| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415160000 | Individually pivoted vanes | 68 |
| 20080206045 | CONTROL OF VARIABLE-PITCH BLADES - The present invention relates to the control of variable-pitch blades, particularly a device for controlling a pivot of a variable-pitch blade in a stator of a turbomachine compressor. | 08-28-2008 |
| 20080292451 | Securing arrangement - A securing arrangement | 11-27-2008 |
| 20080317587 | VARIABLE-SHAPE VARIABLE-STAGGER INLET GUIDE VANE FLAP - A variable shape inlet guide vane (IGV) system includes a variable-shape IGV flap with a flexible portion that enables the desired spanwise distribution of Cx, alpha, and beta at a fan rotor inlet. An actuation system that rotates a root section of the variable-shape IGV flap to flex the flexible portion such that the twisted shape of the flap can reverse rather symmetrically during actuation from max open to max closed. | 12-25-2008 |
| 20090022580 | VARIABLE GEOMETRY TURBOCHARGER, VANE RING ASSEMBLY WITH RETAINING MEMBER - A vane ring assembly which includes a lower vane ring ( | 01-22-2009 |
| 20090060721 | BUSHING AND CLOCK SPRING ASSEMBLY FOR MOVEABLE TURBINE VANE - A bushing assembly for a turbine vane includes a bushing, housing, and a flexible conductor. The bushing includes a bore for receiving a trunnion of the vane and a first conductor extending from the bushing. The first conductor is adapted to be connected to a heater element disposed on the vane. The housing is positioned over the, and the bushing is rotatable relative to the housing. The housing includes a second conductor extending from the housing for connection to an electrical power source. The flexible conductor is electrically connected between the first conductor and the second conductor, such that an electric current is transmitted from the second conductor to the first conductor to provide an electric current to the heater element | 03-05-2009 |
| 20090060722 | VARIABLE-PITCH VANE OF A TURBOMACHINE - A stator stage of a compressor of a turbomachine, comprising an annular row of variable-pitch vanes, each vane comprising an external cylindrical pivot defining the axis of rotation of the vane, and an internal cylindrical pivot mounted in a housing of an internal ring, the internal pivot of each vane extending along an axis substantially parallel to the axis of rotation of the vane and at a distance from this axis, and being mounted in the housing of the ring by a swiveling or a tilting system. | 03-05-2009 |
| 20090087304 | STAGE OF VARIABLE-PITCH VANES FOR A TURBOMACHINE - A stage of variable-pitch vanes for a turbomachine, these vanes ( | 04-02-2009 |
| 20090104022 | Gas Turbine Engine Systems Involving Gear-Driven Variable Vanes - Gas turbine engine systems involving gear-driven variable vanes are provided. In this regard, a representative gas turbine engine system includes: a ring gear assembly operative to be mounted within an engine casing; and a vane module having a first vane airfoil and a first gear, the first gear being operative to engage the ring gear assembly such that movement of the ring gear alters a position of the first vane airfoil. | 04-23-2009 |
| 20090104023 | Variable Nozzle Turbocharger - The shape, of a vane for use in a variable nozzle assembly of a turbocharger was designed, including a step of defining a camberline curve and a thickness curve by means of two Bézier curves having a certain number of control points, and a step of applying computational fluid dynamics analysis and a Design of Experiments methodology for optimizing the setting of the control points to improve performance of the vane. As result, a distinct vane shape as shown in the drawings was obtained. | 04-23-2009 |
| 20090162192 | Variable turbine vane actuation mechanism having a bumper ring - A variable vane actuation assembly for gas turbine engines having rotatable stator vanes comprises an engine casing, a unison ring, a bumper ring, a radial spline connection and a plurality of bumper shims. The engine casing is configured to encase the rotatable stator vanes. The unison ring is disposed concentrically with the engine casing. The bumper ring is disposed concentrically between the engine casing and the unison ring. The radial spline connection extends from the engine casing and joins with the bumper ring to permit the bumper ring to float radially with respect to the engine casing, but prevent the bumper ring from rotating circumferentially with respect to the engine-casing. The plurality of bumper shims are positioned between the unison ring and the bumper ring to limit deformation of the unison ring. | 06-25-2009 |
