# US 11,111,812 B2 · Turbine arrangement for an exhaust gas turbocharger > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,111,812 B2 - Document ID: US11111812B2 - Status: Granted - Kind: B2 - Application number: 16/954,611 - Filed: 2018-12-17 - Published: 2020-10-22 - Granted: 2021-09-07 - Earliest claimed: 2017-12-18 - Assignees: BorgWarner Inc. - Applicants: BorgWarner Inc. - Inventors: Thomas Ramb; Gerald Schall - Web page: https://patentgrep.com/patent/US11111812B2 ## CPC - F01D 17/165: {for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line (F01D17/167 takes precedence)} - F02B 37/24: by using pumps or turbines with adjustable guide vanes - F02C 6/12: Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure - F05D 2220/40: in turbochargers - Y02T 10/12: Improving ICE efficiencies - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02B: INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL (gas-turbine plants F02C; hot-gas or combustion-product positive-displacement engine plants F02G) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A turbine arrangement for an exhaust gas turbocharger includes a turbine housing, a turbine wheel that is arranged in the turbine housing and has an axis of rotation, and a variable turbine geometry arrangement (VTG arrangement). The VTG arrangement includes a bearing ring, a disc, multiple vanes rotatably mounted in the bearing ring, and a contour sleeve that is coupled with the disc. The turbine housing comprises an axial stop, against which the contour sleeve stops in order to secure the VTG arrangement in an axial direction within the turbine housing. ## Claims ### Claim 1 A turbine arrangement for an exhaust gas turbocharger comprising a turbine housing; a turbine wheel, which is arranged in the turbine housing and has an axis of rotation; a variable turbine geometry arrangement (VTG arrangement) comprising a bearing ring; a disc; and multiple vanes rotatably mounted in the bearing ring, said vanes arranged between the bearing ring and the disc; and a contour sleeve which is coupled with the disc; characterized in that the turbine housing comprises an axial stop, against which the contour sleeve stops in order to secure the VTG arrangement in an axial direction within the turbine housing, wherein the contour sleeve comprises a cylinder section and an annular section, wherein the annular section adjoins the disc and the cylinder section comprises an end area and an intermediate area, and wherein the intermediate area is arranged between the end area and the annular section and a wall thickness of the contour sleeve is smaller in the intermediate area than in the end area. ### Claim 2 (depends on 1) The turbine arrangement according to claim 1, characterized in that a front face of the contour sleeve interacts with a radial stop surface of the stop. ### Claim 3 (depends on 1) The turbine arrangement according to claim 1, characterized in that the contour sleeve and the disc are in the form of one piece. ### Claim 4 (depends on 1) The turbine arrangement according to claim 1, characterized in that a front guide baffle is also provided, wherein said front guide baffle comprises a first annular element, which is coupled with the bearing ring, and a second annular element, which is coupled with the disc; and wherein multiple spacers, in particular in the form of guide elements, are arranged between the first annular element and the second annular element. ### Claim 5 (depends on 1) The turbine arrangement according to claim 1, characterized in that at least 50%, more particularly at least 70%, and preferably at least 75% of the surface of a rear side of the disc is left free. ### Claim 6 (depends on 1) The turbine arrangement according to claim 1, characterized in that a securing means is also provided, wherein said securing means is arranged in an axial direction between the VTG arrangement and a turbine rear wall. ### Claim 7 (depends on 6) The turbine arrangement according to claim 6, characterized in that the securing means is in the form of a disc spring. ### Claim 8 (depends on 6) The turbine arrangement according to claim 6, characterized in that a front face of the contour sleeve interacts with a radial stop surface of the stop. ### Claim 9 (depends on 6) The turbine arrangement according to claim 6, characterized in that the contour sleeve comprises a cylinder section and an annular section, wherein the annular section adjoins the disc. ### Claim 10 (depends on 6) The turbine arrangement according to claim 6, characterized in that a radially outward end of the securing means lies against the bearing ring, and a radially inward end lies against the turbine rear wall. ### Claim 11 (depends on 10) The turbine arrangement according to claim 10, characterized in that the securing means is in the form of a disc spring. ### Claim 12 (depends on 1) The turbine arrangement according to claim 1, characterized in that the contour sleeve and the disc are designed as two separate components. ### Claim 13 (depends on 12) The turbine arrangement according to claim 12, characterized in that the disc comprises ceramic material, in particular wherein the disc is manufactured entirely from ceramic material. ### Claim 14 (depends on 1) The turbine arrangement according to claim 1, characterized in that a gap is formed in an axial direction between the annular section of the contour sleeve and the turbine housing. ### Claim 15 An exhaust gas turbocharger for a combustion engine comprising a compressor and a turbine arrangement comprising a turbine housing; a turbine wheel, which is arranged in the turbine housing and has an axis of rotation; a variable turbine geometry arrangement (VTG arrangement) comprising a bearing ring; a disc; and multiple vanes rotatably mounted in the bearing ring, said vanes arranged between the bearing ring and the disc; and a contour sleeve which is coupled with the disc; characterized in that the turbine housing comprises an axial stop, against which the contour sleeve stops in order to secure the VTG arrangement in an axial direction within the turbine housing, and wherein the contour sleeve comprises a cylinder section and an annular section, wherein the annular section adjoins the disc and the cylinder section comprises an end area and an intermediate area, and wherein the intermediate area is arranged between the end area and the annular section and a wall thickness of the contour sleeve is smaller in the intermediate area than in the end area. ### Claim 16 (depends on 15) The exhaust gas turbocharger according to claim 15, characterized in that a securing means is also provided, wherein said securing means is arranged in an axial direction between the VTG arrangement and a turbine rear wall. ### Claim 17 (depends on 16) The exhaust gas turbocharger according to claim 16, characterized in that a radially outward end of the securing means lies against the bearing ring, and a radially inward end lies against the turbine rear wall. ### Claim 18 (depends on 16) The exhaust gas turbocharger according to claim 16, characterized in that the securing means is in the form of a disc spring. ### Claim 19 A turbine arrangement for an exhaust gas turbocharger comprising a turbine housing; a turbine wheel, which is arranged in the turbine housing and has an axis of rotation; a variable turbine geometry arrangement (VTG arrangement) comprising a bearing ring; a disc; and multiple vanes rotatably mounted in the bearing ring, said vanes arranged between the bearing ring and the disc; and a contour sleeve which is coupled with the disc; characterized in that the turbine housing comprises an axial stop, against which the contour sleeve stops in order to secure the VTG arrangement in an axial direction within the turbine housing, and characterized in that a front guide baffle is also provided, wherein said front guide baffle comprises a first annular element, which is coupled with the bearing ring, and a second annular element, which is coupled with the disc; and wherein multiple spacers, in particular in the form of guide elements, are arranged between the first annular element and the second annular element.