Abstract: The invention relates to a device for adjusting the centring of a turbo-engine pivoting vane control ring, comprising a control ring (26) centred on a longitudinal axis (X-X) of the turbo-engine and provided with a plurality of tapped holes (36) running in a radial direction and a plurality of pad holders (32), each comprising a threaded rod (34) screwed into one of the ring's tapped holes (36), each pad holder (32) holding, at an inner end, a pad (30) intended to come into contact with a cylindrical shell (28), coaxial with the ring. The control ring (26) comprises, in addition, a plurality of slots (38) running in a tangential direction, each slot (38) communicating with one of the ring's tapped holes (36) The device comprises means (40, 42a, 42b) of pinching, in a longitudinal direction, each of the slots (38) in such a way as to lock the pad holders (32) in position.

Abstract: A guide device with adjustable guide vanes is provided with a drive for the adjustable guide vanes, in which a cylindrical driving pin and an adjusting lever are provided each with one surface pair which are matched to one another and which slide on one another in operation when the guide vanes are being adjusted. To adjust the guide vanes, the adjusting ring is moved, by which the driving pin attached to the adjusting ring slides in an elongated groove of the adjusting lever and applies a force to the adjusting lever. This approach yields an economical and durable structure which is easy to install. This results in surface support with the corresponding low compressive loads per unit area and consequently greatly reduced wear.

Abstract: Guide vanes are supported in a two-part or multipart housing (32, 33). Housing separation takes place radially in the region of the bearing point (25) of the vane shaft so that the separating joint (36) between the housing parts (32, 33) leads through the bearing openings (34) which are designed to hold the vane shafts. The completely round opening (34) leads to the bearing point of the vane shaft having large-area support in any position. Thus high surface pressures can be avoided.

Abstract: The invention provides a device for adjusting the centering of a control ring for pivoting vanes of a turbomachine, the device comprising a plurality of pads for coming into contact with a circular surface that is coaxial with the ring, each pivoting vane being connected to the control ring via a lever having a first end secured to the control ring via a crank pin disposed radially on said ring, and a second end mounted on a pivot of the vane, each of said pads being secured to a pad carrier. Each pad carrier is secured under the control ring by means of attachment systems that are designed to be assembled from over the ring.

Abstract: The invention relates to a variable-pitch vane for a turbomachine compressor, the vane including a bushing mounted to rotate about a guide pivot of the vane for mounting in a casing of the turbomachine, the pivoting contact between the bushing and the guide pivot being of the nickel-graphite and titanium type.

Abstract: A compressor or pump employs principles of unsteady delayed stall to enhance the head increase produced by the compressor or pump. Plural airfoil-shaped lifting elements are spaced from each other in a cascade and the fluid is directed into the cascade by a device that varies a parameter of the flow relative to each lifting element in repeating cycles to cause the flow relative to each lifting element to begin to separate from the lifting element and then reattach thereto during each cycle. The cascade can comprise an axial flow impeller with plural impeller blades arranged around a hub capable of rotating on an axis. The device for varying the flow parameter can be a stator with a plurality of stator blades upstream of the impeller, or a second, counter-rotating axial flow impeller. In either case, the parameter is a flow angle at which the flow is directed to the downstream impeller.

Abstract: Four actuators are instructed to move to a condition indicated by a demand line 81. Their actual conditions are indicated by four arrows. The method determines if the range 84 of actual conditions exceeds a threshold value, representing an unacceptable mismatch of actuator positions. This comparison is used to establish further demand instructions. For example, if the range is too great, and the average 82 is below the demand line 81, the devices are instructed to move to the upper extreme position at 88. If the average position 82 is above the demand line 81, the devices are instructed to move to the lower end of the range, at 90. This results in the actuator positions moving together, as they also move toward the demand line 81, reducing risks associated with actuator mismatches.

Abstract: A variable vane arrangement (36) for a compressor (26) of a gas turbine engine (10) comprises a plurality of circumferentially arranged vanes (38), a plurality of operating levers (64) and a control ring (66). Each vane (38) is pivotally mounted to a casing (30) of the compressor (26). Each operating lever (64) is pivotally mounted at a first end (68) to the control ring (66) and is mounted at second end (70) to a respective one of the vanes (38). The second end (70) of each operating lever (64) comprises a multi-sided aperture (72) and each vane (38) has a multi-sided spindle (60) which locates in the multi-sided aperture (72) of the respective operating lever (64). Each operating lever (64) has a drive member (74) located in the multi-sided aperture (72) and around the multi-sided spindle (60) of the respective vane (38). Each drive member (74) engages the respective multi-sided aperture (72) and the respective multi-sided spindle (60) to transmit drive from the operating lever (64) to the vane (38).

