| Entries |
| Document | Title | Date |
|---|
| 20080304957 | Pane Arrangement for a Turbocharger - The invention relates to a turbocharger ( | 12-11-2008 |
| 20090041577 | VARIABLE-GEOMETRY TURBOCHARGER WITH ASYMMETRIC DIVIDED VOLUTE FOR ENGINE EXHAUST GAS PULSE OPTIMIZATION. - A turbine assembly for a variable-geometry turbocharger includes a turbine housing defining a divided volute having first and second scrolls, wherein the first scroll has a substantially smaller volume than the second scroll. The first scroll feeds exhaust gas to a first portion of a turbine wheel upstream of the throat of the wheel, while the second scroll feeds gas to a second portion of the wheel at least part of which is downstream of the throat. Flow from the second scroll is regulated by a sliding piston. The first scroll can be optimized for low-flow conditions such that the turbocharger can operate effectively like a small fixed-geometry turbocharger when the piston is closed. The turbine housing defines an inlet that is divided by a dividing wall into two portions respectively feeding gas to the two scrolls, a leading edge of the dividing wall being downstream of the inlet mouth. | 02-12-2009 |
| 20090053044 | Vtg Mechanism Assembly Using Wave Spring - The present invention is a turbocharger unit ( | 02-26-2009 |
| 20090092482 | Systems and Methods for Altering Inlet Airflow of Gas Turbine Engines - Systems and methods for altering airflow to gas turbine engines are provided. In this regard, a representative system includes a gas turbine engine inlet having a slat, the slat being movable between a retracted position and an extended position. In the extended position, the slat increases an effective diameter of the inlet compared to the diameter of the inlet when in the retracted position. | 04-09-2009 |
| 20090092483 | Turbocharger with variable nozzle mechanism - A turbocharger having a variable nozzle mechanism, which is accommodated in an accommodating chamber, is disclosed. The variable nozzle mechanism has a nozzle ring, a nozzle vane, a nozzle vane drive mechanism, and a support ring. The nozzle ring defines a gas passage through which exhaust gas is guided to a turbine wheel. The nozzle vane is supported by the nozzle ring and varies the flow area of the gas passage. The nozzle vane drive mechanism drives the nozzle vane. The support ring is connected to the nozzle ring. The nozzle vane drive mechanism is accommodated in the accommodating chamber as spaced from the nozzle ring through the support ring. The turbocharger has a drain passage that extends through a lower portion of the support ring and reaches the gas passage. The drain passage is located downward from the nozzle vane drive mechanism. | 04-09-2009 |
| 20090097969 | Variable geometry turbine - Variable geometry turbine, in particular a gas turbine, comprising a housing ( | 04-16-2009 |
| 20090136338 | TURBOCHARGER WITH AT LEAST ONE VARIABLE TURBINE GEOMETRY TURBINE - The invention relates to a turbocharger for a combustion engine, in particular of a motor vehicle, with at least one variable turbine geometry turbine, which exhibits a rotor disk and vanes arranged on a vane support, which are spaced apart from each other around the rotor disk in at least one circumferential area, and with an adjuster to select the angular setting of the vanes. It is provided that the vanes ( | 05-28-2009 |
| 20090142185 | ADJUSTING RING FOR ADJUSTING THE BLADES OF THE VTG DISTRIBUTOR OF EXHAUST GAS TURBOCHARGERS - The invention relates to an adjusting ring ( | 06-04-2009 |
| 20090142186 | Variable geometry turbine - A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and of vanes that are received in corresponding slots in the facing wall. Each vane major surface such that at a predetermined axial position of the nozzle ring relative to the facing wall the recess is in axial alignment with the slot and affords an exhaust gas leakage path through the inlet passageway. The recess is configured to reduce the efficiency of the turbine at small inlet gaps appropriate to engine braking or exhaust gas heating modes. | 06-04-2009 |
| 20090148273 | COMPRESSOR INLET GUIDE VANE FOR TIP TURBINE ENGINE AND CORRESPONDING CONTROL METHOD - A tip turbine engine ( | 06-11-2009 |
