting, on the basis of the second matrix maximum values, an overshoot operational parameter amount during the identified transient manoeuvre and a time the overshoot occurrence; selecting a setting, using the first matrix, to eliminate the predicted overshoot; and applying the setting to the component(s) for a predetermined period around the predicted time of occurrence to reduce or avoid the overshoot.

Abstract: The invention relates to a system for controlling variable pitch blades for a turbine engine, comprising an annular row of variable pitch blades extending about an axis (A) and each comprising a blade connected at the radially outer end thereof to a pivot (20) that defines a substantially radial axis of rotation of the blade and which is connected by a lever (34) to control means (40a, 40b) extending about said axis. The invention is characterized in that said control means include first links (40a) supported by said pivots and second links (40b) extending between said first links, said first and second links extending substantially along a same circumference of said axis and being connected to one another and to actuation means (56).

Abstract: A variable vane assembly includes a variable vane, a trunnion arranged on one end of the variable vane, an inner bushing configured to receive the trunnion in a press fit relationship, and an outer bushing configured to rotatably receive the inner bushing. A retention feature is configured to retain the trunnion axially with respect to the outer bushing. A gas turbine engine and a method of assembling a variable vane assembly are also disclosed.

Abstract: According to one aspect of the present disclosure, a gas turbine engine is disclosed that includes an engine section comprising a plurality of stages of variable vanes, and also includes first and second synchronizing rings (sync-rings). Movement of the first sync-ring adjusts vane angles of a first one of the stages of variable vanes, and movement of the second sync-ring adjusts vane angles of a second one of the stages of variable vanes. At least one sensor is configured to measure a condition of the gas turbine engine. A controller is configured to move the first sync-ring independently of the second sync-ring based on data from the at least one sensor.

Abstract: A system for controlling variable-pitch vanes for a turbine engine, including a control ring having an axis of revolution and, about the axis of revolution, an annular row of connecting rods for connecting the ring to the vanes, each connecting rod including a first end designed so as to be connected to one of the vanes, and a second end which is connected to an elongate shaft which is connected to s the ring. The shaft connected to each connecting rod has an axis of elongation which is inclined relative to a plane extending substantially through the axis of revolution and the connecting rod.

Abstract: A variable vane system includes a first variable vane stage with a multiple of first actuator gears, each of the multiple of first actuator gears mounted to a respective variable vane of the first variable vane stage, and a second variable vane stage with a multiple of second stage actuator gears. Each of the multiple of second stage actuator gears mounted to a respective variable vane of the second variable vane stage, an extended geared unison ring driven by the drive gear, wherein the extended geared unison ring spans at least a first variable vane stage and a second variable vane stage, each of the multiple of first and second stage actuator gears driven by the extended geared unison ring.

Abstract: A blower fan includes a plurality of blades radially extending from a boss provided at the rotary center and spaced apart from each other in the rotational direction, and a ring portion connecting outer peripheral ends of the blades in a ring shape. An inner peripheral wall surface of an end part on an air-flow downstream side of a cylindrical portion is disposed on the outside in a radial direction of the rotary shaft in the blower fan, with respect to an end part on the air-flow downstream side of the ring portion. The end part on the air-flow downstream side of the cylindrical portion is positioned outward in the radial direction of the rotary shaft, as toward the air-flow downstream side. Thus, the blower can prevent the backflow air from being swirled, thereby reducing noise.

Abstract: A variable vane system includes a harmonic drive driven by an actuator, and a drive gear driven by the harmonic drive. A geared unison ring includes an actuator gear rack driven by the drive gear and a multiple of vane gears, each of the multiple of vane gears mounted to one of a multiple of variable vanes, the multiple of vane gears driven by a gear rack of the geared unison ring.

