Abstract: A spring (15) of angular shape is placed between the lug (17) of a connecting rod (10) controlling the orientation of a stator blade and the pivot (3) of said blade, such that its edge (18) bends against one edge face (19) of the connecting rod (10) and the washer (16) moves the pivot (3) in the play of the bore (21) of the connecting rod and sets and maintains the contact between two plane faces (12 and 13), so as to reduce the differences in angular displacements between the connecting rod and pivot due to the play remaining in the bore (21).

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

Abstract: A turbine in which a turbine wheel is mounted in a housing between an inlet and an outlet. Rotatably mounted vanes are located in the inlet and coupled by linkages to an actuator which is displaceable relative to the vanes so as to control the angular orientation of the vanes relative to the housing inlet. Each vane is coupled to the actuator by a flexible link, the ends of the link being secured to the vanes and actuator in a manner which prevents relative movement between the link ends and the vane or the actuator. Flexing of the links thus accommodates the rotation of the vanes which results from actuator displacements.

Abstract: The present invention relates generally to systems and methods for facilitating the movement of fluids, transferring mechanical power to fluid mediums, as well as deriving power from moving fluids. The present invention employs an impeller system in a variety of applications involving the displacement of fluids, including for example, any conventional pumps, fans, compressors, generators, circulators, blowers, generators, turbines, transmissions, various hydraulic and pneumatic systems, and the like.

Abstract: A method enables a variable vane assembly for a gas turbine engine to be coupled to an engine casing. The variable vane assembly includes a bushing assembly and at least one variable vane that includes a platform and a vane stem. The method comprises coupling a first bushing to the engine casing in a press fit, coupling a second bushing to the variable vane, and coupling the variable vane to the engine casing such that at least a portion of the first bushing is between the engine casing and the second bushing, and such that at least a portion of the second bushing is between the first bushing and the vane stem.

Abstract: A turbine comprises a turbine wheel having radial blades and supported in a housing for rotation about an axis. An annular inlet passageway extends radially inwards towards the turbine wheel, the inlet passageway being defined between first and second facing annular walls. An annular array of vanes extend across the inlet passageway. Each vane has a trailing edge extending adjacent the turbine wheel blades, wherein the trailing edge of each vane deviates from a straight line over at least a portion of its length defined between its ends.

Abstract: A guiding grid of variable geometry for turbines comprises a turbine housing and a plurality of guiding vanes in the housing in angular distances around a central axis. Each vane is pivotal about an associated pivoting axis to assume different angles in relation to the central axis and, thus, to form a nozzle of variable cross-section between each pair of adjacent vanes. A generally annular nozzle ring supports the adjustment shafts of the guiding vanes. A unison ring is displaceable around the central axis relative to the nozzle ring. This unison ring is operatively connected to the vanes via a transmission mechanism in order to pivot them when being displaced to adjust their respective angular position in relation to the central axis. The transmission mechanism comprises a first transmission element with an opening and a second transmission element slidably engaging this opening.

Abstract: A bushing and washer forming a bearing assembly at the outer radial end of a stator vane, the outer bearing assembly, and the bearing assembly at the inner radial end of the stator vane, the inner bearing assembly, that facilitate durability, effectiveness and reduced cost. Both the inner and outer bearing assemblies are designed to rotate relative to the vane shaft and the respective mating shroud or case to even out the wear around the circumference of the bushing. However, the bushing is designed so that if the relative wear rate between the bushing material and the vane or the shroud/case is high, the bushing will not rotate relative to that material. When a rotating bushing is used, a flange on the bushing is designed to be positioned on the inside of the case, so that a pressure differential across the case applies a force to the vane to move it outwardly against the flange and the flange against the case, thereby minimizing air leakage.

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

Abstract: The present invention relates to a bumper system for use with a compressor variable vane system. The bumper system broadly comprises a synchronizing ring, a bumper, a shim for defining a gap between a bumper pad and the bumper, a pin for preventing rotation of the bumper relative to the synchronizing ring, and a device for fully trapping the shim. In a first embodiment, the device for fully trapping the shim comprises a sleeve passing through the synchronizing ring. In a second embodiment, the device for fully trapping the shim comprises a pin which passes through the synchronizing body. In a third embodiment, the device for fully trapping the shim comprises a fastener with a shoulder.

