Cummins Turbo Technologies Limited Patent applications |
Patent application number | Title | Published |
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 |
20140147255 | VARIABLE GEOMETRY TURBINE - 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. | 05-29-2014 |
20140144134 | MULTI-STAGE TURBOCHARGER SYSTEM - A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger ( | 05-29-2014 |
20140133969 | 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. | 05-15-2014 |
20140130351 | VARIABLE GEOMETRY TURBOMACHINE - A method for assembling a variable geometry turbomachine with a bearing housing, an adjacent turbine housing, a turbine wheel rotating in the turbine housing about a turbine axis; an inlet passage upstream of the turbine wheel between inlet surfaces of first and second wall members, one wall member moveable along the turbine axis to vary the inlet passage size; vanes across the inlet passage connected to a first wall member; an array of vane slots defined by the second wall member to receive the vanes for relative movement between the wall members; the second wall member comprising a shroud defining vane slots; the second wall member supported by a support member retained by a mounting feature; the mounting feature being one of the bearing housings, the turbine housing, or the actuation element; and the shroud is fixed to the support member. | 05-15-2014 |
20140105730 | 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. | 04-17-2014 |
20130239569 | GAS EXPANDER SYSTEM - A gas expander system suitable for use in a turbomachine, the gas expander system comprising: a gas expander provided with a moveable part; a magnetic gear arrangement; and a shaft; the moveable part of the gas expander being connectable to a load via the magnetic gear arrangement and the shaft, and movement of the moveable part of the gas expander being arranged to cause movement of the shaft, wherein the magnetic gear arrangement is used in a closed loop heat recovery system, with the inner and outer rotors of the magnetic gear separated by a wall that contains the stator. | 09-19-2013 |
20130189094 | MULTISTAGE COMPRESSOR WITH IMPROVED MAP WIDTH PERFORMANCE - A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between said passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, hi other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width. | 07-25-2013 |
20130142621 | MULTISTAGE COMPRESSOR WITH IMPROVED MAP WIDTH PERFORMANCE - A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between said passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, hi other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width. | 06-06-2013 |
20130094938 | TURBOMACHINE - A turbomachine comprising a housing defining a bearing cavity and a turbine chamber separated by a first wall, a heat shield disposed between the first wall and the turbine wheel, a heat shield cavity defined between the first wall and the heat shield. The shaft extends through a passage defined in part by a first aperture in the wall and a second aperture in the heat shield. A first seal is provided between the shaft and the first aperture. The housing defines a first gas channel communicating with the heat shield cavity for connection to a pressure source for raising pressure within the heat shield cavity. A second channel is provided between the heat shield cavity and the passage, the second channel opening to the passage on the opposite side of the first seal to the bearing assembly. A second seal is provided between the shaft and the second aperture. | 04-18-2013 |
20090160091 | Method and apparatus for manufacturing turbine or compressor wheels - A method for forming a turbine or compressor wheel from a semi-solid material uses a die assembly that has an inner cartridge made up from a plurality of segments and an outer die. The semi-solid material is injected under pressure and high temperature into the die so that it flows into blade cavities defined between the segments of the cartridge. The cartridge is removed from the outer die and the segments are then separated to release the wheel. | 06-25-2009 |