Abstract: A variable gas turbine compressor vane assembly comprising a case structure comprising a cavity. A compressor vane is at least partially disposed inside the cavity in the case structure. The portion of the compressor vane is rotatably supported inside the cavity. A wear coating is disposed on at least a portion of a surface of the compressor vane. An antifriction coating is disposed on the wear coating. A bushing is disposed between the antifriction coating and the case structure. The bushing is in sliding contact with each of the antifriction coating and the case structure. The antifriction coating maintains a coefficient of friction between the antifriction coating and the bushing of equal to or less than about 0.95 in atmospheres substantially devoid of water vapor.

Abstract: The system enables an increase in the guidance length of the outer pivot of the vane, so that the bushing can be extracted without needing to open the stator casing. It mainly includes a bushing placed inside a bossing of the stator, the length of which is greater than the length of the bossing projecting outwards from the bossing. Thus, the contact length of the outer pivot is prolonged. The bushing is terminated at its end by a gripping hook to enable extraction of the bushing by means of a claw. It is advantageously also provided with a positioning edge.

Abstract: A method for controlling a variable geometry turbine of a turbocharger to increase the temperature of the exhaust gas delivered to an after-treatment system. In one form the method includes reducing a fluid flow area to the turbine below a normal size and bypassing a portion of the exhaust gas around a plurality of guide vanes.

Abstract: Materials, heretofore unknown for use in bearing assemblies, which produce equal or better wear resistance at reduced materials cost have been identified. These alternatives fall into four general categories: solid materials from which bushings and washers can be fabricated, coatings bonded to metallic vanes to minimize total system wear, solid lubricant coatings placed on any bushing or vane stem to reduce friction, and porous ceramic material from which seals can be fabricated.

Abstract: A device for the adjustment of stator vanes of a turbo engine includes an adjusting ring and an adjusting lever. The adjusting lever includes a first end, and a second end having an opening. The first end of the adjusting lever is connected to the adjusting ring. The device also includes an end of a shank of the stator vane, and the end of a shank of the stator vane enters into the opening of the second end of the adjusting lever to connect the second end of the adjusting lever to the end of the shank of the stator vane. The adjusting lever swivelingly connects the stator vane to the adjusting ring outside of the housing of the turbo engine. The device further includes a projection on the end of the shank, and the projection projects past the rim of the opening when the stator vane is in an installed position.

Abstract: A variable stator vane actuating lever (50) for use in a compressor (20) of a gas turbine engine (10). The lever (50) comprises a first end (52) for pivotal connection to a stator vane actuator ring (36) and a second end (54) for abutting a stator vane spindle (32). The stator vane spindle (32) has a diameter and flat positions (56,58,60,62). The second end (54) of the lever (50) has resilient members (64,66) for abutting the flat portions (56,58,60,62) of the stator vane spindle (32) at diametrically opposite locations. The resilient members (64,66) are integral with the second end (54) of the stator vane spindle (32) and are curved so that they are substantially tubular to provide even load distribution and improved location of the lever (50) on the stator vane spindle (32).

Abstract: A variable stator vane assembly for use in a compressor section of a turbine engine having a plurality of movable metallic stator vanes and a method for making a variable stator vane assembly. The variable stator vane assembly includes a metallic stator casing supporting the vanes and a bushing system positioned between the stator vanes and the stator casings. The bushing system includes a bushing fabricated from a material selected from the group consisting of metal, ceramic or combinations thereof. The variable stator vane further including a titanium nitride wear coating disposed on a surface of the vanes in contact with the bushing system.

Abstract: The manufacturing cost of the control device is relatively low. This device comprises mainly a first end (46) of a control lever (40) provided with a drive hole (45) that drives the driving part (16) of a blade (10) through a first contact area (41). The close contact between these two parts in this area is obtained using a play compensation plate (50) bearing on a side part (47) of the control lever (40), and fixed to the assembly using a nut (60) screwed onto the external pivot (11) of the blade (10). For application on turbomachines.

