# US 2014/0360160 A1 · Variable geometry turbine vane > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0360160 A1 - Document ID: US20140360160A1 - Status: Published application - Kind: A1 - Application number: 13/915,452 - Filed: 2013-06-11 - Published: 2014-12-11 - Earliest claimed: 2013-06-11 - Assignees: Ford Global Technologies, LLC - Applicants: Ford Global Technologies, LLC - Inventors: Harold Huimin Sun; Liangjun Hu; Ben Zhao; Dave R. Hanna - Web page: https://patentgrep.com/patent/US20140360160A1 ## CPC - F02B 37/22: by varying cross-section of exhaust passages or air passages {, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits} (F02B37/24 takes precedence) - 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 - F05D 2220/40: in turbochargers - F02B: INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL (gas-turbine plants F02C; hot-gas or combustion-product positive-displacement engine plants F02G) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract Embodiments may provide variable geometry turbine, a nozzle vane for a variable geometry turbine, and a method. The variable geometry turbine that may include a turbine wheel and a plurality of adjustable vanes radially positioned around the turbine wheel. The turbine may also include a flow disrupting feature on one or more outside surfaces of one or more of the plurality of adjustable vanes. ## Claims ### Claim 1 A variable geometry turbine comprising: a turbine wheel; a plurality of adjustable vanes radially positioned around the turbine wheel; and a flow disrupting feature on one or more outside surface of one or more of the plurality of adjustable vanes. ### Claim 2 (depends on 1) The variable geometry turbine of claim 1, wherein the flow disrupting feature is a plurality of flow disrupting features each adjacent to a respective trailing edge of the plurality of adjustable vanes. ### Claim 3 (depends on 2) The variable geometry turbine of claim 2, wherein each flow disrupting feature occupies approximately 10% to 40% of a surface area of one side of each of the plurality of adjustable vanes. ### Claim 4 (depends on 1) The variable geometry turbine of claim 1, wherein the flow disrupting feature includes a groove. ### Claim 5 (depends on 1) The variable geometry turbine of claim 1, wherein the flow disrupting feature includes two or more parallel grooves each having a substantially rectangular cross section. ### Claim 6 (depends on 1) The variable geometry turbine of claim 1, wherein the flow disrupting feature includes a dimple. ### Claim 7 (depends on 1) The variable geometry turbine of claim 1, wherein the flow disrupting feature includes a plurality of substantially round dimples. ### Claim 8 (depends on 1) The variable geometry turbine of claim 1, wherein the flow disrupting feature includes a plurality of substantially rectangular dimples. ### Claim 9 (depends on 1) The variable geometry turbine of claim 1, wherein the flow disrupting feature is adjacent to a first side of a bottom of each of the one or more of the plurality of adjustable vanes. ### Claim 10 (depends on 1) The variable geometry turbine of claim 1, wherein the flow disrupting feature is adjacent to a second side of a bottom of each of the one or more of the plurality of adjustable vanes. ### Claim 11 (depends on 1) The variable geometry turbine of claim 1, wherein the plurality of adjustable vanes are adjustable to constrict flow of an exhaust gas in a corresponding plurality of constricted paths disposed between a leading edge of one vane and trailing edge of an adjacent vane, and wherein the flow disrupting feature is a corresponding plurality of flow disrupting features on each vane on a side opposite to respective plurality of constricted paths. ### Claim 12 A nozzle vane for a variable geometry turbine for a turbocharger comprising: a leading edge; a trailing edge; an outside surface for directing a flow of exhaust gases toward a turbine of the turbocharger from the leading edge toward the trailing edge; and one or more flow disrupting features on the outside surface to disrupt the flow adjacent to the trailing edge. ### Claim 13 (depends on 12) The nozzle vane of claim 12, wherein the one or more flow disrupting features are one or more grooves formed near the trailing edge. ### Claim 14 (depends on 12) The nozzle vane of claim 12, wherein the one or more flow disrupting features are one or more dimples formed near the trailing edge. ### Claim 15 (depends on 12) The nozzle vane of claim 12, wherein the one or more flow disrupting features occupy between 10% and 30% of one side of the outside surface. ### Claim 16 (depends on 12) The nozzle vane of claim 12, wherein the nozzle vane and a plurality of similarly configured other nozzle vanes are arranged in a ring, and configured to pivot from a relatively non-constricting configuration to a flow constricting configuration wherein adjacent nozzle vanes in the ring of nozzle vanes constrict the flow between a bottom surface of a leading edge of one nozzle vane and a top surface of a trailing edge of an adjacent nozzle vane, and wherein the one or more flow disrupting features are on a bottom surface near the trailing edge of each nozzle vane. ### Claim 17 (depends on 16) The nozzle vane of claim 16, wherein the parallel grooves form an angle with a terminal edge of the trailing edge. ### Claim 18 (depends on 16) The nozzle vane of claim 16, wherein the parallel grooves are substantially parallel with a terminal edge of the trailing edge. ### Claim 19 A method, comprising: during engine braking, expanding exhaust gas through a variable geometry nozzle of a turbocharger; and disrupting flow via flow disrupting grooves on a surface of nozzle vanes upstream from exhaust vanes of the turbocharger. ### Claim 20 (depends on 19) The method of claim 19, wherein the disrupting flow includes disrupting the flow at and/or adjacent to a trailing edge of the surface of the nozzle vanes. ### Claim 21 (depends on 19) The method of claim 19, wherein the disrupting flow includes disrupting the flow with a series of grooves on a respective outside surface of each of the nozzle vanes. ### Claim 22 (depends on 19) The method of claim 19, wherein the disrupting flow includes disrupting the flow with dimples on respective outside surfaces of each of the nozzle vanes. ### Claim 23 (depends on 19) The method of claim 19, wherein the nozzle vanes have an airfoil profile with a central axis substantially normal to a cross section of the airfoil, and wherein the disrupting the flow includes disrupting the flow with a series of parallel grooves on the surface of the nozzle vanes disposed at an angle with the central axis of the airfoil.