| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415157000 | Single, axially movable cylinder or plate | 20 |
| 20090003994 | Turbine of a Turbocharger - A turbine of a turbocharger comprises a floating insert which defines a nozzle for passing a fluid and which is supported axially slidable with respect to a housing by a sliding support means. Furthermore, the turbine comprises a gas shielding for preventing a flow of said fluid from impinging on said sliding support means. | 01-01-2009 |
| 20090003995 | Exhaust Gas Turbocharger With Adjustable Slide Ring - A turbine of a turbocharger comprises a floating insert which defines a nozzle for passing a fluid and which is supported axially slidable with respect to a housing by a sliding support means. Furthermore, the turbine comprises a sealing means for preventing a flow of said fluid between said floating insert and said housing. | 01-01-2009 |
| 20100316490 | TURBOCHARGER HAVING NOZZLE RING LOCATING PIN AND AN INTEGRATED LOCATOR AND HEAT SHIELD - A turbocharger with a variable nozzle includes a pin mounted in the center housing and extending axially therefrom and engaged in a hole in the nozzle ring to orient the nozzle ring rotationally relative to the center housing. A portion of a length of the pin has a substantially greater compliance than the remainder of the length such that the pin has a flexible tip that engages the hole in the nozzle ring. The flexible tip reduces constraint of thermal deformation of the nozzle ring. The pin portion of greater compliance can be a section of the tube that is slit and expanded. The turbocharger can also include a one-piece locator and heat shield having a locating portion abutting the center housing and the nozzle ring for radially locating the nozzle ring relative to the center housing, and having a shield portion shielding the center housing from hot exhaust gas. | 12-16-2010 |
| 20110097197 | NOZZLE ASSEMBLY OF VARIABLE GEOMETRY TURBOCHARGER - According to the present invention, it is possible to achieve improved durability by improving the connection structure of operation links and a control ring to reduce friction and wear between the operation links and the control ring, facilitate manufacturing by simple configuration and structure, and achieve silent and stable operation by making it possible to set the gaps between the parts relatively small. | 04-28-2011 |
| 20110116911 | VARIABLE GEOMETRY TURBINE - A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis. An exhaust gas inlet passageway is defined between a shroud and a wall of a nozzle ring. The shroud is moveable in the axial direction to vary the size of the inlet passageway. The nozzle ring has an array of vanes that extends across the inlet passageway. An array of openings is provided in the shroud for receipt of the array of vanes. The shroud is part of a substantially annular axially moveable sleeve that is slidably disposed on an annular supporting wall. At least one biasing member is disposed between the moveable sleeve and the support and is designed to apply a circumferentially distributed force in the radial direction so as to maintain concentric alignment of the supporting wall and the sleeve. | 05-19-2011 |
| 20110194929 | TURBOMACHINE - According to a first aspect of the present invention there is provided a variable geometry turbine comprising: a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls, the annular inlet being divided into at least two axially offset inlet portions; a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet; and a guide for guiding the movement of the cylindrical sleeve, the guide being at least partially located within the inlet at a radially extent of the inlet portions, and extending in an axial direction parallel to the turbine axis. | 08-11-2011 |
| 20120251298 | TURBINE - According to an aspect of the invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the annular inlet, the annular inlet being divided into at least two axially offset inlet portions; and a ring-like seal adjacent a free end of the sleeve, at least a part of the ring-like seal being located in-between the sleeve and the inlet portions, or a structure defining the inlet portions. | 10-04-2012 |
| 20130315718 | TURBOMACHINE - A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The turbine further comprises a cylindrical sleeve that is axially movable across the annular inlet to vary the size of a gas flow path through the inlet. The annular inlet is divided into at least two axially offset inlet passages. The inner diameter of the sleeve is greater than the inner diameter of the inlet passages. | 11-28-2013 |