| 20090297340 | Rotary sliding vane compressor - The invention relates to increasing the fluid capacity and the fluid discharge pressure of a rotary sliding vane fluid compressor without significantly increasing the fluid discharge temperature. According to the invention supplemental air under pressure is added to a compressor's rotating pocket to increase the fluid capacity and fluid pressure in the pocket. | 12-03-2009 |
| 20100008766 | VARIABLE GEOMETRY VANE RING ASSEMBLY WITH STEPPED SPACER - A vane ring assembly includes a lower vane ring ( | 01-14-2010 |
| 20100014961 | TURBOCHARGER - The invention relates to a turbocharger ( | 01-21-2010 |
| 20100068040 | Exhaust Guide Member of Nozzle Vane-Type Turbocharger - In a turbocharger equipped with a nozzle vane for changing the speed of exhaust gas running through a turbine in accordance with the speed of engine revolution, the member to constitute the nozzle vane and to constitute an exhaust guide for guiding exhaust gas to the turbine is characterized in that the exhaust guide member of a nozzle vane-type turbocharge is formed of an austenite stainless steel containing, in terms of % by mass, at most 0.08% of C, from 2.0 to 4.0% of Si, at most 2.0% of Mn, from 8.0 to 16.0% of Ni, from 18.0 to 20.0% of Cr and at most 0.04% of N and containing these ingredients in such a manner that they satisfy a DE value of the specified formula to be from 5.0 to 12.0, with a balance of Fe and inevitable impurities. | 03-18-2010 |
| 20100080694 | VARIABLE GEOMETRY TURBOCHARGER - A turbocharged engine includes an internal combustion engine and a variable geometry turbocharger. The turbocharger is adjustable to operate efficiently under various engine operating and environmental conditions. The turbocharger includes a turbine and compressor, with the compressor including a compressor housing, an impeller rotatably mounted in the housing, and an adjustable diffuser vane assembly. The diffuser vane assembly includes a plurality of pivotal diffuser vanes spaced about the impeller and a vane rotation drive that interconnects the vanes and permits simultaneous adjustment of the diffuser vanes to improve the efficiency and operating range of the turbocharger. The diffuser vane assembly also includes a vane locking drive operable to engage the pivotal vanes and prevent vane movement during turbocharger operation. | 04-01-2010 |
| 20100092278 | SCALABLE HIGH PRESSURE COMPRESSOR VARIABLE VANE ACTUATION ARM - A variable vane arm has a hook portion comprising a radially inner leg connected to a radially outer leg by an arcuate connection, and an actuation lever extending from the hook portion. The hook portion and actuation lever are formed from a singular piece of material. | 04-15-2010 |
| 20100098529 | TURBOCHARGER VANE | 04-22-2010 |
| 20100104425 | CHARGING EQUIPMENT - The invention relates to a piece of charging equipment having a variable turbine geometry ( | 04-29-2010 |
| 20100111677 | Variable stator blade assembly - A variable stator blade assembly of a compressor, in particular of a gas turbine, including a compressor casing with a counterbore and a receptacle, a stator blade with a spindle, a spindle bush and a seal is provided. The spindle bush is placed inside the receptacle and spindle is placed inside the spindle bush wherein the seal is placed radially between the spindle and the spindle bush. The spindle is the dynamic seal face and a face within the spindle bush is the static seal face. | 05-06-2010 |
| 20100150701 | VARIABLE GEOMETRY TURBOCHARGER - A variable geometry turbocharger is provided. The turbocharger improves efficiency by controlling flow to the rotor ( | 06-17-2010 |
| 20100166542 | VARIABLE STATOR BLADE MECHANISM FOR TURBOCHARGERS - A turbocharger with variable turbine geometry comprising of a turbine housing having an exhaust gas inlet and an outlet, a volute connected to the inlet, and a nozzle wall adjacent the volute, carrying a turbine wheel and is attached to a shaft with a plurality of improved aerodynamic profiled stator blades that are disposed within the turbine housing between the exhaust gas inlet and turbine wheel. | 07-01-2010 |
| 20100166543 | Inlet Guide Vanes and Gas Turbine Engine Systems Involving Such Vanes - Inlet guide vanes and gas turbine engine systems involving such vanes are provided. In this regard, a representative an inlet guide vane for a gas turbine engine includes: a fixed strut; and a variable flap located downstream of the fixed strut and being movable with respect thereto; the fixed strut having a leading edge, a trailing edge and side surfaces extending between the leading edge and the trailing edge, the side surfaces being asymmetric with respect to each other. | 07-01-2010 |