Abstract: An actively morphable vane includes a leading edge, a trailing edge downstream of the leading edge, a tip end, a hub end spaced radially outward from the tip end, a pressure side comprising a pressure surface, and a suction side comprising a suction surface. The pressure surface extends continuously between the tip end, the hub end, the leading edge, and the trailing edge. The suction side is positioned opposite of the pressure side and the suction surface extends continuously between the tip end, the hub end, the leading edge, and the trailing edge. The actively morphable stator vane also includes an actuator in mechanical communication with the tip end. The actuator is operable to selectively morph the actively morphable stator vane between a first configuration and a second configuration. The first configuration is optimized for a first operating condition, and the second configuration is optimized for a second operating condition.

Abstract: The disclosure relates to a supercharged internal combustion with a mixed flow turbine. In one example, a system comprises a mixed-flow turbine having a turbine shaft coupled to a compressor, a plurality of guide vanes arranged in an inlet of the mixed-flow turbine, a plurality of bevel wheels each coupled to a respective guide vane via a respective guide vane shaft, a pinion wheel with a plurality of teeth to mesh with the plurality of bevel wheels, and a pinion drive coupled to one of the bevel wheels.

Abstract: An internal hot gas bypass device coupled with inlet guide vane for centrifugal compressor includes an inlet guide vane assembly, a driving motor assembly and a gas bypass valve assembly. The inlet guide vane assembly further includes a master vane, a plurality of slave vanes, a vane-front fixing ring, a vane-rear fixing ring, a vane-driving ring, a connecting pipe and a vane-opening indicating disk. The driving motor assembly further includes a motor, a driving unit and a motor fixing base. The gas bypass valve assembly further includes a valve, an external fixing-and-guiding ring, an internal fixing-and-guiding ring, a driven element, a spring, a sealing ring, a valve stud and a valve base. The driving motor assembly is connected with the driving unit and the master vane of the inlet guide vane assembly via a connecting rod, and is further connected with the slave vanes of the gas bypass valve assembly.

Abstract: A compressor includes a first stage of stator vanes having a first position and a second group of stator vanes arranged in two or more stages downstream from the first stage of stator vanes, each stage having a respective second position. A first actuator is engaged with the first stage of stator vanes, and a second actuator is engaged with a bar connecting the second group of stator vanes. A method for operating a compressor includes adjusting a first position of a first plurality of stator vanes and adjusting the respective second positions of a second group of stator vanes separately from the first position of the first stage of stator vanes.

Abstract: A turbocharger (100) has an asymmetric, twin scroll volute design, having a first volute (101) and a larger second volute (102). The larger second volute (102) eliminates the need for a wastegate and its associated actuator. The smaller first volute (101) is sized for rapid transients and rated torque, while the second volute (102) is sized such that the turbine inlet pressure is satisfactory for rated power. Furthermore, the turbocharger (100) preferably incorporates a mixed flow turbine wheel (108) rather than a radial wheel, which allows for a larger wheel size to be used while still maintaining inertia. The turbine housing (103) is improved wherein the first and second volutes (101) and (102) are asymmetric with respect to each other and preferably, are leaned toward the bearing housing to match the axial component of the mixed flow turbine wheel inducer (112).

Abstract: A turbo-charging system of an engine comprising: a central body on which a turbine and a compressor, both keyed on a same shaft, are mounted; and at least two flange diffusers connected to two Venturi tubes comprised in the central body and ending with nozzles. The turbocharging system is interposed between the engine air filter and the engine throttle unit, the turbine receiving from the nozzles the engine intaking air at the output of the air filter whose flow determines the handling of the turbine and, through the shaft, of the compressor.

Abstract: A guide mechanism for a gas turbine has a casing supporting on its interior a duct delimited by radially inner and outer duct segments. A variable guide vane located at least partially within the duct can rotate about an axis of rotation to guide flow of a fluid in the duct. The radially inner duct segment is fastened to the guide vane and is retained on the casing element via the guide vane, which is mounted on the casing element via a bushing inserted in the radial direction from outside to inside into a passage opening of the casing element.