| 20090180862 | Method of manufacturing turbine frame for VGS turbocharger, turbine frame manufactured by the method, exhaust gas guide assembly for VGS turbocharger using the turbine frame, and VGS turbocharger in which the exhaust gas guide assembly is incorporated - A novel method of manufacturing a turbine frame for rotatably holding adjustable blades in a VGS turbocharger is provided, which method is capable of manufacturing the turbine frame while almost eliminating a time-consuming cutting operation, whereby mass production of the turbine frame and the like can be realized. The method includes: a blank which is punched out from a metal material having a substantially constant thickness in such a manner as to integrally include a boss forming portion ( | 07-16-2009 |
| 20090196741 | TURBO COMPRESSOR AND REFRIGERATOR - A position adjustment device of a turbo compressor that supports an annular member of which at least a portion is capable of being disposed in a diffuser flow path and that can be disposed in and adjusts the height of the annular member. The position adjustment device has a plurality of lever mechanisms that each have a rod connected to the annular member and are disposed separated from each other in the circumferential direction; and a transmission mechanism that transmits a drive force that at least one of the plurality of lever mechanisms has received to the other lever mechanisms. The transmission mechanism has a substantially circumferential linkage in which an open section is partially provided. | 08-06-2009 |
| 20090214330 | VARIABLE-NOZZLE ASSEMBLY FOR A TURBOCHARGER - A variable-nozzle assembly comprises a nozzle ring and an array of vanes circumferentially spaced about the nozzle ring and rotatably mounted to the nozzle ring such that the vanes are variable in setting angle, and an insert having a tubular portion and an annular nozzle portion extending generally radially out from one end of the tubular portion. A plurality of axially extending holes extend through a thickness of the nozzle portion. A plurality of spacers have first ends joined to the nozzle ring, opposite second ends of the spacers being engaged in the holes and secured to the nozzle portion by welds formed at the second surface. An annular groove is defined in the second surface of the nozzle portion radially inward of and proximate to the holes. Alternatively or additionally, discrete recesses are formed in the second surface adjacent the holes. The groove and/or recesses facilitate weld penetration. | 08-27-2009 |
| 20090238682 | Compressor stator with partial shroud - A gas-turbine axial compressor has a casing | 09-24-2009 |
| 20090269187 | Variable stator vane - A variable stator vane in a gas turbine engine has a journal provided with a circumferential recess. An aperture extends from the recess to a face of the journal directed towards the aerofoil portion of the vane. In operation of the engine, heated air, for example from a downstream compressor stage of the engine is admitted to the recess and flows through the aperture to, for example, the pressure surface of the aerofoil portion. The aerofoil portion is thereby heated, so preventing ice accretion on the vane. | 10-29-2009 |
| 20090285673 | INNER DIAMETER VANE SHROUD SYSTEM HAVING ENCLOSED SYNCHRONIZING MECHANISM - A variable vane mechanism comprises a variable vane, an inner diameter shroud and a synchronizing mechanism. The variable vane comprises a vane body, an inner diameter trunnion extending radially inwardly from the vane body, and a button connected to the inner diameter trunnion and displaced radially inwardly from the inner diameter trunnion. The shroud comprises a shroud body, a socket extending into the shroud body for receiving the inner diameter trunnion, a flange extending into the socket for engaging the button and inhibiting radial movement of the variable vane, and a synchronizing channel extending through the inner diameter shroud aft of the socket so as to be bounded by the shroud body and opening to the socket. The synchronizing mechanism is disposed inside the synchronizing channel and connects to the inner diameter trunnion. | 11-19-2009 |
| 20100104423 | Turbocharger Vane - A variable nozzle device including an annular nozzle passage formed by a gap between two opposing wall members and at least one vane rotatably supported in the nozzle passage. The vane is formed by a strip of sheet metal contoured to have an outer aerodynamic profile, and having a hollow interior with surfaces mimicking the outer profile. The vane is affixed to a shaft having a wind-stream portion forming two contact surfaces that conformingly receive opposing portions of the interior surfaces. | 04-29-2010 |
| 20100104424 | VARIABLE TURBINE GEOMETRY TURBOCHARGER - A turbocharger is provided having a turbine wheel ( | 04-29-2010 |