Abstract: A vane provided with at least one spindle, the at least one spindle configured to engage in operation with a support such that in operation the vane pivots about the at least one spindle. The vane is further provided with an electrically operable heater which is communicable with an electrical supply via an electrical connection node located in the at least one spindle. The electrical connection node comprises a female portion and a corresponding male portion. The support is defined by a casing.

Abstract: A method facilitates assembling a variable vane assembly for a gas turbine engine including a casing and an inner shroud. The method comprises providing at least one variable vane including a radially inner spindle that includes a groove defined therein that has at least one machined face, and coupling the variable vane radially between the casing and the inner shroud such that at least a portion of the radially inner spindle is inserted at least partially through an opening extending radially through the inner shroud. The method also comprises securing the variable vane to the inner shroud by engaging the spindle machined face with a retainer coupled to the inner shroud.

Abstract: Aerodynamically efficient air flow management in axial flow-turbines is provided by utilizing a variable stagger and camber airfoil. In an exemplary embodiment of the invention, this is accomplished by providing a two-piece airfoil including a strut and a flap, each of which is mounted to articulate about a common, radially oriented axis. The strut and flap are respectively positioned by a strut gear and a flap gear, located at the radial end of the airfoil and, in an exemplary embodiment, are driven by a stepped synchronizing ring.

Abstract: A method for improving the wear characteristics of a system for operating a variable vane comprising the steps of providing a trunnion connected to the variable vane via an vane platform and means for causing rotation of the trunnion, and positioning a thrust washer formed from a carbon material about a lower portion of the trunnion and in a space between the vane platform and an outer split case so that during operation of the system the space between the vane platform and the outer split case is maintained substantially constant and unwanted deflection of the vane is avoided.

Abstract: A device for guiding pivoting of variable-pitch vanes in a turbomachine, each vane having a pivot formed by a cylindrical axial shank which is guided in a cylindrical chimney of the casing and in a cylindrical orifice of a stationary element which surrounds the outside of the casing and which is centered and fixed relative thereto. The invention improves pivotal guidance of variable-pitch vanes.

Abstract: A guide device for guiding a variable-pitch blade, in particular in a turbomachine compressor, the blade having a pivot formed by a cylindrical axial shank mounted in a cylindrical housing of a casing and pivotally guided about an axis in said housing by bearings, where the bearings are abutment bearings with conical rollers, the axes of the rollers being substantially perpendicular to the pivot axis of the blade.

Abstract: Materials, heretofore unknown for use in bearing assemblies, which produce equal or better wear resistance at reduced materials cost have been identified. These alternatives fall into three general categories: (1) solid materials from which bushings and washers can be fabricated, (2) coatings bonded to metallic bushings and/or vanes to minimize total system wear, and (3) solid lubricant coatings placed on any bushing or vane stem to reduce friction.

Abstract: A variable geometry turbocharger includes vanes disposed therein having an inner airfoil surface oriented adjacent a turbine wheel, and an outer airfoil surface oriented opposite and parallel to the inner airfoil surface. The vane includes first and second axial surfaces that are each positioned perpendicular to and interposed between the inner and outer airfoil surfaces. A vane leading edge is positioned along a first inner and outer airfoil surface junction, and a trailing edge is positioned along a second inner and outer airfoil surface junction. One or more of the first and second axial surfaces have a composite construction comprising a solid section that extends a distance from the leading edge towards the trailing edge, and a cored-out section that extends a distance from the trailing edge towards the leading edge.

Abstract: A guide device for an exhaust gas turbocharger has a geometry which is variable. The guide device includes guide blades, blade levers which are connected to particularly assigned guide blades in a rotationally fixed manner, and a setting ring in which the blade levers are mounted via a spring element.

Abstract: A variable vane arm is disclosed having dual retention capability to ensure vanes of a gas turbine engine remain connected to the vane arm even under surge loads or when fastener preload, or the entire fastener, is lost. The variable vane arm further provides a surge slot to facilitate rotation of the vane even when the vane is operating under surge or otherwise excessively high pressure conditions.

Abstract: A turbocharger comprising a turbine housing where at least one supply channel supplies an exhaust gas. The exhaust gas is fed through a guide grid that forms passages of variable cross-section between the supply channel and a turbine rotor. This guide grid comprises a plurality of vanes of predetermined width in a vane space of about the same width. A vane support ring defines one axial end of the annular vane space and an opposite ring is spaced from the vane support ring by about the width of the vanes to define the other axial end of the annular vane space. To maintain this width, at least two spacers are integrally formed on at least one the rings.

