# US 2024/0200466 A1 · Adjustment ring for a variable turbine geometry > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2024/0200466 A1 - Document ID: US20240200466A1 - Status: Published application - Kind: A1 - Application number: 18/112,900 - Filed: 2023-02-22 - Published: 2024-06-20 - Earliest claimed: 2022-12-15 - Assignees: BorgWarner Inc. - Applicants: BorgWarner Inc. - Inventors: Nico Kanoffsky; Thomas Ramb - Web page: https://patentgrep.com/patent/US20240200466A1 ## 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)} - F01D 9/04: forming ring or sector - F01D 17/162: {for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence)} - F02B 37/24: by using pumps or turbines with adjustable guide vanes - F02C 9/22: by adjusting turbine vanes - F05D 2220/40: in turbochargers - 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 ## Abstract An adjustment ring (200) for a variable turbine geometry (100). The adjustment ring (200) comprises a disk-shaped body (210) and a plurality of coupling regions (220) which are configured in the disk-shape body (210). The coupling regions (220) are spaced apart in the circumferential direction (26), and each coupling region (220) is adapted for at least partially receiving a vane lever (140) for adjusting a guide vane (120) of a variable turbine geometry (100). Each coupling region (220) circumferentially is fully surrounded by the disk-shaped body (210). The disk-shaped body (210) on one or more of the coupling regions (220) has at least one reinforcement means (230) which extends in the axial direction (22) from the disk-shaped body (210) and circumferentially at least partially surrounds the coupling region (220). ## Claims ### Claim 1 An adjustment ring (200) for a variable turbine geometry (100), comprising: a disk-shaped body (210); and a plurality of coupling regions (220) which are configured in the disk-shaped body (210); the coupling regions (220) being spaced apart in the circumferential direction (26); and each coupling region (220) being conceived for at least partially receiving a blade lever (140) for adjusting a guide vane (120) of a variable turbine geometry (100), wherein each coupling region (220) circumferentially is fully surrounded by the disk-shaped body (210); and wherein the disk-shaped body (210) on one or a plurality of coupling regions (220) has at least one reinforcement feature (230) which extends in the axial direction (22) from the disk-shaped body (210) and circumferentially at least partially surrounds the coupling region (220). ### Claim 2 (depends on 1) The adjustment ring (200) as claimed in claim 1, wherein the disk-shaped body (210) on each coupling region (220) of the plurality of coupling regions (220) has the at least one reinforcement feature (230). ### Claim 3 (depends on 1) The adjustment ring (200) as claimed in claim 1, wherein each coupling region (220) is configured as a passage in the disk-shaped body (210). ### Claim 4 (depends on 1) The adjustment ring (200) as claimed in claim 1, wherein each coupling region (220) has an encircling wall (221). ### Claim 5 (depends on 1) The adjustment ring (200) as claimed in claim 1, wherein the at least one reinforcement feature (230) is configured so as to be integral to the disk-shaped body (210). ### Claim 6 (depends on 1) The adjustment ring (200) as claimed in claim 1, wherein the at least one reinforcement feature (230) is configured so as to be collar-shaped. ### Claim 7 (depends on 1) The adjustment ring (200) as claimed in claim 1, wherein the at least one reinforcement feature (230) circumferentially fully surrounds the coupling region (220). ### Claim 8 (depends on 1) The adjustment ring (200) as claimed in claim 1, wherein the disk-shaped body (210) has a first lateral face (211) and a second lateral face (212). ### Claim 9 (depends on 8) The adjustment ring (200) as claimed in claim 8, wherein the at least one reinforcement feature (230) extends from the first lateral face (211) and/or from the second lateral face (212). ### Claim 10 (depends on 8) The adjustment ring (200) as claimed in claim 8, wherein the at least one reinforcement feature (230) comprises a first reinforcement feature (231) and a second reinforcement feature (232), the first reinforcement feature (231) extending from the first lateral face (211), and the second reinforcement feature (232) extending from the second lateral face (212). ### Claim 11 (depends on 1) The adjustment ring (200) as claimed in claim 1, wherein the at least one reinforcement feature (230) extends up to an axial distance (x2) in the axial direction (22), and wherein the disk-shaped body (210) has a body thickness (x1) measured in the axial direction (22), wherein a ratio of the axial distance (x2) to the body thickness (x1) is between 0.25 and 1.0. ### Claim 12 (depends on 11) The adjustment ring (200) as claimed in claim 11, wherein a ratio of the axial distance (x2) to the body thickness (x1) is between 0.40 and 0.70. ### Claim 13 (depends on 11) The adjustment ring (200) as claimed in claim 11, wherein a ratio of the axial distance (x2) to the body thickness (x1) is between 0.45 and 0.60. ### Claim 14 (depends on 11) The adjustment ring (200) as claimed in claim 11, wherein the at least one reinforcement feature (230) has a minimum width (b1) measured in the radial direction (24), a ratio of the minimum width (b1) to the body thickness (x1) being between 0.10 and 0.70. ### Claim 15 (depends on 14) The adjustment ring (200) as claimed in claim 14, wherein a ratio of the minimum width (b1) to the body thickness (x1) is between 0.15 and 0.50. ### Claim 16 (depends on 1) A variable turbine geometry (100) for a turbine (10), comprising: a blade bearing ring (110); a plurality of adjustable guide vanes (120) which are in each case rotatably mounted in the blade bearing ring (110) by way of one blade shaft (130); an adjustment ring (200) as claimed in claim 1, wherein each guide vane (130) of the plurality of adjustable guide vanes (130) is in each case connected in a rotationally fixed manner to one blade lever (140), and wherein each blade lever (140) is in each case at least partially received in a coupling region (220) for adjusting the respective guide vane (120). ### Claim 17 (depends on 16) The variable turbine geometry (100) as claimed in claim 16, wherein each blade lever (140) has a radial blade lever portion (141) which extends radially from the blade shaft (130), and has an axial blade lever portion (142) which extends axially toward the adjustment ring (200) from the radial blade lever portion (141), wherein the axial blade lever portion (142) extends axially at least partially into the respective coupling region (220). ### Claim 18 (depends on 16) A turbine (10) for a charging device (1), comprising: a turbine housing (11) which defines a feed duct (13) and an outlet duct (14); a turbine wheel (12) which, in the turbine housing (11), is disposed between the feed duct (13) and the outlet duct (14); and a variable turbine geometry (100) as claimed in claim 16, wherein the variable turbine geometry (100) is disposed radially outside the turbine wheel (12). ### Claim 19 (depends on 18) A charging device (1) for an internal combustion engine or a fuel cell, comprising: a bearing housing (40); a shaft (30) which is rotatably mounted in the bearing housing (40); a compressor (50) having a compressor wheel (52); and a turbine (10) as claimed in claim 18, wherein the turbine wheel (12) and the compressor wheel (52) are coupled in a rotationally fixed manner to the shaft (30) at opposite ends of the shaft (30). ### Claim 20 A method for producing an adjustment ring (200) for a variable turbine geometry (100), said method comprising the following steps: a) providing a disk-shaped body (210); b) configuring a plurality of coupling regions (220) in the disk-shaped body (210) in such a manner that the coupling regions (220) are spaced apart in the circumferential direction (26), and each coupling region (220) is conceived for at least partially receiving a blade lever (140) for adjusting a guide vane (120) of a variable turbine geometry (100), and each coupling region (220) circumferentially is fully surrounded by the disk-shaped body (210); c) configuring at least one reinforcement feature (230) on one a plurality of coupling regions (220) in such a manner that the at least one reinforcement feature (230) extends from the disk-shaped body (210) in the axial direction (22) and circumferentially at least partially surrounds the coupling region (220).