| 20100310358 | INNER DIAMETER SHROUD ASSEMBLY FOR VARIABLE INLET GUIDE VANE STRUCTURE IN A GAS TURBINE ENGINE - An inner shroud assembly includes an aft core segment mountable to a forward core segment to support a multiple of vanes for rotational movement relative thereto. A shroud backing plate segment engageable with the aft core segment and at least one fastener which passes through the shroud backing plate, the aft core segment and the forward core segment. | 12-09-2010 |
| 20100329852 | CIRCULATION STRUCTURE FOR A TURBO COMPRESSOR - A circulation structure for a turbo compressor, in particular for a compressor of a gas turbine, is disclosed. The circulation structure includes at least one annular chamber that can be traversed in a circumferential direction, is concentric with a shaft of the turbo compressor in the region of the free blade ends of a blade ring, and radially borders a main flow channel. Several chambers that can be traversed in an axial direction are situated upstream of the or each annular chamber, when viewed from the main flow direction of the main flow channel. | 12-30-2010 |
| 20110038715 | VARIABLE NOZZLE FOR A TURBOCHARGER, HAVING NOZZLE RING LOCATED BY RADIAL MEMBERS - A variable nozzle for a turbocharger ( | 02-17-2011 |
| 20110058932 | VARIABLE STATOR VANE ASSEMBLIES - A variable stator vane assembly for a gas turbine engine has a projection protruding from the upper stem of the vane and which engages an aperture in the vane lever to provide a visual indication of correct alignment between the lever and the vane. | 03-10-2011 |
| 20110076139 | VARIABLE GEOMETRY TURBINE - A variable geometry turbine comprises a turbine wheel ( | 03-31-2011 |
| 20110110767 | SEALED SHAFT ASSEMBLY FOR EXHAUST TURBINES - An exemplary assembly includes a component of a turbocharger that includes a bore that extends between an inner, exhaust gas side of the component and an outer, ambient side of the component; a shaft that includes a pin portion and a head portion; a sleeve positioned on the pin portion of the shaft; and a bushing positioned over at least part of the sleeve and over at least part of the head portion of the shaft where the bushing seats the shaft and the sleeve in the bore. During operation of a turbocharger that includes such an assembly, the shaft, the sleeve and the bushing restrict flow of exhaust gas from the inner, exhaust gas side of the component to the outer, ambient side of the component. Various other exemplary devices, assemblies, methods, etc., are also disclosed. | 05-12-2011 |
| 20110142602 | METHODS OF DETERMINING VARIABLE ELEMENT SETTINGS FOR A TURBINE ENGINE - Variable elements of a turbine engine such as variable inlet guide vanes, variable bleed valves and variable stator vanes can be adjusted to provide a desired level of power and/or efficiency for the turbine engine across a range of operating conditions. The variable element settings typically determined through experimentation when the engine is new. Unfortunately, over the life cycle of the turbine engine, as wear occurs, the original variable element settings may no longer provide a desired level of power and efficiency. To correct this problem, offsets to the original variable element settings are calculated based on observable operational conditions which provide a measure of the wear that has occurred. The offsets are applied to the original variable element settings to generate corrected variable element settings. These corrected variable element settings are then used to configure the turbine engine. The corrected variable element settings allow the turbine engine to continue to operate at a desired level of power and/or efficiency over the life of the turbine engine, despite any deterioration which may have occurred due to normal life cycle wear. | 06-16-2011 |
| 20110158792 | ENGINE AND VANE ACTUATION SYSTEM FOR TURBINE ENGINE - One embodiment of the present invention is a unique turbine engine. Another embodiment is a unique vane actuation system. In one form, the actuation system includes a four bar linkage. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for turbine engines and vane actuation systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith. | 06-30-2011 |
| 20110171008 | TURBOCHARGER AND ADJUSTMENT RING THEREFOR - An adjustment ring for turbocharger applications, particularly in diesel engines, is described, which consists of an iron-based alloy with an austenitic basic structure with dendritic carbide precipitations. | 07-14-2011 |
