# US 12,595,741 B2 · Dirt and dust free turbine vane cooling > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,595,741 B2 - Document ID: US12595741B2 - Status: Granted - Kind: B2 - Application number: 18/463,475 - Filed: 2023-09-08 - Published: 2025-03-13 - Granted: 2026-04-07 - Earliest claimed: 2023-09-08 - Assignees: Rtx Corporation - Applicants: RTX Corporation - Inventors: Mark F. Zelesky - Web page: https://patentgrep.com/patent/US12595741B2 ## CPC - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F01D 5/188: {with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall} - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/121: related to the leading edge of a stator vane - F05D 2240/81: Cooled platforms - F05D 2260/201: by impingement of a fluid - F05D 2260/202: by film cooling - F05D 2260/22141: using fins or ribs - 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 Vane assemblies and gas turbine engines having vane assemblies are described. The vane assemblies include a vane having outer and inner diameter ends and at least a leading-edge cavity therein. A direction of flow through the leading-edge cavity is from the outer diameter end toward the inner diameter end. An inner diameter platform is arranged at the inner diameter end of the vane and includes an inner diameter flow path having an exit at an aft side of the inner diameter platform. The inner diameter platform includes an inner diameter flow aperture fluidly coupling the leading-edge cavity and the inner diameter flow path. A baffle is installed within the leading-edge cavity and arranged to reduce a cross-sectional area in the direction of flow of the leading-edge cavity such that the leading-edge cavity has a larger cross-sectional area proximate the outer diameter end than at the inner diameter end. ## Claims ### Claim 1 A vane assembly comprising: a vane having an outer diameter end and an inner diameter end, the vane defining at least a leading-edge cavity therein, wherein a direction of flow through the leading-edge cavity is from the outer diameter end toward the inner diameter end; an inner diameter platform arranged at the inner diameter end of the vane, the inner diameter platform having an inner diameter flow path comprising an exit at an aft side of the inner diameter platform, the inner diameter platform having an inner diameter flow aperture fluidly coupling the leading-edge cavity and the inner diameter flow path, wherein the inner diameter flow path is defined within the inner diameter platform and extends between the inner diameter flow aperture and the exit; and a baffle installed within the leading-edge cavity, the baffle arranged to reduce a cross-sectional area in the direction of flow through the leading-edge cavity such that a leading-edge portion of the leading-edge cavity between an exterior surface of the baffle and an interior surface of the vane has a larger cross-sectional area proximate the outer diameter end than at the inner diameter end, wherein an impingement flow is directed into the baffle and a throughflow is directed into the leading-edge portion of the leading-edge cavity between the exterior surface of the baffle and the interior surface of the vane, and wherein the inner diameter flow aperture is positioned at least on the inner diameter platform between the exterior surface of the baffle and the interior surface of the vane and configured to provide a flow path for the throughflow from the leading-edge portion of the leading-edge cavity into the inner diameter flow path, wherein the through flow flows from the outer diameter end, through the leading-edge portion of the leading-edge cavity, and into the inner diameter flow aperture. ### Claim 2 (depends on 1) The vane assembly of claim 1, further comprising a purge cavity defined within the inner diameter platform between the inner diameter flow aperture and the inner diameter flow path. ### Claim 3 (depends on 2) The vane assembly of claim 2, further comprising a second vane having a second leading-edge cavity fluidly coupled to the purge cavity by a second inner diameter flow aperture that fluidly couples the purge cavity to the second leading-edge cavity. ### Claim 4 (depends on 2) The vane assembly of claim 2, wherein the purge cavity is fluidly coupled to a plurality of leading-edge cavities of a plurality of respective vanes. ### Claim 5 (depends on 1) The vane assembly of claim 1, wherein the inner diameter flow path is curved such that airflow passing through the inner diameter flow path is turned as it flows from the inner diameter flow aperture to the exit of the inner diameter flow path. ### Claim 6 (depends on 1) The vane assembly of claim 1, wherein the vane comprises a plurality of film cooling holes formed in a wall of the vane defining the leading-edge cavity. ### Claim 7 (depends on 6) The vane assembly of claim 6, wherein the film cooling holes are angled at an angle of 90° or greater