Abstract: A stator of a variable-geometry axial turbine for aeronautical applications has an axis an is provided with an annular duct that has a diameter increasing along the axis, is delimited radially by an outer surface and by an inner surface and houses an array of air foil profiles; the profiles are rotatable relative to the outer and inner surfaces about respective axes of adjustment incident to the axis of the stator and each have an associated pair of end edges opposite each other and each slidably at a predetermined clearance from an associated shaped zone of the outer and inner surfaces, each shaped zone has a form complementary to an ideal surface generated by rotation of the associated end edges about the axis of adjustment so as to maintain a constant clearance between the profiles and the inner and outer surfaces.

Abstract: A method enables a variable vane assembly for a gas turbine engine to be coupled to an engine casing. The variable vane assembly includes a bushing assembly and at least one variable vane that includes a platform and a vane stem. The method comprises coupling a first bushing to the engine casing in a press fit, coupling a second bushing to the variable vane, and coupling the variable vane to the engine casing such that at least a portion of the first bushing is between the engine casing and the second bushing, and such that at least a portion of the second bushing is between the first bushing and the vane stem.

Abstract: A flexible rod (20) is articulated at a first end to a control ring (30) and is fixed at a second end to a pivot of a blade (10) that is to be controlled. At this second end, it is held so that it can rotate without play on the blade pivot by a holding device (44; 52; 54). The articulation device comprise a pivot (24) passing through a first orifice (22) pierced in this first end and engaged in a radial housing (28) of the control ring, the pivot being held in position by a locking ring (34) which has openings (36) for the passage of this pivot and which slides on this control ring. The fixing device comprise a fixing screw (40) passing through a second orifice (38) pierced in the second end of the rod and introduced into a hole (42) of the pivot of the blade that is to be controlled.

Abstract: A vane for a stator of a variable-geometry turbine, in particular for aeronautical engines, has an airfoil profile and a pair of hinge portions, which are carried by the airfoil profile and enable the airfoil profile to be coupled to a support structure of the stator so as to be rotatable about an axis of adjustment; the vane also has internal channels that allow a flow of air to pass through in order to cool the hinge portions.

Abstract: A trunnion support for a variable-position stator vane in a turbomachine. The stator vane includes an upper trunnion and a lower trunnion to allow the stator vane to be pivoted about a longitudinal axis. The lower trunnion is supported in a bushing that is carried in an opening provided in an annular stator vane carrier ring. The bushing is longitudinally split and is installed in the carrier ring while in a laterally compressed condition so that when installed in the carrier ring the bushing bears against the carrier ring opening in which it is positioned. When the carrier ring material expands with rising temperature, the pre-stress in the bushing will cause it to expand to maintain tight frictional engagement between the bushing and the opening and thereby prevent relative rotation between the bushing and the carrier ring to minimize wear of the carrier ring material.

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

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

Abstract: A method for assembling an articulated fan front frame for a gas turbine engine facilitates improving engine performance. The method includes forming a strut including a pair of sidewalls connected at a leading edge and a trailing edge, forming a flap including a first sidewall and a second sidewall connected at a leading edge and a trailing edge, and extending in radial span between a root endwall and a tip endwall, wherein each endwall extends between the first and second sidewalls, and wherein at least one of the root endwall and the tip endwall is contoured in a radial direction extending between the flap leading and trailing edges, and pivotally coupling the flap downstream from the strut such that a gap is defined between the flap and the strut.

Abstract: A trunnion support for a variable-position stator vane in a turbomachine. The stator vane includes an upper trunnion and a lower trunnion to allow the stator vane to be pivoted about a longitudinal axis. The lower trunnion is supported in a bushing that is carried in an opening provided in an annular stator vane carrier ring. The bushing is longitudinally split and is installed in the carrier ring while in a laterally compressed condition so that when installed in the carrier ring the bushing bears against the carrier ring opening in which it is positioned. When the carrier ring material expands with rising temperature, the pre-stress in the bushing will cause it to expand to maintain tight frictional engagement between the bushing and the opening and thereby prevent relative rotation between the bushing and the carrier ring to minimize wear of the carrier ring material.

