# US 11,078,796 B2 · Redundant entry cooling air feed hole blockage preventer for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,078,796 B2 - Document ID: US11078796B2 - Status: Granted - Kind: B2 - Application number: 16/220,400 - Filed: 2018-12-14 - Published: 2020-06-18 - Granted: 2021-08-03 - Earliest claimed: 2018-12-14 - Assignees: Raytheon Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Christopher Perron; Justin M. Aniello; Shawn M. McMahon; Ricardo Trindade; Steven Bruce Gautschi; David Barger; Brett Alan Bartling; Nicholas J. Madonna; Robin Prenter; Ryan Lundgreen; Christopher Cosher; Mohamed Hassan - Web page: https://patentgrep.com/patent/US11078796B2 ## CPC - F01D 5/187: {Convection cooling} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)} - F01D 25/12: Cooling - F01D 25/14: Casings modified therefor (double casings F01D25/26) - F01D 25/246: {Fastening of diaphragms or stator-rings} - F05D 2240/11: Shroud seal segments - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/81: Cooled platforms - F05D 2260/201: by impingement of a fluid - F05D 2260/607: Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles - 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 A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages. ## Claims ### Claim 1 A vane ring for a gas turbine engine component, comprising: an inner vane platform around an axis; an outer vane platform around the axis; a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages intersects with the respective one of the multiple of metering passages at an angle, wherein each of the multiple of secondary passages is a branch from one of the multiple of metering passages, and wherein a diameter of each of the multiple of secondary passages is equivalent to a diameter of each of the multiple of metering passages. ### Claim 2 (depends on 1) The vane ring as recited in claim 1, wherein each of the multiple of metering passage passages is circular in cross-section. ### Claim 3 (depends on 2) The vane ring as recited in claim 2, wherein each of the multiple of secondary passages is circular in cross section. ### Claim 4 (depends on 1) The vane ring as recited in claim 1, wherein the multiple of metering passages and the multiple of secondary passages are located within a rail of the outer vane platform. ### Claim 5 (depends on 1) The vane ring as recited in claim 1, wherein the multiple of metering passages and the multiple of secondary passages are located within a hooked rail of the outer vane platform. ### Claim 6 (depends on 1) The vane ring as recited in claim 1, wherein the multiple of metering passages and the multiple of secondary passages each have an entrance in a surface transverse to the axis. ### Claim 7 (depends on 6) The vane ring as recited in claim 6, wherein the cooling airflow scrubs along the surface. ### Claim 8 (depends on 1) The vane ring as recited in claim 1, wherein each of the multiple of secondary passages is a branch from one of the multiple of metering passages, wherein each metering passage and each secondary passage have an entrance in a surface transverse to the axis, each of the multiple of metering passages intersects with one of the multiple of feed passages such that the cooling airflow scrubs along the surface. ### Claim 9 (depends on 1) The vane ring as recited in claim 1, wherein each of the multiple of metering passages and each of the multiple of secondary passages is circular in cross section, the multiple of metering passages and the multiple of secondary passages are located within a hooked rail of the outer vane platform, wherein each metering passage and each secondary passage have an entrance in a surface of the hooked rail transverse to the axis such that the cooling airflow scrubs along the surface. ### Claim 10 A vane ring for a gas turbine engine component, comprising: an inner vane platform around an axis; an outer vane platform around the axis; a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a hooked rail that extends from the outer vane platform; and a multiple of metering passages in the hooked rail, each of the multiple of metering passages intersects with one of the multiple of feed passages; and a multiple of secondary passages recessed in the hooked rail, each of the multiple of secondary passages in communication with one of the multiple of metering passages at an angle, each of the multiple of metering passages and the multiple of secondary passages being circular in cross-section, a diameter of each of the multiple of secondary passages equivalent to a diameter of each of the multiple of metering passages. ### Claim 11 (depends on 10) The vane ring as recited in claim 10, wherein an entrance to each of the multiple of the metering passages and each of the multiple of secondary passages are formed in a surface of the hooked rail transverse to the axis. ### Claim 12 (depends on 11) The vane ring as recited in claim 11, wherein the cooling airflow scrubs along the surface of the hooked rail. ### Claim 13 (depends on 12) The vane ring as recited in claim 12, wherein the airflow is a cooling airflow. ### Claim 14 (depends on 13) The vane ring as recited in claim 13, wherein the vane ring is in a second turbine stage. ### Claim 15 (depends on 10) The vane ring as recited in claim 10, wherein each of the multiple of secondary passages is a branch from one of the multiple of metering passages.