| 20100172744 | VARIABLE POSITION GUIDE VANE ACTUATION SYSTEM AND METHOD - Disclosed herein is a turbine variable position guide vane actuation system. The system includes, a plurality of variable position guide vanes, a plurality of actuators with each actuator in operable communication with one of the plurality of variable position guide vanes, and each of the plurality of actuators having a pin. The system further having at least one structure, movable parallel to an axis of the turbine, having a plurality of slots and each of the plurality of slots is in operable communication with one of the pins. | 07-08-2010 |
| 20100202874 | VARIABLE NOZZLE MECHANISM - When changing a nozzle blade angle by rotating a drive ring, a contact load generated between an inner circumferential surface of the drive ring and an outer circumferential surface of a mount can be reduced, allowing the drive ring to rotate smoothly and reducing the amount of wear and a driving force. It is also possible to reduce an impact force, such as engine vibrations, generated at the drive ring when an external force acts, reducing the risk of damage. A plurality of notches ( | 08-12-2010 |
| 20100232936 | VARIABLE STATOR VANE CONTOURED BUTTON - A variable stator vane airfoil is mounted on a button centered about a rotational axis and includes circular leading and trailing edges circumscribed about the rotational axis at a button radius. Contoured pressure and suction sides extend from the circular leading edge to the circular trailing edge and are recessed inwardly from a perimeter circumscribed about the rotational axis at the button radius. One of upstream and downstream pressure side portions of the contoured pressure side is straight and another of the upstream and downstream pressure side portions is curved. One of the upstream and downstream suction side portions is straight and another of the upstream and downstream suction side portions is curved. One of the upstream pressure side portion and upstream suction side portion is straight and another of the upstream pressure side portion and upstream suction side portion is curved. | 09-16-2010 |
| 20100232937 | CHARGING DEVICE, MORE PREFERABLY FOR A MOTOR VEHICLE, WITH A VARIABLE TURBINE GEOMETRY - The invention relates to a charging device, more preferably a turbocharger, with a spring for clamping the guide blade carrier ( | 09-16-2010 |
| 20100247293 | VARIABLE AREA TURBINE VANE ARRANGEMENT - A ring vane nozzle for a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of fixed turbine vanes between an inner vane ring and an outer vane ring and a multiple of rotational turbine vanes between the inner vane ring and the outer vane ring, each of the rotational turbine vanes rotatable about an axis of rotation. | 09-30-2010 |
| 20100260596 | Hydraulic bulb turbine with mixed-flow propeller runner - The invention is a Bulb turbine with mixed-flow propeller runner instead of axial flow propeller runner. The main area of application for the invention are the large tidal power plants (Fundy Bay, Severn Lake, etc.) with barrages where the propeller runners are working together with DC generators located in the bulbs. | 10-14-2010 |
| 20100260597 | VARIABLE-VANE ASSEMBLY HAVING FIXED GUIDE PINS FOR UNISON RING - A variable-vane assembly for a variable nozzle turbine comprises a nozzle ring supporting a plurality of vanes affixed to vane arms that are engaged in recesses in the inner edge of a unison ring. The unison ring is rotatable about the axis of the nozzle ring so as to pivot the vane arms, thereby pivoting the vanes in unison. A plurality of guide pins for the unison ring are inserted into apertures in the nozzle ring and are rigidly affixed therein such that the guide pins are non-rotatably secured to the nozzle ring with a guide portion of each guide pin projecting axially from the face of the nozzle ring. Each guide portion defines a shoulder radially overlapping the inner edge of the unison ring such that the unison ring is restrained by the guide pins against excessive movement in both radial and axial directions. | 10-14-2010 |
| 20100310359 | PROCESS FOR CALIBRATING A VARIABLE-NOZZLE ASSEMBLY OF A TURBOCHANGER AND A VARIABLE-NOZZLE ASSEMBLY FACILITATING SUCH PROCESS - A process for calibrating a variable-nozzle assembly ( | 12-09-2010 |
| 20110123316 | VARIABLE GEOMETRY TURBINE - A variable geometry turbine comprises: a turbine wheel ( | 05-26-2011 |
| 20110182717 | TURBOCHARGER - The invention relates to a turbocharger ( | 07-28-2011 |