Abstract: A turbocharger with an improved suspension mechanism for the actuation ring of a variable nozzle mechanism, for improved maintenance of the geometry of the suspension mechanism in the case of higher temperature oscillations. The suspension mechanism includes a number of guide rollers (48) provided between a housing part (24, 26) and nozzle ring (38) with circumferential grooves (59) in which the inner circumference of the actuating ring rides. The rollers are freely rotatable on pins (55′, 55″), and these pins are inserted in bores (55a or 55b) either in a housing part (24, 26) or in the nozzle ring (38), but not both.

Abstract: A turbocharger with an improved suspension mechanism for the actuation ring of a variable nozzle mechanism, for improved maintenance of the geometry of the suspension mechanism in the case of extreme temperature oscillations. The suspension mechanism includes a number of guide rollers (149) provided between housing part (126) and nozzle ring (138) with circumferential grooves (159) in which the inner circumference of the actuating ring rides. The rollers are formed as one piece together with axial extensions (149′, 149″, 149a, 149b), which extensions are rotatably seated in appropriate bores in the nozzle ring (138) and/or in the housing part (126). The axial extensions can have diameters which are smaller than or the same as the diameter of the actual roller part.

Abstract: A spring (15) of angular shape is placed between the lug (17) of a connecting rod (10) controlling the orientation of a stator blade and the pivot (3) of said blade, such that its edge (18) bends against one edge face (19) of the connecting rod (10) and the washer (16) moves the pivot (3) in the play of the bore (21) of the connecting rod and sets and maintains the contact between two plane faces (12 and 13), so as to reduce the differences in angular displacements between the connecting rod and pivot due to the play remaining in the bore (21).

Abstract: In a turbomachine compressor stator comprising a plurality of variable-pitch vanes (36), each vane mounted in rotation, about an axis of pivoting (38), in a wall (34) forming a surface of revolution about a longitudinal central axis of rotation of the turbomachine (32), being inclined by a specified angle (&agr;) with respect to a plane perpendicular to this longitudinal central axis, there is provision for this wall to be machined locally opposite an end part of each vane (42) so as to form a spherical portion or pocket (40) whose center is positioned on the axis of pivoting and whose radius is determined so as to ensure, over the entire range of operation of the vane, a predetermined minimum clearance between this end part of each vane and the opposite machined spherical pocket while limiting the depth of machining of this pocket.

Abstract: A variable geometry turbocharger in which a bill-like projection portion is arranged in a part of an outer periphery of a flow passage spacer, and the projection portion is protruded to a turbine rotor side at a predetermined angle or the projection portion is movably provided. Alternatively, a rod-like member is arranged in a part of an outer periphery of a flow passage spacer and the rod-like member is arranged so as to be adjacent to the turbine rotor side at a predetermined angle. Alternatively, a guide vane in which a leading edge side of a rotational shaft is eliminated is arranged in a part of an outer periphery of a flow passage spacer and the rotational shaft is arranged so as to be adjacent to the turbine rotor side at a predetermined angle.

Abstract: A torque shaft assembly includes a hollow tube with a central axis disposed between and fixedly connected to first and second crankshafts at first and second distal ends, respectively, of the tube for movement of an array of connecting members such as push rods. A hollow interior of tube between the first and second crankshafts is filled with a sufficient quantity of flowable inertia material or damping media to absorb vibratory energy by friction during operation of the engine. The hollow interior is preferably filled with a quantity of damping media to a level by volume of about 98% and a preferred flowable inertia material is round steel shot. A plurality of spaced-apart clevises are fixedly attached to a tube wall on an outer surface of the tube wall surrounding the hollow interior. Each clevis includes connection means disposed away from the wall outer surface for connection with an actuator for movement of the array of adjustable devices such as variable stator vanes.

