# US 10,502,068 B2 · Engine with chevron pin bank > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,502,068 B2 - Document ID: US10502068B2 - Status: Granted - Kind: B2 - Application number: 15/367,978 - Filed: 2016-12-02 - Published: 2018-06-07 - Granted: 2019-12-10 - Earliest claimed: 2016-12-02 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Emily Clark Clark; Julienne LaChance - Web page: https://patentgrep.com/patent/US10502068B2 ## CPC - F01D 5/187: {Convection cooling} - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F05D 2250/75: given by its similarity to a letter, e.g. T-shaped - F05D 2260/22141: using fins or ribs - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An apparatus for a turbine engine, such as a gas turbine engine, can include an engine component such as an airfoil. The airfoil includes an outer wall with a pressure side and a suction side confronting a hot gas flow exterior of the airfoil. A cooling circuit can provide a flow of cooling fluid through the interior of the airfoil to cool the airfoil operating within the hot gas flow. The cooling circuit can include a pin bank to induce turbulence on the cooling fluid to improve cooling of the airfoil. ## Claims ### Claim 1 An airfoil for a turbine engine, the airfoil comprising: an outer wall defining a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction; a cooling circuit located within the airfoil and with a cooling passage including opposing sidewalls, and at least partially defining the cooling circuit; and a pin bank provided in the cooling passage comprising multiple chevron pins with at least one chevron pin of the multiple chevron pins including a pair of linear legs joined at a junction, where the multiple chevron pins are arranged in rows where the chevron pins in each row are separated by an intervening gap, where the rows are offset such that one intervening gap of one row is aligned in the span-wise direction with a chevron pin of an adjacent row; and at least one cooling fluid flow path extending in the span-wise direction through the one intervening gap of the one row and intersecting the chevron pin of the adjacent row. ### Claim 2 (depends on 1) The airfoil of claim 1 wherein the pair of linear legs terminates at opposing feet. ### Claim 3 (depends on 2) The airfoil of claim 2 wherein the feet mount to the sidewalls of the cooling passage. ### Claim 4 (depends on 2) The airfoil of claim 2 wherein the feet are provided in the cooling passage, extending between the opposing sidewalls. ### Claim 5 (depends on 2) The airfoil of claim 2 wherein the pair of legs defines an included angle and the included angle is between 30 degrees and 60 degrees. ### Claim 6 (depends on 5) The airfoil of claim 5 wherein the included angle is 45 degrees. ### Claim 7 (depends on 1) The airfoil of claim 1 wherein the cooling passage defines a passage axis along a longitudinal length of the cooling passage and the at least one chevron pin is oriented at a pitch angle relative to the passage axis. ### Claim 8 (depends on 1) The airfoil of claim 1 wherein the cooling passage includes a local centerline, and the at least one chevron pin is angled at a pitch angle relative to the local centerline of the cooling passage. ### Claim 9 (depends on 8) The airfoil of claim 8 wherein the at least one chevron pin includes a pair of legs and each leg is angled at a different confronting angle relative to the local centerline of the cooling passage. ### Claim 10 (depends on 1) The airfoil of claim 1 wherein the at least one chevron pin includes a cross-sectional profile that is a rounded rectangular shape. ### Claim 11 (depends on 1) The airfoil of claim 1 wherein the at least one chevron pin is formed by additive manufacturing. ### Claim 12 (depends on 1) The airfoil of claim 1 wherein each of the multiple chevron pins forming the pin bank comprises a corresponding pair of linear legs joined at a junction. ### Claim 13 (depends on 1) The airfoil of claim 1 wherein the at least one chevron pin provides for an increased heat transfer coefficient along the cooling passage at the pin bank. ### Claim 14 A component for a turbine engine, the component comprising: a wall separating a cooling airflow from a hot airflow having a first surface facing the cooling airflow and a second surface facing the hot airflow; a cooling circuit at least partially defined by the wall and including a cooling passage having opposing sidewalls and defining a passage axis along a longitudinal length of the cooling passage; and a pin bank provided in the cooling passage comprising multiple chevron pins with at least one chevron pin of the multiple chevron pins including a pair of linear legs joined at a junction, where the multiple chevron pins are arranged in rows where the chevron pins in each row are separated by an intervening gap, where the rows are offset such that one intervening gap of one row is aligned along the passage axis with a chevron pin of an adjacent row; and at least one cooling fluid flow path extending along the passage axis through the one intervening gap of the one row and intersecting the chevron pin of the adjacent row. ### Claim 15 (depends on 14) The component of claim 14 wherein the pair of linear legs terminates at opposing feet. ### Claim 16 (depends on 15) The component of claim 15 wherein the feet mount to the sidewalls of the cooling passage. ### Claim 17 (depends on 15) The component of claim 15 wherein the feet are provided in the cooling passage, extending between the opposing sidewalls. ### Claim 18 (depends on 14) The component of claim 14 wherein the at least one chevron pin is oriented at a pitch angle relative to the passage axis. ### Claim 19 (depends on 14) The component of claim 14 wherein the cooling passage includes a local centerline, and the at least one chevron pin is angled at a pitch angle relative to the local centerline of the cooling passage. ### Claim 20 (depends on 19) The component of claim 19 wherein the at least one chevron pin includes a pair of legs and each leg is angled at a different confronting angle relative to the local centerline of the cooling passage. ### Claim 21 An airfoil for a turbine engine, the airfoil comprising: an outer wall defining a pressure side and a suction side extending axially between a leading edge and a trailing edge defining a chord-wise direction and extending radially between a root and a tip defining a span-wise direction; a cooling circuit located within the airfoil and with a cooling passage including opposing sidewalls, and at least partially defining the cooling circuit; and a pin bank provided in the cooling passage comprising a set of chevron pins arranged in rows, with the chevrons in each row separated by an intervening gap, and the rows being offset, such that the chevron pins of one row are aligned with the gap of an adjacent row, and the chevron pins of the one row have an effective width confronting the gap that is wider than the gap of the adjacent row; and at least one cooling fluid flow path through the rows is at least partially defined by the gaps in sequential rows.