| 20110293406 | VARIABLE-PITCH VANE FOR STATOR STAGE, INCLUDING A NON-CIRCULAR INNER PLATFORM - A variable-pitch vane for a stator stage including includes an active part of the vane either side of which are positioned a radially inner platform and a radially outer platform, where the active part of the vane, which has a surface forming a convex surface, and a surface forming a concave surface, separate the platform into a part positioned on the convex side and a part positioned on the concave side. Seen along the direction of the vane's axis of rotation, the part has an outer outline superimposed on a circle, at the distance of which, and inside which, is at least a part of the outer outline of the part of the platform. | 12-01-2011 |
| 20120076641 | VARIABLE VANE ASSEMBLY FOR A TURBINE COMPRESSOR - A variable vane assembly for a compressor having a plurality of vanes is disclosed. The variable vane assembly may generally include a synchronizing ring and a plurality of attachment studs secured to the synchronizing ring. The variable vane assembly may also include a plurality of lever arms, with each lever arm having a first end and a second end. The first end of each lever arm may be attached to one of the vanes. Additionally, a plurality of rotational attachment devices may be configured to rotatably couple the second end of each lever arm to one of the attachment studs so as to define a rotational interface therebetween. Further, each of the attachments studs may be rigidly attached to one of the rotational attachment devices at the rotational interface such that there is substantially no relative radial and circumferential sliding motion between the synchronizing ring and the plurality of lever arms during rotation of the synchronizing ring. | 03-29-2012 |
| 20120257961 | MULTISTAGE VACUUM PUMP - A multistage vacuum pump has a pair of rotors disposed in each of pump chambers connected in stages. As the rotors rotate while intermeshing, a suctioned gas is compressed and discharged, angles of the rotors are adjusted so that a phase angle Δθ of the rotors of adjacent pump chambers relative to a rotation angle C of the rotors during a single cycle of the pump chambers from intake to discharge and the number of stages S of the rotors satisfies Δθ≦C/S. When a rotor angle is φ | 10-11-2012 |
| 20130216361 | VANE ASSEMBLY FOR A GAS TURBINE ENGINE - A vane assembly for a gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible features, a first platform, a second platform spaced from the first platform, and a first variable airfoil that extends radially across an annulus between the first platform and the second platform. One of a radial outer portion and a radial inner portion of the variable airfoil includes a rotational shaft and the other of the radial outer portion and the radial inner portion includes a ball and socket joint that rotationally connect the first variable airfoil relative to the first platform and the second platform. | 08-22-2013 |
| 20130243580 | GAS TURBINE ENGINE VARIABLE STATOR VANE ASSEMBLY - A variable stator vane assembly for a gas turbine engine includes a variable stator vane and a non-structural fairing on the variable stator vane. | 09-19-2013 |
| 20140140822 | Contoured Stator Shroud - A contoured stator shroud has a stator chord overhang having a surface which varies in elevation forming a plurality of surface contours, wherein the contours reduce clearance between adjacent vanes during off design performance positioning of the vanes. | 05-22-2014 |
| 20140169950 | VARIABLE VANE HAVING BODY FORMED OF FIRST MATERIAL AND TRUNNION FORMED OF SECOND MATERIAL - A variable vane includes a variable vane body that has an airfoil portion. The variable vane body is formed of a first material. A trunnion is attached at one end of the variable vane body. The trunnion includes a pivot formed of a second, different material. | 06-19-2014 |
| 20140234087 | INLET GUIDE VANE RETENTION FEATURE - A variable vane assembly includes a vane having a trunnion. The trunnion includes a partial flange. A shroud supporting the trunnion in a recess has a forward axial half and an aft axial half. The recess includes a retainer portion which receives the partial flange. An engine and a vane are also described. | 08-21-2014 |
| 20140286758 | NOZZLE RING WITH NON-UNIFORMLY DISTRIBUTED AIRFOILS AND UNIFORM THROAT AREA - A segmented nozzle ring is disclosed having a throat area between neighboring vanes that is the same for each segment which is achieved by rotation (i.e., opening or closing of the throat area) of the individual vane compounds belonging to the different segments. The resulting uniform throat area leads to a uniform exit flow angle of the nozzle and a uniform inlet flow angle of the rotor. As a result, high-cycle fatigue excitations of the rotor caused by the non-uniform flow can be eliminated, the thermodynamic efficiency of the turbine stage can be improved, and the nozzle ring need not be arranged in a fixed position relative to the gas inlet casing. | 09-25-2014 |