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

Abstract: In order to make the components of a guide apparatus for an axial flow turbine easy to activate and also to permit only small gap flows, an axial flow machine is proposed with a guide apparatus, which comprises a row of adjustable guide vanes in the flow duct, which flow duct is bounded, on the one hand, by an inner spherically configured hub and, on the other hand, by an outer spherically configured guide vane carrier, the guide vanes being, on the one hand, rotationally supported in radial bearing holes of the annular guide vane carrier and, on the other hand, the spherically configured tip and root profiles of the guide vanes sealing against the guide vane carrier and the hub, in which arrangement the hub is embodied with a flexible hub contour at least in the sealing region of the inner tips of the guide vanes and the support for the guide vanes in the direction of the guide vane axes (A) is likewise designed to be flexible.

Abstract: Exhaust gas that is supplied to a turbine, but without going through channels between nozzle vanes provided in a variable-capacity turbocharger, is eliminated. A nozzle unit 100 in turbocharger 10 has a mounting plate 102 and a side plate 106 installed in a recess 20a provided in a housing 20 such that the side plate can move in the recess. A pushing mechanism 116 or 150 pushes the side plate toward the mounting plate 102. A movement limit 108 limits the movement of the side plate parallel to the turbine shaft toward the mounting plate 102.

Abstract: A stator of a variable-geometry axial turbine for aeronautical applications has an axis and is provided with an annular duct that has a diameter increasing along the axis, is delimited radially by an outer surface and by an inner surface and houses an array of airfoil profiles; the profiles are rotatable relative to the outer and inner surfaces about respective axes of adjustment incident to the axis of the stator and each have an associated pair of end edges opposite each other and each coupled slidably with an associated shaped zone of the outer and inner surfaces, each shaped zone has a form complementary to an ideal surface generated by rotation of the associated end edges about the axis of adjustment so as to maintain a constant clearance between the profiles and the inner and outer surfaces.

Abstract: An axial fan with reversible flow direction comprises a rotor (11), which is driven by a variable speed-controlled driving motor (14) and is provided with adjustable rotor blades (13) fitted around a rotational axis. The rotor (11) is preceded by an inlet stator (15) and followed by a downstream stator (16), which are each provided with guide vanes (17, 18). The guide vanes (17, 18) of the inlet stator (15) and the downstream stator (16) are designed so as to be mirror-symmetrical to the radial center plane of the rotor (11) and may be adjusted at an angle to the direction of flow in such a way that—when the flow direction is reversed—the inlet stator (15) takes on the function of a downstream stator and the downstream stator (16) takes on the function of an inlet stator.

Abstract: Improved vanes of this invention are constructed for use within a variable geometry turbocharger assembly. Each vane comprises an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite the inner airfoil surface. The inner and outer airfoil surfaces define a vane airfoil thickness. Each vane includes a leading edge positioned along a first inner and outer airfoil surface junction, a trailing edge positioned along a second inner and outer surface junction, a hole disposed within a first axial vane surface substantially parallel to an outer nozzle wall for receiving a respective post therein, and an actuation tab extending from a second axial vane surface opposite from the first vane surface. A key feature of improved vanes of this invention is that they have an airfoil thickness that is greater than 0.16 times a length of the vane as measured between the vane leading and trailing edges.

Abstract: A variable gas turbine compressor vane structure includes a gas turbine compressor vane having a vane support at an end thereof, and a case structure having a bearing support disposed to engage the vane support of the gas turbine compressor vane. The bearing support is typically a bearing bushing or a bearing washer. The bearing support is made of a metal skeleton having open-cell porosity extending therethrough, and an infiltrant material such as an organic or a ceramic infiltrated into the porosity of the metal skeleton.

Abstract: A variable stator vane assembly for a gas turbine engine including a bushing that facilitates extending a useful life of the stator vane assembly is described. The stator vane assembly includes a spacer and a vane secured to an engine casing. The bushing is between the spacer and vane, and prevents the spacer and the vane from contacting the engine casing. The bushing is fabricated from several materials formed in a matrix, such that at least a portion of the bushing is electrically conductive. During engine operation, a conductive path is realized through the bushing that discharges electrical charges.