| 20110176913 | NON-LINEAR ASYMMETRIC VARIABLE GUIDE VANE SCHEDULE - A variable inlet guide vane arrangement for a compressor includes a case defining an inlet of the compressor; at least one vane support coaxially disposed within the case; a plurality of vanes circumferentially disposed around the circumference of the case, each vane being pivotally mounted between the case and the at least one vane support; an actuator mechanism configured to pivot at least some of the plurality of vanes in an asymmetrical pattern around the circumference of the case. A method of controlling a variable inlet guide vane arrangement for a compressor includes pivoting at least some of the plurality of vanes in an asymmetrical pattern around the circumference of the case. | 07-21-2011 |
| 20120082539 | VARIABLE GEOMETRY TURBINE - A variable geometry turbine for a turbocharger has a plurality of vanes disposed in an inlet passageway of a turbine housing outboard of the turbine wheel. The vanes are movable so as to adjust the effective cross-section area of the inlet between a first position in which the area of the inlet is a minimum and a second position in which the area of the inlet is a maximum. The movement of one end of the vanes is supported by a plurality of first guide tracks, such as slots, defined in a guide member. A vane actuator such as, for example a unison ring, effects movement of the vanes. The vane actuator has a plurality of actuation tracks (e.g. slots) for engagement with the vanes and is rotatably disposed in the housing. When it rotates the vane actuator induces sliding translation of the vanes relative to the first guide tracks in a first direction and sliding translation of the vanes relative to the actuation tracks in a second direction so as to adjust the cross-section area of the inlet. The swirl angle changes between the first and second positions. | 04-05-2012 |
| 20120087780 | INTEGRATED ACTUATOR MODULE FOR GAS TURBINE ENGINE - An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing. | 04-12-2012 |
| 20120230814 | DIFFUSER FOR A TURBOCHARGER HAVING AN ADJUSTABLE TURBINE GEOMETRY AND TURBOCHARGER FOR AN INTERNAL COMBUSTION ENGINE - In a diffuser for a turbocharger having an adjustable turbine geometry wherein the diffuser comprises an axial slide and an adjusting device for moving the axial slide and wherein the adjusting device comprises an adjusting fork having an opening with a guide axis for the accommodation of a guide element and the adjusting device further comprises an adjusting lever with a lever end, the lever end is accommodated in a recess of the adjusting fork which is disposed at a side of the adjusting fork facing the axial slide in order to minimize tilting forces and provide for smooth sliding movement of the fork. | 09-13-2012 |
| 20120251299 | TURBOCHARGER - The invention relates to a turbocharger ( | 10-04-2012 |
| 20120328416 | TURBOCHARGER - A turbocharger includes a drive shaft to transmit a driving force of an actuator to a mechanism in the turbo housing, and a bush to rotatably support the drive shaft, wherein a seal is provided at an end portion on the open-air side of the bush. The seal includes a seal body made of resin and a metallic spring fitted into a recessed portion of the seal body, wherein an internal lip portion of the seal body is pressed by the elastic force of the spring to the outer circumferential surface of the drive shaft. Further, an end surface that is contactable with a member (drive link) disposed on the open-air side of the drive shaft is formed in the seal body. The seal having the above-described structure is provided at the end portion on the open-air side of the bush so as to achieve excellent sealability, so that this securely prevents exhaust gas in the turbo housing from passing through between the outer circumferential surface of the drive shaft and the inner circumferential surface of the bush and flowing out to the outside. | 12-27-2012 |
| 20130078082 | TURBOCHARGER VARIABLE-NOZZLE ASSEMBLY WITH VANE SEALING ARRANGEMENT - A variable-nozzle assembly for a turbocharger includes a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring such that the vanes can be pivoted about their axes for regulating exhaust gas flow to the turbine wheel. A unison ring engages vane arms that are affixed to axles of the vanes, such that rotation of the unison ring causes the vanes to pivot between a closed position and an open position. The vanes have proximal ends that are adjacent a face of the nozzle ring. A vane sealing member is supported on the nozzle ring and has a portion disposed between the proximal ends of the vanes and the face of the nozzle ring. The unison ring includes cams that engage cam followers. Rotational movement of the unison ring causes the cam followers to be moved axially and thereby urge the vane sealing member against the proximal ends of the vanes. | 03-28-2013 |