| 20140286759 | TURBINE FOR AN EXHAUST GAS TURBOCHARGER - In a turbine for an exhaust gas turbocharger with a turbine casing comprising a housing space for the turbine wheel of a turbine with guide vanes arranged upstream of the turbine wheel in a radial direction of the turbine wheel so as to be stationary relative to the turbine casing for guiding exhaust gas to the turbine wheel, and with an actuating element by which an inlet flow cross-section of the turbine through which the exhaust gas flows is variably adjustable and which is movable in the axial direction of the turbine between a blocking position restricting the flow cross-section and an open position clearing the flow cross-section relative to the turbine casing, the actuating elements extend through conforming openings formed in the guide walls between the guide vanes into the spaces defined between the guide vanes for controlling the turbine inlet flow cross-section. | 09-25-2014 |
| 20150118030 | VARIABLE GEOMETRY TURBO SYSTEM - A variable geometry turbo system that controls a flow of exhaust gas introduced into a turbine of a turbo charger may include a vane base ring in which the turbine may be positioned at a center thereof, a fixed vane which may be fixed onto a first surface of the vane base ring to guide the exhaust gas introduced into the turbine, a variable vane which may be pivotally positioned on the first surface of the vane base ring and adjacent to the fixed vane so as to vary a flow path of the exhaust gas introduced into the turbine, a vane cover ring fixed to the vane base ring with the fixed vane and the variable vane interposed therebetween, and an actuating module coupled to the variable vane and selectively actuating the variable vane. | 04-30-2015 |
| 20150132113 | ADJUSTABLE GUIDE VANE MECHANISM FOR A TURBINE, TURBINE FOR AN EXHAUST GAS TURBOCHARGER AND EXHAUST GAS TURBOCHARGER - In an adjustable guide vane mechanism for a turbine, comprising a bearing ring with a plurality of guide vanes rotatably supported on the bearing ring by means of guide vane shafts provided with actuating levers which are engaged by a rotatable ring, the rotatable ring comprises axially spaced radial inner and outer sections with a radially inclined center section joining the spaced radial inner and outer sections, the radially inner section being rotatably supported and the radially outer section extending around the actuating levers and having recesses in which the actuating levers are received for pivoting the actuating levers and the guide vanes upon rotation of the rotatable ring. | 05-14-2015 |
| 20150377061 | Unknown - The invention relates to a guide means ( | 12-31-2015 |
| 20160017745 | CASE WITH VANE RETENTION FEATURE - One exemplary aspect of this disclosure relates to an assembly for a gas turbine engine having an engine axis. The assembly includes a case including an integrally formed projection configured to extend transverse to the engine axis. The assembly further includes an engine component including a flange configured for contact with the projection to limit motion of the component along the engine axis. | 01-21-2016 |
| 20160146038 | TURBOMACHINE INCLUDING A VANE AND METHOD OF ASSEMBLING SUCH TURBOMACHINE - A vane for a turbomachine includes a pressure surface and a suction surface opposite the pressure surface. The pressure surface and the suction surface define a width therebetween. The vane also includes a first end. The first end includes a distal portion, a proximal portion, a pressure surface first portion, and a suction surface first portion. At least one of the pressure surface first portion and the suction surface first portion slope away from the other of the pressure surface first portion and the suction surface first portion such that the width increases from a first end minimum width at the proximal portion to a first end maximum width at the distal portion. | 05-26-2016 |
| 20160146099 | ADJUSTABLE-TRIM CENTRIFUGAL COMPRESSOR, AND TURBOCHARGER HAVING SAME - A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes a variable-geometry conical mechanism comprising a plurality of vanes that in the closed position collectively form a frusto-conical inlet member having a trailing edge inner diameter that is smaller than an inner diameter of the shroud surface of the compressor housing at the inducer portion of the compressor wheel such that an effective diameter of the air inlet at the inducer portion is determined by the trailing edge inner diameter of the variable-geometry conical mechanism. The vanes in the open position are pivoted radially outwardly so as to increase the trailing edge inner diameter of the inlet member and thereby increase the effective diameter of the air inlet at the inducer portion. | 05-26-2016 |
