# US 9,435,220 B2 · Turbocharger control linkage with reduced heat flow > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,435,220 B2 - Document ID: US9435220B2 - Status: Granted - Kind: B2 - Application number: 13/520,252 - Filed: 2011-01-05 - Published: 2013-01-10 - Granted: 2016-09-06 - Earliest claimed: 2010-01-16 - Assignees: BorgWarner Inc. - Applicants: Vahidin Alajbegovic - Inventors: Vahidin Alajbegovic - Web page: https://patentgrep.com/patent/US9435220B2 ## CPC - F02B 37/186: {Arrangements of actuators or linkage for bypass valves} - F01D 17/20: Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted (sensing elements alone F01D17/02; final actuators alone F01D17/10) - 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 - F16C 7/00: Connecting-rods or like links pivoted at both ends (coupling-rods for locomotive driving-wheels B61C17/10); Construction of connecting-rod heads (heads rigid with crossheads F16C5/00) - F02B 37/18: by bypassing exhaust {from the inlet to the outlet of turbine or to the atmosphere} - F02B 37/183: {Arrangements of bypass valves or actuators therefor} - F05D 2260/22141: using fins or ribs - F05D 2300/5024: Heat conductivity - F16C 2202/24: Insulating - Y02T 10/12: Improving ICE efficiencies - Y10T 29/49238: Repairing, converting, servicing or salvaging - 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) - 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) - F16C: SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS - 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 - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract The life of an actuator such as a turbocharger VTG actuator is extended by reducing heat conduction from the turbine housing along the control linkage to the actuator link and into the actuator, thereby protecting sensitive electronic components. To this end, the control linkage may be equipped with cooling fins, or be made hollow rather than solid, or be made of a thermal energy retarding material in order to retard heat from the turbine housing assembly reaching the actuator. ## Claims ### Claim 1 A turbocharger including an electric actuator unit connected internally within a turbocharger housing (1) connected to a variable turbine geometry mechanism via an axially extending control linkage, wherein the axially extending control linkage includes a shaft and a rod end, and wherein at least one of the shaft and the rod ends is provided with a plurality of cooling fins along at least one axial segment thereof cooling fins. ### Claim 2 (depends on 1) The turbocharger as in claim 1, wherein said cooling fins are axially spaced radially outwardly projecting cooling fins extending generally perpendicular to the axis of the linkage. ### Claim 3 (depends on 2) The turbocharger as in claim 2, wherein said cooling fins are generally annular cooling fins. ### Claim 4 (depends on 1) The turbocharger as in claim 1, wherein said cooling fins are longitudinally extending fins extending parallel to the longitudinal axis of the control linkage. ### Claim 5 (depends on 1) The turbocharger as in claim 1, wherein said control linkage comprises a center section having first and second ends and one rod end respectively connected to each center section end via a threaded connection, wherein said cooling fins are provided on both rod ends. ### Claim 6 (depends on 1) The turbocharger as in claim 1, wherein said control linkage comprises a center section having first and second ends and one rod-end respectively connected to each center section end via a threaded connection, wherein said cooling fins are provided on said center section. ### Claim 7 A turbocharger including an electric actuator unit connected internally within a turbocharger housing (1) connected to a variable turbine geometry mechanism via an axially extending control linkage, wherein the axially extending control linkage includes a shaft and a rod end, and wherein at least one of the shaft and the rod ends is provided with at least one hollow segment having a plurality of cooling fins. ### Claim 8 (depends on 7) The turbocharger of claim 7, wherein said control linkage is formed of a material having a thermal conductivity of not more than 7.2 (W/(m*K)). ### Claim 9 A turbocharger including: a turbocharger housing (1); an electric actuator unit (10) attached to the turbocharger housing (1), the electric actuator unit (10) including an actuator drive arm (12); at least one of a variable turbine-geometry mechanism; a control linkage including a drive-end rod end (15) and a driven-end rod end (7) connected directly to each other or connected via an intermediate center section, each rod end (15, 7) including a cylindrical section (20) and a head section (3) divided by a transition plane (19), with a ball (8) constrained but free to rotate in the head (3), wherein each ball includes a bore (9); a drive pin (14) extending from the actuator shaft (11) into the bore (9) in the ball (8) in the drive-end rod end (15); a driven pin (6) extending from the bore (9) in the ball (8) in the driven-end rod end (7) and connected for driving the variable turbine geometry mechanism; wherein a surface area of the control linkage between the transition planes (19) is at least 1.4 times that of a baseline surface area; wherein the baseline surface area is calculated using a model control linkage; wherein the model control linkage comprises a drive-end rod end (15) and a driven-end rod end (7), the rod ends connected via a shaft (16), each rod end (15, 7) including a cylindrical section (20) and the head section (3) divided by a transition plane (19), with a ball (8) constrained but free to rotate in the head section (3), wherein each ball includes a bore (9); wherein the model control linkage has the same centerline length as the control linkage, wherein the centerline length is the distance from the center of the ball (8) of the drive-end rod end (15) to the center of the ball (8) of the driven-end rod end (7); wherein a diameter of the shaft of the model control linkage is the same as a diameter of the bore (9) of the control linkage; wherein the lengths and diameter of the cylindrical sections (20) of the rod ends of the model control linkage are determined as follows: Calc. length Length from from Ball end to Transition Head Barrel bore centerline plane to end Diameter diameter Descriptor B A C D J Rod end 5 5 27 18 18 9 Rod end 6 6 30 20 20 11 Rod end 8 8 36 25 24 14 Rod end 10 10 43 30 28 17 Rod end 12 12 50 35 32 19 Rod end 14 14 57 40 36 22 Rod end 16 16 64 46 42 29 Rod end 20 20 77 54 50 32 and wherein the surface area of the model control linkage is measured between the transition planes (19). ### Claim 10 (depends on 9) The turbocharger as in claim 9, wherein a flat or hexagonal wrench-receiving feature are is ignored in computing an effective heat radiating surface area of the control linkage and model control linkage. ### Claim 11 (depends on 9) The turbocharger as in claim 9, wherein the surface area of the control linkage between the transition planes (19) is at least 1.40 times that of a baseline surface area. ### Claim 12 (depends on 9) The turbocharger as in claim 9, wherein the surface area of the control linkage between the transition planes (19) is at least 2.0 times that of a baseline surface area. ### Claim 13 (depends on 9) The turbocharger as in claim 9, wherein the surface area of the control linkage between the transition planes (19) is at least 3.0 times that of a baseline surface area.