| 20140072413 | GAS TURBINE ENGINE SYNCHRONIZING RING WITH MULTI-AXIS JOINT - An assembly includes a synchronizing ring, a vane arm, and a multi-axis joint. The multi-axis joint connects the synchronizing ring to the vane arm and provides the vane arm with movement about a first pivot axis and a second pivot axis. | 03-13-2014 |
| 20150063989 | COMPRESSOR OF TURBOCHARGER - A compressor of a turbocharger including a compressor housing and a compressor impeller. The compressor housing includes: a compressor flow passage, a compressor air inlet, and a compressor air outlet. The compressor impeller includes an impeller feeding flow passage. The compressor impeller is disposed inside the compressor housing. The compressor flow passage is disposed inside the compressor housing. The compressor flow passage is connected to the compressor air inlet and the compressor air outlet. The impeller air feeding flow passage is connected to the compressor air inlet and the compressor flow passage. | 03-05-2015 |
| 20150098804 | EXTERNAL ACTUATOR FOR AN IMPELLER SHROUD OF A VARIABLE WATER PUMP - An external actuator for a variable water pump is provided having an actuator housing with an outer wall with a plurality of radially inwardly directed projections, and a drive ring rotatably mounted in the housing. The drive ring has an internal thread. The projections contact an outer surface of the drive ring to define a plurality of hydraulic chambers that are divided by vanes extending from the drive ring into first and second chamber portions. A control valve controls a flow of pressurized hydraulic fluid to the chambers to rotate the drive ring in both directions or hold it in position. A drive nut having external threads is located within the drive ring and rotation of the drive ring causes an axial displacement of the drive nut. An actuator pin connected to the drive nut extends into the water pump housing to actuate the variable flow impeller. | 04-09-2015 |
| 20150125274 | INLET GUIDE VANE DEVICE - An inlet guide van device having a central axis comprises a first base, a guide sleeve, a blade, a second base, a transmission disk, and an actuator. The first base has at least one first support groove and at least one guide groove. The first support groove extends along a radial direction of the central axis, and the at least one guide groove is located in the first support groove. The guide sleeve is disposed on the first support groove in a manner that the guide sleeve is capable of moving along the radial direction. The guide sleeve has a sliding sleeve, an upper guide post and a lower guide post, the sliding sleeve has a through hole extending along the radial direction. The upper guide post and the lower guide post pass through the sliding groove, and the lower guide post is movably disposed on the guide groove. | 05-07-2015 |
| 20150377060 | Airflow Modulation System and Method - The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine. | 12-31-2015 |
| 20160061103 | TURBOMACHINE - A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The turbine further comprises a cylindrical sleeve that is axially movable across the annular inlet to vary the size of a gas flow path through the inlet. The annular inlet is divided into at least two axially offset inlet passages. The inner diameter of the sleeve is greater than the inner diameter of the inlet passages. | 03-03-2016 |
| 415158000 | Movable to position surrounding blade | 6 |
| 20110020111 | TURBOCHARGER - According to an aspect of the present invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted on a turbine shaft within a housing assembly for rotation about a turbine axis, the housing assembly defining a gas flow inlet passage upstream of the turbine wheel; an annular wall member defining a wall of the inlet passage and which is displaceable in a direction substantially parallel to the turbine axis to control gas flow through the inlet passage; at least one moveable rod operably connected via a first end of the rod to the annular wall member, the rod being moveable to control displacement of the annular wall member, the rod extending in a direction substantially parallel to the turbine axis, the rod being connected to the annular wall member via a first arm and a second arm, a first end of the first arm and a first end of the second arm being attached to the rod, and a second end of the first arm being attached to the annular wall member at a first circumferential position, and a second end of the second arm being attached to the annular wall member at a second, different circumferential position, the first arm and the second arm being resilient in order to allow relative movement between the first end of the rod and the annular wall member during expansion of the annular wall member. | 01-27-2011 |