| 415161000 | And fixed vane | 2 |
| 20090087305 | Exit stay apparatus with intermediate flange - The invention is an Exit Stay Apparatus with Intermediate Flange for Francis and propeller hydraulic turbines. The purpose of the invention is to improve the effectiveness of known Exit Stay Apparatus (U.S. Pat. No. 6,918,744, July 2005, for Hydraulic Turbine and Exit Stay Apparatus therefor) in eliminating the axial central vortex and, therefore, in increasing the efficiency and decreasing the flow pressure pulsations in draft tube cone at off optimum operating regimes. The new Exit Stay Apparatus has an intermediate flange between exit stay crown and periphery and two sets of exit stay vanes: crown exit stay vanes secured to the exit stay crown and the intermediate flange and peripheral exit stay vanes secured to the intermediate flange and following to the periphery. When installed in the turbine the peripheral exit stay vanes are secured at the periphery. There are more crown exit stay vanes than the peripheral exit stay vanes and their profiles are longer than the profiles of the peripheral exit stay vanes. The Exit Stay Apparatus with Intermediate Flange is expected to have the same peak efficiency as known Exit Stay Apparatus. | 04-02-2009 |
| 20090104024 | Air intake for a turbocharger for an internal combustion engine - Disclosed is an air intake for a turbocharger for an internal combustion engine, said air intake including a series of variable position guide vanes for directing the air such that it is swirling in a rotational sense on reaching the impeller of the compressor of the turbocharger. The variable position guide vanes are made comprised of sound absorbent material such as to achieve a substantial reduction in turbocharger noise at the air intake. | 04-23-2009 |
| 415162000 | Plural, selectively adjustable vane sets | 7 |
| 20090155058 | Variable Geometry Compressor Module - A variable geometry compressor housing module has a housing ( | 06-18-2009 |
| 20090208329 | GAS TURBINE COMPRESSOR - A gas turbine compressor presents a first fixed stage having a plurality of first adjustable vanes and a further fixed stage, which has an inner ring extending about a first axis; an outer ring arranged about the inner ring and coaxial with the inner ring; and a plurality of second adjustable vanes, each of which extends along a second axis in an essentially radial direction with respect to the first axis between the inner ring and the outer ring; and it is adjustable about the corresponding second axis independently from the first adjustable vanes. | 08-20-2009 |
| 20100278639 | CONTROL MECHANISM - A control mechanism is provided for moving at least two components of a gas turbine engine. The control mechanism comprises a moveable actuation rod. The control mechanism further comprises a first linkage arrangement which includes a first bell crank and which operatively connects the actuation rod to a first component of the gas turbine engine. Movement of the actuation rod produces an output motion of the first bell crank which in turn drives movement of the first component. The control mechanism further comprises a second linkage arrangement which includes a second bell crank and which operatively connects the actuation rod to a second component of the gas turbine engine. Movement of the actuation rod produces an output motion of the second bell crank which in turn drives movement of the second component. The first linkage arrangement and the second linkage arrangement are configured so that over a predetermined range of movement of the actuation rod the first component is moved by the first bell crank while the second component is not moved by the second bell crank. | 11-04-2010 |
| 20130236296 | Low Pressure Compressor Variable Vane Control for Two-Spool Turbofan or Turboprop Engine - A system and a method for adjusting an angle of at least one stator vane of a low pressure compressor (LPC) of a two spool gas turbine engine is disclosed. Variable stator vanes are rotatably coupled to a stationary case in one of the stages of the LPC. An actuator is coupled to at least one of the variable stator vanes for imparting rotation of the stator vane about a radius of the case. Various coupling or linkage arrangements may be made so that rotation of one vane results in rotation of the other vanes disposed along the case. The controller includes the stored constraints, the ability to estimate operating condition, and the ability to estimate optimum targets. | 09-12-2013 |