in a direction away from the direction of flow, such that flow entering the film cooling holes must turn at the angle of 90° or greater from the direction of flow. ### Claim 8 (depends on 7) The vane assembly of claim 7, wherein the angle is 145° or greater. ### Claim 9 (depends on 1) The vane assembly of claim 1, wherein the baffle comprises a plurality of impingement holes arranged to direct an impingement flow at an internal surface of a wall of the vane that defines the leading-edge cavity. ### Claim 10 (depends on 1) The vane assembly of claim 1, wherein the vane comprises a plurality of thermal transfer augmentation features arranged on an internal surface of the vane defining the leading-edge cavity. ### Claim 11 A gas turbine engine comprising: a turbine section comprising at least one vane assembly and at least one rotor arranged downstream from the at least one vane assembly, wherein a rotor cavity is defined between the at least one vane assembly and the at least one rotor, wherein the at least one vane assembly comprises: a vane having an outer diameter end and an inner diameter end, the vane defining at least a leading-edge cavity therein, wherein a direction of flow through the leading-edge cavity is from the outer diameter end toward the inner diameter end; an inner diameter platform arranged at the inner diameter end of the vane, the inner diameter platform having an inner diameter flow path comprising an exit at an aft side of the inner diameter platform that fluidly couples to the rotor cavity, the inner diameter platform having an inner diameter flow aperture fluidly coupling the leading-edge cavity and the inner diameter flow path, wherein the inner diameter flow path is defined within the inner diameter platform and extends between the inner diameter flow aperture and the exit; and a baffle installed within the leading-edge cavity, the baffle arranged to reduce a cross-sectional area in the direction of flow through the leading-edge cavity such that a leading-edge portion of the leading-edge cavity between an exterior surface of the baffle and an interior surface of the vane has a larger cross-sectional area proximate the outer diameter end than at the inner diameter end, wherein an impingement flow is directed into the baffle and a throughflow is directed into the leading-edge portion of the leading-edge cavity between the exterior surface of the baffle and the interior surface of the vane, and wherein the inner diameter flow aperture is positioned at least on the inner diameter platform between the exterior surface of the baffle and the interior surface of the vane and configured to provide a flow path for the throughflow from the leading-edge portion of the leading-edge cavity into the inner diameter flow path, wherein the through flow flows from the outer diameter end, through the leading-edge portion of the leading-edge cavity, and into the inner diameter flow aperture. ### Claim 12 (depends on 11) The gas turbine engine of claim 11, further comprising a purge cavity defined within the inner diameter platform between the inner diameter flow aperture and the inner diameter flow path. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, further comprising a second vane having a second leading-edge cavity fluidly coupled to the purge cavity by a second inner diameter flow aperture that fluidly couples the purge cavity to the second leading-edge cavity. ### Claim 14 (depends on 12) The gas turbine engine of claim 12, wherein the purge cavity is fluidly coupled to a plurality of leading-edge cavities of a plurality of respective vanes. ### Claim 15 (depends on 11) The gas turbine engine of claim 11, wherein the inner diameter flow path is curved such that airflow passing through the inner diameter flow path is turned as it flows from the inner diameter flow aperture to the exit of the inner diameter flow path. ### Claim 16 (depends on 11) The gas turbine engine of claim 11, wherein the vane comprises a plurality of film cooling holes formed in a wall of the vane defining the leading-edge cavity. ### Claim 17 (depends on 16) The gas turbine engine of claim 16, wherein the film cooling holes are angled at an angle of 90° or greater in a direction away from the direction of flow, such that flow entering the film cooling holes must turn at the angle of 90° or greater from the direction of flow. ### Claim 18 (depends on 17) The gas turbine engine of claim 17, wherein the angle is 145° or greater. ### Claim 19 (depends on 11) The gas turbine engine of claim 11, wherein the baffle comprises a plurality of impingement holes arranged to direct an impingement flow at an internal surface of a wall of the vane that defines the leading-edge cavity. ### Claim 20 (depends on 11) The gas turbine engine of claim 11, wherein the vane comprises a plurality of thermal transfer augmentation features arranged on an internal surface of the vane defining the leading-edge cavity.