Cummins Turbo Technologies Limited

Cummins Inc.

Holset Engineering Company, Limited

Stephen E Garrett

John Frederick Parker

James Alexander McEwen

Robert L Holroyd

Tom J Roberts

Tim Denholm

Christopher Normington

Arun Vijayakumar

Simon David Moore

Michael Voong

Samuel C Geckler

Anthony Kyle Perfetto

Adrian P Dale

Lee J Robinson

John Bywater

David Andrew Luck

Nicholas Kenneth Sharp

James Alexander Mcewen

Henry David Lambton Carr

Michael David Dolton

Arun Tamil Selvan Vijayakumar

Richard Owen Evans

Simon Moore

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.

Turbomachine

A unique engine system has an engine with a dedicated exhaust gas recirculation cylinder, an EGR system that receives exhaust gas from the dedicated cylinder, and a turbocharger having turbine inlet ports in fluid communication with other engine cylinders via a plurality of exhaust passages. At least two of the exhaust passages are substantially isolated from each other. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for engines and engine systems.

Engine systems and methods for operating an engine

A variable geometry turbine comprises: a turbine wheel in a housing assembly defining a radial gas flow inlet passage; an annular wall member which is displaceable to control gas flow through the inlet passage; and a linkage mechanism comprising at least one actuating member operably connected to the annular wall member to control displacement of the wall member. The actuating member has a terminal portion defining a radially extending flange and extends in a direction substantially parallel to the turbine axis through an aperture defined by a retaining member to locate the radially extending flange in between said retaining member and annular wall member. The terminal portion is contacted by the retaining member to connect the actuating member to the annular wall member. The aperture defines a clearance to accommodate displacement of the retaining member relative to the actuating member.

Variable geometry turbine

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.

Variable geometry turbine and assembly thereof

A turbine wheel mounted within a housing rotating about a turbine axis; a gas flow control passage upstream of the turbine wheel between a radial first surface of a movable wall member and a facing wall of the housing, the movable wall member comprising second and third surfaces opposing the first surface. The movable wall member moves in an axial direction to vary the size of the gas flow control passage. A first gas region of the turbine, being upstream of the gas flow control passage, includes a portion of the gas flow control passage; a second gas region of the turbine downstream of the gas flow control passage containing 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.

A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis. The housing defines an annular inlet passage around an inducer portion of the turbine wheel and an outlet passage including a tubular wall disposed around an exducer portion of the turbine wheel; the inlet passage is defined between first and second radial inlet surfaces, one of the inlet surfaces being defined by a moveable wall member and the other of the inlet surfaces being defined by a facing wall of said housing. The moveable wall member is moveable relative to the facing wall of the housing along the turbine axis to vary the size of the inlet passageway. The moveable wall member is displaceably mounted within an annular cavity defined between the tubular wall and a surrounding wall of the housing.

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.

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.

A variable geometry turbine comprises: a turbine wheel mounted within a housing assembly for rotation about a turbine axis, the housing assembly defining a radial gas flow inlet passage; an annular wall member defining one 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; and a linkage mechanism comprising at least one actuating member operably connected to the annular wall member to control displacement of the wall member. The actuating member extends in a direction substantially parallel to the turbine axis through an aperture defined by a retaining member such that a first bearing surface defined by the actuating member extending transverse to the turbine axis is contacted by a surface of the retaining member so as to connect the actuating member to the annular wall member. The aperture is appropriately dimensioned to define a clearance between a wall of the aperture and a portion of the actuating member located within the aperture so as to accommodate displacement of the retaining member, resulting from displacement of the annular wall member, relative to the actuating member.

A variable geometry turbine has a gas inlet chamber and a gas flow inlet passage downstream of the inlet chamber and upstream of said turbine wheel. The inlet passage is defined between a moveable first wall and a second wall and an actuator is operable to control displacement of the first wall in order to vary the size of the gas flow inlet passage. A piston member defining the first wall or being connected to it is received in a piston chamber and serves to move the first wall as a result of displacement of the piston member in the piston chamber. A bypass passage defined in the housing and extends between the piston chamber and a location in the turbine upstream of the inlet passage for delivering gas to the piston chamber. The bypass passage is disposed such that gas introduced through the bypass passage pressurizes the chamber and applies a force to displace the piston member in a direction that causes the first wall to move towards the second wall. The gas, which may be the exhaust gas from an engine, thus serves to assist the operation of the actuator.

A turbomachine system comprises a first turbocharger comprising an exhaust gas flow first turbine for location in an exhaust path and a first compressor driven by said first turbine; a turbomachine for location in the exhaust path upstream or downstream of said first turbocharger and comprising an exhaust gas flow second turbine and a second compressor driven by said second turbine. The first turbine has an outlet that is in fluid communication with an inlet of the second turbine. One of said first and second turbines is a radial outflow turbine. The arrangement provides for a relatively compact package. The radial outflow turbine may have a particular structure in which there is provided a deflector member at or near its inlet for directing the gas outwards, a stator for introducing swirl and a downstream turbine rotor. A shroud is fixed to blades of the turbine rotor to prevent leakage and to provide additional structural rigidity.

Turbomachine system and turbine therefor

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 has a circumferential array of vanes () that are received in corresponding slots () in the facing wall. A wastegate valve () is provided in a chamber behind the facing wall and gas bypasses the turbine through the chamber to the wastegate port () at high flow rates.

Variable geometry turbine with wastegate

A turbocharger comprises a turbine wheel () mounted within a housing assembly () for rotation about a turbine axis, a gas flow inlet passage () upstream of the turbine wheel (), and a gas flow control mechanism () located within the housing assembly () upstream of the turbine wheel () and operable to control gas flow through said gas flow inlet passage (). An actuator assembly is mounted to the housing assembly and comprises: A lead screw including a lead screw shaft () defining a lead screw axis, and a lead screw nut () threadedly engaged on a threaded portion of the lead screw shaft (). The lead screw () being arranged so that rotation of one of said shaft and nut relative to the housing assembly produces linear movement in the other of said shaft and nut in the direction of the lead screw axis: The lead screw () engages the gas flow control mechanism () at a location within a housing cavity defined within said housing assembly ().

Growing community of inventors

Huddersfield, United Kingdom

Stephen E Garrett