| 20130136581 | VARIABLE TURBINE GEOMETRY - A variable turbine geometry may have guide blades rotatably mounted in a blade bearing ring. An adjusting ring may be arranged on the bearing ring and an actuator may be configured to adjust the adjusting ring via a link lever. An adjustable eccentric may be arranged on the link lever and guided in a groove arranged on the blade bearing ring. The eccentric may be configured to stop on at least one end of the groove to limit at least one minimal flow through the variable turbine geometry. | 05-30-2013 |
| 20130177403 | VARIABLE GEOMETRY TURBINE - A variable geometry turbine comprise a housing; a turbine wheel supported in the housing for rotation about a turbine axis: and an annular inlet passage upstream of said turbine wheel defined between respective inlet surfaces defined by an annular nozzle ring and a facing annular shroud. The nozzle ring and shroud are axially movable relative to one another to vary the size of the inlet passage; the nozzle ring having a circumferential array of inlet vanes extending across the inlet passage. The shroud covers the opening of a shroud cavity and defines a circumferential array of vane slots, each vane slot corresponding to an inlet vane, the vane slots and shroud cavity being configured to receive said inlet vanes to accommodate axial movement of the nozzle ring. At least one vane slot has a first side corresponding to a first side of the corresponding inlet vane and a second side corresponding to a second side of the corresponding inlet vane, the first side of the vane slot being located a shorter radial distance from the turbine wheel than the second side of the vane slot. The at least one vane slot has a leading end corresponding to a leading end of a corresponding inlet vane, and a trailing end downstream of the leading end, the trailing end corresponding to a trailing end of the inlet vane. A vane chord extends in a straight line between the a leading end tip and a trailing end tip of the inlet vane. The at least one vane slot has an increased clearance portion, the clearance between a portion of the at least one vane slot, which forms part of the increased clearance portion, and an adjacent portion of the inlet vane being greater than the clearance between a further portion of the at least one vane slot, which does not form part of the increased clearance portion, and an adjacent portion of the inlet vane. The increased clearance portion is located at the second side of the vane slot and extending from a trailing end tip of the trailing end of the vane slot to a point which is a distance from the trailing end of the vane slot, in the direction of the vane chord, that is greater than about 10% of the length of the vane chord. | 07-11-2013 |
| 20130236295 | COMPACT IGV FOR TURBOEXPANDER APPLICATION - An inlet guide vane actuation apparatus is provided. The inlet guide vane actuation apparatus comprises an actuation ring with a first connector for connecting an actuator rod, wherein the first connector positions the actuator rod over the rotational axial center of the actuation ring, a plurality of crank rods with a first end connected respectively to a plurality of second connectors located on the rotational axial center of the actuation ring; and a plurality of cranks with each having a third connector connected respectively to a second end of the plurality of crank rods and respectively to vanes associated with a nozzle, wherein the third connector located on the rotational axial center of the actuation ring. | 09-12-2013 |
| 20130294895 | VARIABLE GEOMETRY TURBINE - A variable geometry turbine includes a fluid space formed by a nozzle mount and a nozzle plate; and a plurality of nozzle vanes arranged in the fluid space at certain intervals in the circumferential direction so as to partition the fluid space. The nozzle vanes are supported by shafts on the nozzle mount, in such a manner as to be capable of turning. The flow rate of the discharged fluid can be adjusted by opening or closing the cross-sectional area of a flow path formed by the adjacent nozzle vanes. The nozzle plate is provided with plate projections protruding toward the nozzle vanes further than, at least, end surfaces of the nozzle vanes, so as to cover the spaces between leading edges of the nozzle vanes and trailing edges of the nozzle vanes adjacent thereto, when the nozzle vanes are at a closed position. | 11-07-2013 |