Abstract: A control arrangement (1) of an exhaust-gas turbocharger (2), having a bearing bushing (3); having a control shaft (4) which is connected at a first end (5) to a connecting lever (6) and which is guided in the bearing bushing (3); and having a connecting piece (7) which is arranged on the connecting lever (6). The connecting piece (7) is arranged on a lever surface (8), which faces toward the bearing bushing (3), of the connecting lever (6).

Abstract: An actuation linkage assembly may include a first lever arm connected to one end of a shaft, a second lever arm connected at one end to another end of the shaft, a transition linkage connected to the other end of the second lever arm, and a bracket connected to the transition linkage. The transition linkage is configured to connect the bracket on a driver ring and to the shaft to transfer rotational motion about the axis of the shaft, from a linear motion received by an actuator, to a linear motion through the bracket causing rotational motion of the driver ring. The actuation linkage assembly is configured with high mechanical advantage. The actuation linkage assembly can be part of a movable inter-stage vane guide assembly in a compressor such as for example a centrifugal compressor, which may be part of a chiller such as in a HVAC system.

Abstract: An axial-flow compressor with variable stator vanes located at a single stage can be modified by adding variable stator vanes to the axial-flow compressor so that the variable stator vanes are located at a plurality of stages. The axial-flow compressor includes stator vane rows located at the plurality of stages and include the variable stator vanes extending in a radial direction of the axial-flow compressor and rotating around rotary shafts of the variable stator vanes so as to adjust angles of the variable stator vanes; a plurality of rings are connected to the stator vane rows and drive and rotate the variable stator vanes of the stator vane rows that correspond to respective rings; a plurality of levers that correspond to the plurality of rings; a rotary shaft that holds the plurality of levers so as to enable the levers to pivot.

Abstract: A strut-flap vane system for a turbomachine includes a vane strut comprising an airfoil portion and a strut mount extending in a radially outward direction from the airfoil portion. The strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof. The system includes an aft mount portion or portions defining a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder. The strut cylinder defines a cylinder opening and the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the mount portion.

Abstract: A stopper 30 is provided with: a nut-receiving part 44a provided on a heat insulation plate 44 that is attached to an actuator bracket 43; and a movable-side stopper part 33 provided on an actuator rod 26 that moves in relation to the heat insulation plate 44. An actuator 27 is provided with an actuator body 41 that generates driving force, and the actuator rod 26 which transmits the driving force from the actuator body 41. The movable-side stopper part 33 is provided on the actuator rod 26 that extends from the actuator body 41 to the nozzle vane side.

Abstract: A refrigerating apparatus includes a centrifugal compressor, a capacity control mechanism that controls a capacity of the compressor by changing an opening degree of the capacity control mechanism, an expansion mechanism that reduces a pressure of a refrigerant, and a controller. The controller calculates an opening degree of the expansion mechanism using compressor capacity as one of a plurality of indices of change in load. The compressor capacity is obtained from a current rotation number of the compressor, an opening degree of the capacity control mechanism, and a divergence rate of a current operation head from a surge region.

Abstract: The invention relates to a turbine (1), in particular of an exhaust gas turbocharger, having a turbine rotor (4), which is rotatably mounted in a housing (2), with which at least one radial inlet channel (9) for a guide apparatus (7) forming a medium which drives the turbine rotor (4) is associated, wherein said guide apparatus (7) has multiple guide vane bearing rings (10), which radially enclose said turbine rotor (4) and have guide vanes (8) which lie in said inlet channel (9), and a guide vane cover ring (12), and wherein said inlet channel (9) is axially delimited by said guide vane bearing ring (10) and said guide vane cover ring (12) and said guide apparatus (7) is mounted in the housing (2) so it is axially and/or radially movable for material relaxation. Furthermore, the invention relates to an exhaust gas turbocharger, in particular for a motor vehicle.

Abstract: In a scroll structure for a radial turbine configured such that a turbine rotor 02 is rotationally driven by causing exhaust gas to flow from a spiral scroll portion 4 formed in a turbine housing 1 toward a rotor blade 3 of the scroll portion 4 in a radial direction, and act on the rotor blade 3, then flow out in an axial direction, a heat radiation space portion is formed in a shroud portion 11 between the turbine housing 1 and a turbine chamber provided with the rotor blade 3.