Abstract: A vane adjustment mechanism, for controlling the quantity of exhaust gas including a base unit having an inner base unit and an outer base unit. The inner base unit (2A) has first and second flanges, and is forced into the outer base unit (2B). A plurality of U-shaped indentations (2c) are spaced at regular angular intervals and each indentation extends from the first flange (2a) to the second flange (2b), so that the U-shaped indentations form vane shaft holes for accommodating the vane lever units (3) when the inner base unit is inserted into the outer base unit to block the U-shaped indentations in such a way that the vane lever units are free to rotate. A link plate (4) has U-shaped indentations, in which protrusions of the vane lever units (3) engage, all along the circumferential edge of the link plate.

Abstract: A gas turbine engine including a variable geometry system that includes a mounting system to facilitate extending a useful life of a variable geometry system is described. The engine includes a high pressure compressor including a plurality of variable vanes and rotating vanes. The variable geometry system is coupled to an actuator and includes a master lever, an aft mount, and a slot and groove joint. The master lever is coupled to the aft mount with the slot and groove joint, and adjusts a position of the variable vanes without inducing angular displacement on the aft mount.

Abstract: A gas turbine engine variable geometry exhaust nozzle including a seal system that facilitates extending a useful life of the engine variable geometry system is described. The seal system includes a backbone and an attachment assembly. The attachment assembly frictionally engages the backbone to secure the attachment assembly to the backbone. The attachment assembly includes a plurality of clamp sub-assemblies and base sheet fabricated from a ceramic matrix composite material. The clamp sub-assemblies are clamped through openings extending through the base sheet, such that a predetermined amount of preload force is applied to the base sheet.

Abstract: A variable gas turbine compressor vane structure includes a gas turbine compressor vane having a vane support at an end thereof, and a case structure having a bearing support disposed to engage the vane support of the gas turbine compressor vane. The bearing support is typically a bearing bushing or a bearing washer. The bearing support is made of a metal skeleton having open-cell porosity extending therethrough, and an infiltrant material such as an organic or a ceramic infiltrated into the porosity of the metal skeleton.

Abstract: A gas turbine engine including a variable geometry system that includes a mounting system to facilitate extending a useful life of a variable geometry system is described. The engine includes a high pressure compressor including a plurality of variable vanes and rotating vanes. The variable geometry system is coupled to an actuator and includes a master lever, an aft mount, and a slot and groove joint. The master lever is coupled to the aft mount with the slot and groove joint, and adjusts a position of the variable vanes without inducing angular displacement on the aft mount.

Abstract: With a turbo machine comprises a trunnion portion and an airfoil portion, the airfoil portion is defined by a leading edge, a trailing edge, and a pair of side edges. One or more of the side edges comprises a fin which extends from proximate to the trunnion portion toward the trailing edge of the airfoil portion. The fin tapers in thickness from the trunnion portion to the trailing edge portion. The fin may extend above and/or below the top and bottom surfaces of the airfoil. The fin may be formed on a portion of one or both of the side edges.

Abstract: A variable inlet guide vane includes opposite pressure and suction sides extending along a chord between leading and trailing edges and in span from root to tip. The vane has a maximum thickness greater than about eight percent chord length and located less than about thirty-five percent chord length from the leading edge.

Abstract: A fabricated torque shaft is provided that features a bolt-together design to allow vane schedule revisions with minimal hardware cost. The bolt-together design further facilitates on-site vane schedule revisions with parts that are comparatively small. The fabricated torque shaft also accommodates stage schedules that are different one from another in non-linear inter-relationships as well as non-linear schedules for a particular stage of vanes.

Abstract: Disclosed is a producing method of an exhaust gas vane blade for superchargers of motor vehicles. The vane blade consists of a pivot part and a blade part with a streamlined section, which are integrally formed with each other. The vane blade is made of a heat resisting steel. The diameter of the pivot part is larger than the thickness of the blade part. The method comprises a multi-step cold-forging of a blank material of the above steel.