| 20140099191 | TURBINE FOR AN EXHAUST GAS TURBOCHARGER - In a turbine for exhaust gas turbocharger of a combustion engine with a turbine casing forming an installation space in which a turbine wheel is arranged so as to be rotatable about an axis of rotation and into which exhaust gas of the combustion engine may be supplied via at least one flow duct in which a guide vane structure is arranged, the guide vane structure includes vanes, which are pivotably supported relative to the turbine casing and form an axial inlet nozzle structure adjacent a wall portion of the turbine which extends along the guide vane structure, the wall portion comprising at least a first guide wall area which overlaps the guide vane structure, and which is set back relative to a second guide wall area in which the vanes are pivotably supported and which adjoins the first wall area. | 04-10-2014 |
| 20140119897 | Hydroturbine Guide Vanes and Hydroturbine - The invention provides hydroturbine guide vanes and a hydroturbine which are capable of achieving high efficiency in a Francis turbine having a low flow rate at the highest efficiency point according to the specifications thereof and, in addition, hardly present a strength problem when regulating the flow rate. The guide vanes includes a plurality of fixed guide vanes having a long chord length and a plurality of movable guide vanes having a short chord length arranged between the fixed guide vanes, and a flow rate regulation including a fully-closed state is performed by rotating the movable guide vanes having the short chord length. | 05-01-2014 |
| 20140127004 | CHARGING DEVICE AND ASSOCIATED OPERATING METHOD - A charging device for an exhaust gas turbocharger of an internal combustion engine may include at least one variable turbine and compressor geometry and an adjusting device for adjusting the at least one variable turbine and compressor geometry. The adjusting device may include a minimum set limit, which defines a minimum set flow of the at least one variable turbine and compressor geometry for an exhaust gas driving the charging device, and a maximum set limit, which defines a maximum set flow of the at least one variable turbine and compressor geometry for the exhaust gas driving the charging device. The adjusting device may be designed such that at least one minimum set limit of the adjusting device and the maximum set limit of the adjusting dive are variably adjustable and readjustable. | 05-08-2014 |
| 20140133970 | Turbocharger and Variable-Nozzle Assembly Therefor - A variable-vane assembly includes a generally annular nozzle ring and an array of vanes rotatably mounted to the nozzle ring and connected to a rotatable actuator ring, and an insert having a tubular portion structured and arranged to be sealingly received into a bore of a turbine housing and having a nozzle portion extending generally radially out from one end of the tubular portion, the nozzle portion being axially spaced from the nozzle ring such that the vanes extend between the nozzle ring and the nozzle portion. A ring-shaped wire cage is disposed radially outwardly of the vanes and has one axial end rigidly affixed to the nozzle ring and an opposite axial end rigidly affixed to the nozzle portion so as to fix a spacing between the nozzle ring and the nozzle portion in an axial direction of the variable-vane assembly. | 05-15-2014 |
| 20140154057 | FRANCIS TURBINE OR A FRANCIS PUMP OR A FRANCIS PUMP TURBINE - The present invention provides a Francis turbine or any other machine built according to the Francis principle. The machine includes a blade wheel that has multiple blades, with at least one of the blades being adjustable. A spiral housing encloses the blade wheel. A traverse ring with multiple traverses has a portion with larger traverses that extends over a portion of a circumference of the blade wheel and starts at a beginning of a spiral. The traverse ring also has a portion with smaller traverses that extends over a further circumference of the blade wheel up to an end of the spiral. An inner blade wheel ring is provided downstream of the traverse ring. Also included is an outer guide blade ring which is disposed upstream of the traverse ring. | 06-05-2014 |