Abstract: A vane pack assembly is provided that can remove the spacers between the upper and lower vane rings to a location outside of the exhaust flow through the vane ring. In particular, the spacers are located within the vanes. Further, the assembly can effectively retain the small blocks used in varying the angle of the vanes on their associated vane pivot posts. A vane pack with such a configuration can use inexpensive parts, eliminate the need for welding of the vane pack and/or simplify the vane pack assembly process. Further, the vane pack can be decoupled from the turbine housing, thereby avoiding problems with differential thermal expansion.

Abstract: A multipurpose rotary device includes a rotor configured to include a plurality of blades in a circumferential direction; and a load guide body configured to guide a flow of fluids flowing into the inside of the rotor, wherein the load guide body includes an upper support member and a lower support member configured to be disposed to face each other at the upper and lower sides thereof and connected to one another such that the rotor is rotatably installed; load guide plates configured to correspond to the blades and are rotatably installed between the upper and lower support members in a longitudinal direction; and stop pins configured to be formed on inner surfaces facing the upper and lower support members to control a rotational angle of the load guide plates.

Abstract: Embodiments of the present application include a stall detection system for a gas turbine engine. The system may include a compressor and a number of variable stator vanes associated with the compressor. The variable stator vanes may form one or more variable stator vane stages. The system may also include one or more resolvers associated with one or more of the variable stator vanes. The resolvers may be configured to detect a flutter in an angle of the variable stator vanes. The flutter may be indicative of the onset of compressor stall.

Abstract: An exhaust-gas turbocharger (1) having a turbine (2) which is provided with a variable turbine geometry (18) and/or a wastegate; and having an actuator (11) which is connected to the variable turbine geometry (18) and/or the wastegate via a coupling rod (14; 14?; 14?). The coupling rod (14; 14?) is connected at its end regions (21, 22) at one side to the actuator (11) and at the other side to a pin (19) of an adjusting shaft arrangement (23; 26) of the variable turbine geometry (18) and/or of the wastegate. The pin (19) of the adjusting shaft arrangement (23; 26) is in the form of a bayonet pin, and that end region (22) of the coupling rod (14) which interacts with the pin (19) is in the form of a bayonet receptacle (24; 27) which is matched to the bayonet pin (19).

Abstract: A stator vane adjusting device of a gas turbine has a plurality of stator vanes each rotatable about a radial axis 44 and arranged in at least two radial planes, as well as at least one stator vane adjusting ring connected to the respective stator vanes and rotatable in the circumferential direction by at least one actuating device. The actuating device includes a crankshaft element rotatable about a stationary pivot axis by an actuator. A first lever is articulated by a joint to the stator vane adjusting ring, with its free end being connected by a joint to a center area of a second lever, the second lever being mounted at its one end on a stationary pivot point and at its other end being linked by a joint to a third lever, which is mounted by a joint at its free end on the crankshaft element.

Abstract: A bumper assembly includes a bracket and a pad. The pad is connected to the bracket by a first rivet. Additionally, a synchronizing ring assembly for a gas turbine engine includes a ring section and a bumper assembly. The bumper assembly is connected to a side surface of the ring section and extends axially adjacent an inner radial surface of the ring. The bumper assembly is disposed adjacent a gap at an end of the ring section.

Abstract: In a variable vane drive device of an axial-flow fluid machine, a ring support unit supporting a movable ring includes: a first roller; a first support part supporting the first rollers so as to be relatively immovable with respect to a vane holding ring in a radial direction and in an axial direction; a second roller; a second support part supporting the second roller so as to be relatively movable with respect to the vane holding ring in the radial direction and pressing the second roller in the radial direction; a third roller allowing relative movement of the movable ring in the radial direction and restricting relative movement of the movable ring in the axial direction; and a third support part supporting the third roller so as to be relatively immovable with respect to the vane holding ring in the axial direction and in the radial direction.