Abstract: A method of replacing an inlet guide vane from a lower inlet casing of a compressor, the lower inlet casing adapted to be secured to an upper inlet casing at a horizontal joint, and after removal of the upper half of the inlet casing but with a rotor of the compressor remaining in place, wherein the inlet guide vane is supported between radially inner and outer walls of the lower inlet casing, and further wherein the inlet guide vane is formed with an integral stem that extends radially through the outer wall and supports a drive gear on its outer end that engages an annular gear rack, the method including a) removing the gear on the radially outer end of the integral stem of the inlet guide vane; b) shearing the inlet guide vane into two cut portions; c) removing the cut portions from inside the lower inlet casing; and d) replacing the inlet guide vane by a modified inlet guide vane having a two-piece stem assembly that enables installation without removal of the rotor.

Abstract: A rotor machine arrangement comprises a rotor, a stator, at least one guide vane, which at two opposite ends is supported by the stator, and at least one end is pivotably arranged relative to the stator in at least a first plane, and at least one conducting member arranged to conduce a fluid into the guide vane for influencing the temperature of the same. The rotor machine arrangement comprises a sealing element which is pivotably connected with the guide vane in at least a second plane, is arranged to seal between the stator and the guide vane, and the sealing function of which is essentially independent of the angular position between the guide vane and the stator in said first plane.

Abstract: The object of this invention is to propose a variable capacity turbine, requiring neither adjustment process of the full-opening position and the perfect closing position nor the dedicated full position stopper, in which the adjustment works for setting up the full-opening position of the nozzle vanes are not required, and the accidents of damaging the turbine wheel caused by the nozzle vanes which opened excessively can be avoided. It has a plurality of joint members of the same number as the nozzle vanes, which connect a plurality of nozzle shafts for nozzle vanes and the nozzle driving member, and which rotate the nozzle shafts with a swing motion forced by the nozzle driving member. The nozzle angle regulator is provided with two full-opening stopper surfaces provided on at least two neighboring joint members to move the nozzle vanes towards the opening direction and stop the nozzle vanes at the full-opening position by contacting the two neighboring joint members to each other.

Abstract: An exhaust gas turbocharger with an exhaust gas turbine and a radial compressor includes an impeller which pumps air through guide vanes or wedge guide elements into a helical passage. It is proposed that the guide vanes or wedge vane elements be guided for axial displacement in the casing of the radial compressor and be able to be shifted across the pumped stream of the impeller.

Abstract: A vane and post arrangement for a variable geometry turbocharger employs vanes having a hole in a first end surface receiving a post extending from a surface of the nozzle in the turbine housing. A second end surface on each vane incorporates an extending tab which is received in a respective slot in a unison ring for rotation of the vanes on the posts upon movement of the unison ring.

Abstract: An assembly for coupling together in a turbofan engine the guide vane and the inner vane shroud. The assembly includes a bushing positioned within a shroud port for receiving the inner trunnion of the vane. A washer located between the bushing and a trunnion button of the vane provides substantial retaining contact between the bushing and the vane. A shroud retainer affixed to the inner surface of the shroud captures the bushing in the shroud port. The retainer preferably spans a series of shroud sections for as much as about one-half of the entire circumference of the shroud. The combination of the washer and the retainer with significant span reduces movement between the shroud and the vane. Wear on the vane trunnion is therefore reduced and maintenance obligations correspondingly reduced.

Abstract: A nozzle drive mechanism is provided for a link plate 112, which can operate all nozzle vanes smoothly and synchronously. The nozzle vanes 104 supported in such a way that the nozzle vanes are free to rotate between open and closed positions on nozzle shafts. The nozzle vanes are connected to levers which correspond to the nozzle shafts so as to rotate along with the levers. Each boss at the end of each lever 114 functions as a shaft which is parallel to the nozzle shaft. The shafts (bosses) in the nozzle vanes engage in oblong holes in the link plate in such a way that they are free to swing, and are thereby connected to the link plate. A declined straight or curved centerline which runs through the oblong hole to the oblong direction, extends at a given angle with respect to the radius of the link plate.

Abstract: A vane having a trunnion portion and an airfoil portion is provided with a stress reducing undercut on the trunnion portion proximate to the transition zone defined between the trunnion portion and the airfoil portion of the vane.