| 20140234085 | BUSHING ARRANGED BETWEEN A BODY AND A SHAFT, AND CONNECTED TO THE SHAFT - A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft. | 08-21-2014 |
| 20140234086 | BUSHING ARRANGED BETWEEN A BODY AND A SHAFT, AND CONNECTED TO THE SHAFT - A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft. | 08-21-2014 |
| 20140248137 | VARIABLE NOZZLE UNIT AND VARIABLE GEOMETRY SYSTEM TURBOCHARGER - A variable geometry system turbocharger includes a variable nozzle unit, which is disposed in a turbine housing by being sandwiched between the turbine housing and a bearing housing, and which adjusts a passage area for the exhaust gas to be supplied to a turbine impeller. The bearing housing includes a container recessed portion which contains a link mechanism of the variable nozzle unit. | 09-04-2014 |
| 20140248138 | VARIABLE GEOMETRY TURBINE - A variable geometry turbine comprises: a turbine wheel in a housing for rotation about a turbine axis; an annular inlet passage defined between respective radial inlet surfaces of first and second wall members, at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage; an array of vanes extending across the inlet passage, said vanes being connected to said first wall member; a complementary array of vane slots defined by the second wall member, said vane slots configured to receive said vanes to accommodate relative movement between the first and second wall members; the second wall member comprising at least two axially adjacent co-axial plates, a first plate defining a first array of openings which overlie a second array of openings defined by a second plate so as to define said array of vane slots, said first plate being fixed to said second plate. | 09-04-2014 |
| 20140334918 | VARIABLE NOZZLE UNIT AND VARIABLE GEOMETRY SYSTEM TURBOCHARGER - Three or more attachment pins are arranged on a right lateral surface of a nozzle ring at intervals. All the attachment pins are placed outside support holes in the nozzle ring in radial directions of the nozzle ring. A guide ring is provided across right lateral surfaces of the attachment pins. A first side guide member to support a right lateral surface of a drive ring in away that allows the right lateral surface to be in sliding contact therewith is provided to the right of the guide ring. A second side guide member to support a left lateral surface of the drive ring in a way that allows the left lateral surface to be in sliding contact therewith is provided to the left of the guide ring. | 11-13-2014 |
| 20140341718 | VARIABLE NOZZLE TURBOCHARGERS - Embodiments of the present invention may include a variable nozzle turbocharger having a variable nozzle mechanism for controlling a flow velocity of exhaust gas to a turbine wheel. The variable nozzle mechanism includes a plurality of variable nozzles, a unison ring and a biasing member. The variable nozzles each have a nozzle vane. The unison ring is configured to adjust a degree of opening of the variable nozzles through rotation of the unison ring. The biasing member biases the unison ring so as to open the variable nozzles. | 11-20-2014 |
| 20140341719 | VARIABLE NOZZLE TURBOCHARGERS - Embodiments of the present invention may include a variable nozzle turbocharger having a variable nozzle mechanism. The variable nozzle mechanism has a unison ring and a drive arm. The unison ring adjusts a degree of opening of variable nozzles having nozzle vanes through rotation of the unison ring. The unison ring has a first fit-engagement groove. The first fit-engagement groove has a closing side surface of a concave arcuate shape and an opening side surface of a convex arcuate shape facing the closing side surface with a fixed groove width therebetween. A drive arm has a first fit-engagement portion engaged with the first fit-engagement groove so that the first fit-engagement portion is rotatable and movable in the radial direction of the unison ring. The first fit-engagement portion has a closing side contact surface of a convex arcuate shape that is able to contact the closing side surface. | 11-20-2014 |
| 20150030438 | Axial Compressor - An axial compressor includes: a spray nozzle ( | 01-29-2015 |