Abstract: A device for controlling variable-pitch vanes in a turbomachine comprises links connecting the radial pivots of the vanes to radial fingers carried by semicircular elements and bridges of a control ring, the links being mounted in ball-and-socket manner on the radial fingers which are fixed to the control ring. This form of mounting enables all the vanes associated with the control ring to be set to the same angular pitch.

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: An attachment system for use with a variable incidence vane is disclosed. The attachment system includes a vane arm for joining a unison ring to a vane spindle. The vane arm has an arm portion and a bushing connected to the arm portion. The attachment system further has a pin for joining the vane arm to the unison ring. The pin fits within an interior bore in the bushing and is joined to the unison ring by a dual swage.

Abstract: A sealing arrangement for a stator shroud segment is provided that includes a resilient seal to reduce air leakage and improve turbine engine efficiency. The stator shroud segment includes an outer shroud having a leading edge groove and a trailing edge groove, and a plurality of inner shrouds each having a leading edge hook and a trailing edge hook. The leading and trailing hooks of each of the inner shrouds are respectively engaged with the leading and trailing edge grooves of the outer shroud so as to connect the inner shrouds to the outer shroud. A resilient shaped seal is located on a leading edge hook of the inner shroud so as to be between the leading hook and a retaining ring that contributes to holding the inner shroud in place.

Abstract: Vane actuating apparatus for adjusting the angle of incidence of a set of variable angle vanes in a gas turbine engine comprises a plurality of vane actuator levers attached at one end to a respective vane and at the other end to an actuation arrangement for moving the vanes in unison. Each lever has an interlocking connection arrangement for pivotally connecting the lever with respect to its respective vane in such a way that the lever is capable of being attached and detached from the vane at a first angular position, and retained in interlocking engagement for pivotal movement at a second angular position or range of positions.

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: Exemplary turbine blade outer edges, exemplary vane inner edges, exemplary systems and exemplary methods are disclosed that help to reduce noise in variable geometry turbines and optionally other turbines wherein a turbine blade interacts with an object. Other exemplary turbine-related technologies are also disclosed.

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 hydraulic turbine with increased power capacities for new or existing hydroelectric installations. The turbine has a larger axial runner wheel and a reshaped runner ring peripherally extending around the runner wheel. A draft tube with a larger elbow section extends on a downstream side of the runner ring. A water supply port extends around a rotation axis of the runner wheel on an upstream side of the runner ring, and is adapted to produce a centripetal water flow swirling around the rotation axis of the runner wheel. A turning passageway extends between the water supply port and the runner ring, and is adapted to guide and redirect the centripetal water flow in a substantially axial direction of the runner wheel. An axial distributor extends between the turning passageway and the runner ring.

Abstract: A blade for a stator of a variable-geometry turbine, particularly for aircraft engines; the blade has an airfoil profile hinged to a structure of the stator to rotate about an axis, and having a pressure front wall and a suction rear wall; the blade also has two end walls, which are located at opposite ends of the airfoil profile, cooperate in sliding manner with the structure of the stator, and are cooled, in use, by air flowing through a number of holes; the outlets of the holes are located close to the outer edges between the end walls and the front wall to generate a tangential stream of cooling air by virtue of the pressure difference acting on the front and rear walls.

Abstract: In a nozzle vane driving control apparatus of a variable nozzle turbocharger including an actuator for carrying out a driving operation for opening and closing a nozzle vane of a variable nozzle and an ECU for controlling the opening degree of the nozzle vane which is obtained by the actuator, an actuator cover for covering a pinion and reduction gears by interposing a base provided integrally with a motor case portion therebetween, a unit body accommodating each of control boards, a position sensor for detecting the rotating position of an output shaft and a connector having a terminal connecting a motor and each of the control boards, and a unit cover for covering the unit body are removably fastened and fixed with a bolt and are thus integrated with each other.

Abstract: A turbocharger comprising at least one turbine wheel supplied with exhaust gas from a combustion motor. The amount of gas supplied is determined by a fluid control arrangement to which an actuation device is assigned for generating a controlling movement for the fluid control arrangement. In addition, a transmitting mechanism for this movement comprising an adjusting device is presented by which the control movement may be adjusted.