| 20130287550 | COMPRESSOR OF A GAS TURBINE SYSTEM - A compressor of a gas turbine system includes at least one inlet row having a plurality of inlet guide vanes. Also included is at least one stator row having a plurality of stator vanes. Further included is a first actuation mechanism operably connected to the at least one stator row, wherein the first actuation mechanism is configured to positionally manipulate the at least one stator row. Yet further included is a second actuation mechanism operably connected to the at least one stator row, wherein the second actuation mechanism is configured to positionally manipulate the at least one stator row. | 10-31-2013 |
| 20150050129 | VTG TURBOCHARGER VANE PACK ASSEMBLY WITH ABRADABLE COATING - A vane pack for a VTG turbocharger is provided. The vane pack includes a plurality of vanes pivotably positioned between an inner surface of an upper vane ring and an inner surface of a lower vane ring. Clearances are defined between opposing cheek surfaces of the vanes and the inner surfaces of the vane rings. The vane pack is configured to minimize these clearances by applying an abradable coating is to the inner surface of the upper vane ring, the inner surface of the lower vane ring and/or cheek surface(s) of one or more of the vanes. In this way, an essentially zero clearance can be established without interfering with the proper function of the vanes. As a result, there can be gains in efficiency. Further wearing of the abradable coating may occur during turbocharger operation. | 02-19-2015 |
| 20150071768 | VARIABLE PITCH RECTIFIER FOR A TURBOMACHINE COMPRESSOR COMPRISING TWO INNER RINGS - A variable pitch rectifier for a compressor includes a plurality of radial vanes having respectively, at outer and inner ends of same, outer and inner pivots, the inner pivots being received between two upstream and downstream inner rings, which are assembled by a link device. The link device includes only a set of angular sectors of elastically deformable stirrups, arranged to grip together the inner peripheral edges of the upstream and downstream rings by clamping one against the other. | 03-12-2015 |
| 415163000 | Pivoted parallel to runner axis | 11 |
| 20080219834 | Rotor Shaft Assembly for Magnetic Bearings for Use in Corrosive Environments - Rotor and stator assemblies that utilize magnetic bearings for supporting the rotor shaft during operation can be suitably used in corrosive environments, such as sour gas. The rotor and stator assemblies include NACE compliant magnetic bearing arrangements for sour gas applications. In one embodiment, a rotor shaft assembly for a magnetic bearing arrangement comprises a rotor shaft formed of a ferromagnetic material comprising a plurality of rotor laminations disposed on the rotor shaft; and a barrier layer formed on selected exposed surfaces of the rotor shaft, wherein the barrier layer is effective to resist corrosion relative to the surface without the barrier layer. | 09-11-2008 |
| 20080260520 | Turbocharger and Variable-Nozzle Cartridge Therefor - A variable-nozzle turbocharger includes a cartridge containing a variable vane mechanism connected between the center housing and the turbine housing. The cartridge comprises an annular nozzle ring supporting an array of rotatable vanes, an insert having a tubular portion sealingly received into the bore of the turbine housing and having a nozzle portion extending radially out from one end of the tubular portion and being axially spaced from the nozzle ring with the vanes therebetween, a plurality of spacers connected between the nozzle portion of the insert and the nozzle ring, and an annular retainer ring fastened to the center housing so as to capture the nozzle ring between the retainer ring and the center housing. The retainer ring is formed as a separate part from the insert ring and is mechanically and thermally decoupled from the insert. | 10-23-2008 |
| 20090022581 | TURBOCHARGER COMPRISING ADJUSTABLE GUIDE BLADES, BLADE LEVER AND ADJUSTING RING THEREFOR - The invention relates to a turbocharger ( | 01-22-2009 |
| 20090252601 | CONTROL RING FOR VARIABLE TURBINE GEOMETRY - The invention relates to a variable turbine geometry ( | 10-08-2009 |