| 20150110608 | RETENTION SYSTEM AND METHOD FOR VANE RING ASSEMBLY - A variable geometry turbocharger includes a vane pack having rotatable vanes constrained by a pair of vane rings held together by a plurality of pins. A first end of each pin can be configured with a head. Each pin is received in a pair of aligned apertures in the vane rings such that the head of each pin engages one of the vane rings. A second end of each pin is deformed (e.g., by orbital riveting) such that it engages the other vane ring. Thus, a clamp load is applied to the vane rings, which can control the parallelism and distance between the vane rings so that the vanes can rotate with a minimum clearance without jamming. Also, the pins can maintain vane axle apertures in the vane rings in the correct angular position relative to each other. Such a vane pack configuration can reduce process time and cost. | 04-23-2015 |
| 20150118028 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger (1) having a turbine (2), with a turbine wheel (3) surrounded by an intake duct (4), and a VTG cartridge (5), with a washer (6) and a vane bearing ring (7), which delimit the intake duct (4), and with a plurality of vanes (8), arranged in the intake duct (4) and mounted in the vane bearing ring (7) by way of rotatable vane shafts (9), which are connected to vane levers (10), the lever heads (11) of which engage into associated grooves (12) in a unison ring (13), which surrounds the vane bearing ring (7); and having a radial bearing between the unison ring (13) and the vane bearing ring (7). The vane levers (10) for forming the radial bearing are in the form of cam levers, the lever heads (11) of which are supported in the grooves (12). | 04-30-2015 |
| 20150118029 | EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger which has a radial bearing with a simple design which can quickly and easily be mounted. A pin/rolling roller arrangement is provided as the radial bearing. The pin is in this case fixed on the vane bearing ring. The rolling roller is placed onto the pin and, in the mounted state, an inner wall region of the unison ring is supported on the rolling roller mounted rotatably on the pin. | 04-30-2015 |
| 20150132112 | EXHAUST-GAS TURBOCHARGER - A variable turbine geometry (VTG) exhaust-gas turbocharger in which guide vanes are adjusted by means of a unison ring, the structure of which has a simpler and thus more cost-effective design. The number of components is reduced, for example for rollers on pins as are provided in the case of known bearings. A very beneficial relationship between friction radius and rolling radius in the given installation space is obtained. | 05-14-2015 |
| 20150315964 | ASYMMETRIC ACTUATOR PIVOT SHAFT BUSHING FOR VTG TURBOCHARGER - A turbocharger ( | 11-05-2015 |
| 20150361822 | VARIABLE AREA VANE ARRANGEMENT FOR A TURBINE ENGINE - An adjustable stator vane for a turbine engine includes a shaft, a flange and a stator vane body that pivots about a variable vane axis. The stator vane body extends axially between a first end and a second end. The stator vane body includes an airfoil, a cavity, and a body surface located at the first end. The cavity extends axially from an inlet in the body surface and into the airfoil. The shaft extends along the variable vane axis from the first end. The flange extends circumferentially around the inlet and the shaft, and radially from the stator vane body. | 12-17-2015 |
| 20150377252 | APPARATUS FOR TRANSFERRING ENERGY BETWEEN A ROTATING ELEMENT AND FLUID - Embodiments of an apparatus for transferring energy between a rotating element and a fluid are provided herein. In some embodiments, a plenum of an apparatus for transferring energy between a rotating element and a fluid may include a through hole disposed through the plenum; and a plurality of inlet guide vanes disposed proximate a peripheral edge of the through hole, the plurality of inlet guide vanes comprising a first group of inlet guide vanes having a cambered profile and a second group of inlet guide vanes disposed radially inward of the first group of inlet guide vanes, wherein the first group of inlet guide vanes are in a fixed position with respect to the plenum and the second group of inlet guide vanes are movable with respect to the plenum. | 12-31-2015 |
| 20160376914 | VARIABLE VANE ACTUATION SYSTEM - An example variable vane actuation system of a gas turbine engine includes, among other things, an actuation ring, a plurality of variable vanes circumferentially disposed about an engine axis, a plurality of vane arms configured to actuate the plurality of variable vanes, and a plurality of press fit members coupling the vane arms to the actuation ring. | 12-29-2016 |
| 20190145274 | VARIABLE DISPLACEMENT TURBOCHARGER | 05-16-2019 |