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. 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: 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: An axial turbine for aeronautical applications has a casing housing a stator, which is provided with an array of airfoil profiles, which are positioned angularly equidistant from one other about the axis of the turbine, define associated spaces between one another for the passage of a flow of gas and are hinged to an annular structure, each one about an associated hinge axis incident to the axis of the turbine; in service, the airfoil profiles are simultaneously actuated to rotate by an identical angle of adjustment by means of a ring actuated by actuators outside the casing and connected to each airfoil profile via an associated lever.

Abstract: An exhaust gas turbocharger for an internal combustion engine, which has an exhaust gas turbine in the exhaust system and a compressor in the induction system, comprises a variable turbine geometry, associated with the turbine, for adjustably setting a radial inlet cross section for the flow to the turbine rotor. The variable turbine geometry is configured as a guide cascade ring, which has guide vanes distributed over the periphery and encompasses the turbine rotor. The minimum distance between two adjacent guide vanes obeys a specified relationship with respect to the diameter of the turbine rotor and the number of guide vanes of the guide cascade ring. In addition, a flow edge is provided on the radially inner surface of each guide vane.

Abstract: Materials, heretofore unknown for use in bearing assemblies, which produce equal or better wear resistance at reduced materials cost have been identified. These alternatives fall into three general categories: (1) solid materials from which bushings and washers can be fabricated, (2) coatings bonded to metallic bushings to minimize total system wear, and (3) solid lubricant coatings placed on any bushing or vane stem to reduce friction.

Abstract: The guide-vane system serves to change the position of the guide vanes of an axial-flow exhaust-gas turbine of a turbocharger. The guide vanes are arranged axially symmetrically to the turbine axis in a flow passage carrying exhaust gas and can be pivoted by a pivoting device in each case about a radially directed axis. A vane shank led radially outward from the flow passage through a casing wall is attached to each of the guide vanes. With its part directed outward, the vane shank is mounted so as to be rotatable about the pivot axis. The pivoting device contains an adjusting ring, arranged outside the flow passage and rotatable about the turbine axis, and also an adjusting lever which transmits a torque from the adjusting ring to the vane shank of each guide vane. The adjusting ring is mounted with its outside on rolling elements which are each designed as one-armed levers and are mounted so as to be pivotable on a component of a casing wall, this component being designed as a supporting ring.

Abstract: A bearing assembly for use in a gas turbine engine to rotatably mount a torque tube in an access hole extending through a fan duct. The torque tube connects a variable stator vane bell crank positioned inside the fan duct to an actuator positioned outside the fan duct. The bearing assembly includes a bearing having a spherical external engagement surface and a housing having a flange and an annular interior surface having an inner edge and an outer edge. The interior surface is sized and shaped for rotatably receiving the spherical external engagement surface of the bearing so the spherical engagement surface and the annular interior surface make contact along an annular contact area centered on a contact plane lying between the inner and outer edges. The contact plane is tilted with respect to the flange at an angle greater than five degrees.

Abstract: A method enables a variable vane assembly for a gas turbine engine including a casing to be assembled. The variable vane assembly includes a seal assembly and at least one variable vane that includes a platform and a trunnion, wherein the platform extends outwardly from the trunnion. The method comprises coupling a seal assembly journal bushing to the variable vane such that the journal bushing is against the trunnion and between the trunnion and the engine casing, and wherein the journal bushing has a substantially constant diameter extending between a first and a second end of the journal bushing, and positioning a substantially flat first washer on the variable vane ledge to prevent contact between the variable vane assembly and the engine casing.

Abstract: A device for controlling variable-pitch vanes in a turbomachine comprises links connecting the radial pivots of the vanes to radial fingers carried by semicircular elements and bridges of a control ring, the links being mounted in ball-and-socket manner on the radial fingers which are fixed to the control ring. This form of mounting enables all the vanes associated with the control ring to be set to the same angular pitch.

Abstract: Vane actuating apparatus for adjusting the angle of incidence of a set of variable angle vanes in a gas turbine engine comprises a plurality of vane actuator levers attached at one end to a respective vane and at the other end to actuation means for moving the vanes in unison. Each lever has an interlocking connection means for pivotally connecting the lever with respect to its respective vane in such a way that the lever is capable of being attached and detached from the vane at a first angular position, and retained in interlocking engagement for pivotal movement at a second angular position or range of positions.

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, fixing means for fixing a second end of the link on a pivot of a vane to be controlled, and pinch means acting transversely relative to a longitudinal midplane of the link to lock the second end of the link in rotation without slack on the pivot.