| 20110110766 | TURBOMACHINE - A variable geometry turbine comprises a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet; wherein the annular inlet is divided into at least three axially offset annular inlet portions by two or more axially spaced annular baffles disposed between the first and second inlet sidewalls; inlet vanes extending axially into at least one of the inlet portions and defining circumferentially adjacent inlet passages; and wherein each of at least two of said baffles extends radially inboard of inlet vanes which extend into at least one of the inlet portions axially adjacent the respective baffle, and wherein a distance between an inner diameter of a first baffle of said at least two of said baffles and a trailing edge of a radially innermost vane in one of said annular inlet portions adjacent the first baffle is greater than a distance between an inner diameter of a second baffle of said at least two of said baffles and a trailing edge of a radially innermost vane in one of said annular inlet portions adjacent the second baffle. | 05-12-2011 |
| 20120114464 | VARIABLE GEOMETRY TURBINE AND ASSEMBLY THEREOF - A variable geometry turbine has a housing for receipt of the turbine wheel. A gas flow control mechanism in the housing upstream of said turbine wheel is operable to control gas flow through a gas flow inlet passage. The control mechanism has a movable nozzle ring or shroud for varying the size of the gas flow inlet passage. A transmission mechanism for connection between an actuator and the control mechanism converts movement applied by the actuator into movement shroud or nozzle ring. The transmission mechanism comprises a yoke having a shaft that is rotatably supported by a wall of the housing. The yoke defines arms that extend outwardly of the shaft and which engage with the shroud or nozzle ring. There is provided at least one recess defined in an inside surface of the housing, the recess extending from shaft rotation axis and configured to allow passage of an end of the yoke shaft along it during insertion of the yoke into the housing. | 05-10-2012 |
| 20120128471 | VARIABLE GEOMETRY TURBINE - A variable geometry turbine comprises a turbine wheel mounted within a housing for rotation about a turbine axis; and a gas flow control passage upstream of said turbine wheel, the gas flow control passage being defined at least in part between a radial first surface of a movable wall member and a facing wall of the housing, the movable wall member also comprising second and third surfaces which oppose the first surface. The movable wall member is movable in an axial direction so as to vary the size of the gas flow control passage. There is a first gas region of the turbine, a portion of which is upstream of the gas flow control passage, the first gas region including at least a portion of the gas flow control passage; a second gas region of the turbine downstream of the gas flow control passage which contains the turbine wheel; and a third gas region of the turbine downstream of the turbine wheel. The first gas region comprises the first and second surfaces, and the second gas region or third gas region comprises the third surface. | 05-24-2012 |
| 20120189433 | VARIABLE GEOMETRY TURBINE - A variable geometry turbine comprising: a housing; a turbine wheel supported in the housing for rotation; an annular inlet passage defined between respective inlet surfaces defined by an annular nozzle ring and a facing annular shroud; the nozzle ring can vary the size of the inlet passage; a circumferential array of inlet vanes; the shroud covering the opening of a shroud cavity defined by the housing inlet passage and inboard of the shroud, and defining a circumferential array of slots, the slots and shroud cavity being configured to receive said vanes accommodating movement of the nozzle ring; wherein the annular shroud comprises an outer flange, the outer flange defining a circumferential groove for receiving a retaining ring for securing the shroud in the opening of the shroud cavity and defined on an inboard side by a flange wall; wherein an annular flange rim extends axially inboard from said flange wall. | 07-26-2012 |
| 20150125275 | VARIABLE GEOMETRY SYSTEM TURBOCHARGER - A bottom surface of a housing recess of a turbine housing includes a close attachment portion in a continuous annular land shape, which is located radially outside a fitting recess. The close attachment portion is closely attached to a portion radially outside first support holes in a surface of a shroud ring opposite from its facing surface, by a fastening force of attachment bolts. The first support holes in the shroud ring communicate with an outlet side of a turbine impeller through a connection path and a cutout. | 05-07-2015 |