| 20100172745 | CENTRIFUGAL COMPRESSOR HAVING ADJUSTABLE INLET GUIDE VANES - An apparatus for adjustment of inlet guide vanes of a compressor includes a ring having a plurality of slots spaced around a circumference thereof; a plurality of lever arm assemblies each having a pin that includes a body with a first end and a second end and a lever arm extending perpendicularly from the second end of the body of the pin; a plurality of vanes each coupled to an end of one of the plurality of lever arms by a shaft; and a rack and pinion drive mechanism. The pin of each of the lever arm assemblies is configured to be positioned within each of the plurality of slots such that the first end of the pin extends into the slot. The rack and pinion drive mechanism includes a pinion coupled to the shaft of one of the plurality of vanes, thereby creating a drive vane; and a driven rack operationally coupled to the pinion. The drive vane is configured to rotate the ring via the rack and pinion drive mechanism, thereby adjusting an angular position of the plurality of vanes. | 07-08-2010 |
| 20100196146 | TURBOCHARGER WITH VARIABLE TURBINE GEOMETRY - The guide blades provided for the variable turbine geometry are adjustably arranged within a radial gap through which gases can flow on a moveable carrier ring, which is axially clamped against stops on or in the radial gap with a thrust spring device. According to the invention, the thrust spring device loads the carrier ring on the positions closely adjacent to the stops. The thrust spring device is designed open without sealing function and if applicable combined with a separate seal without thrust function. | 08-05-2010 |
| 20110110768 | VARIABLE GEOMETRY TURBOCHARGER WITH GUIDE PINS - A variable geometry turbocharger assembly comprises a unison ring which rotates about a longitudinal axis defined by a shaft on which a turbine wheel and compressor wheel are attached in order to pivot a plurality of vanes and thereby control a flow of exhaust gas to the turbine wheel. The unison ring rotates on at least one guide pin which is secured to the turbocharger. The guide pins may be press-fit into apertures in a center housing at an outer pilot surface. In other embodiments the guide pins may be press-fit into a different part of the turbocharger such as a nozzle ring. The guide pins may each have a wear surface which defines a circumferential radius of curvature which is substantially equal to a circumferential radius of curvature of a radially inner surface of the unison ring. | 05-12-2011 |
| 20110171009 | Variable-Vane Assembly Having Unison Ring Guided Radially By Rollers and Fixed Members, and Restrained Axially by One or More Fixed Axial Stops - A variable-vane assembly for a variable nozzle turbine comprises a nozzle ring supporting a plurality of vanes affixed to vane arms that are engaged in recesses in the inner edge of a unison ring. The unison ring is rotatable about the axis of the nozzle ring so as to pivot the vane arms, thereby pivoting the vanes in unison. The unison ring is radially restrained by a combination of radial guide rollers and fixed axial-radial guide pins secured to the nozzle ring, and is axially restrained by one or more axial stops affixed to the nozzle ring. | 07-14-2011 |
| 20120177482 | GUIDE VANE FOR A TURBO-COMPRESSOR, GUIDE VANE ARRANGEMENT, TURBO-COMPRESSOR, MOTOR VEHICLE AND METHOD - A guide vane of a turbo-compressor has variable turbine geometry, in particular for a motor vehicle. The guide vane has a profile with a lower side, an upper side and a front edge. The guide vane is characterized by a nose which extends along the front edge of the vane, from the front edge of the vane to the upper side of the vane and forms a low pressure on the upper side of the vane when waste gas impacts the guide vane. A guide vane configuration, a turbo-compressor, a motor vehicle and a method for operating this type of turbo-compressor are further disclosed. | 07-12-2012 |
| 415164000 | Vanes and blade in same radial plane | 2 |
| 20080298955 | Inlet guide vane inner air seal surge retaining mechanism - An inner air seal carrier for use in a gas turbine engine having an inlet guide vane surge retainer comprises a body, a stationary sealing element and an outcropping. The body secures around an inlet guide vane inner diameter shroud. The stationary sealing element is disposed on a radially inward face of the body for engaging with a rotatable sealing element of a compressor rotor. The outcropping is positioned on the radially inward face of the body forward of the stationary sealing element for engaging with the surge retainer. | 12-04-2008 |
| 20090220335 | TURBINE AND TURBOCHARGER HAVING THE SAME - A turbine is provided which can reduce variations in mass flow at throats even when the flow rate of fluid is low or high, to prevent a decrease in performance. The invention employs a turbine including a turbine rotor which has turbine blades; a turbine housing which accommodates the turbine rotor | 09-03-2009 |
