# US 10,767,489 B2 · Component for a turbine engine with a hole > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,767,489 B2 - Document ID: US10767489B2 - Status: Granted - Kind: B2 - Application number: 15/238,058 - Filed: 2016-08-16 - Published: 2018-02-22 - Granted: 2020-09-08 - Earliest claimed: 2016-08-16 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Ronald Scott Bunker - Web page: https://patentgrep.com/patent/US10767489B2 ## CPC - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 11/08: for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) - F01D 25/12: Cooling - F01D 25/14: Casings modified therefor (double casings F01D25/26) - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F23R 3/06: Arrangement of apertures along the flame tube - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/128: Nozzles - F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor - F05D 2240/35: Combustors or associated equipment - F05D 2250/13: trapezoidal - F05D 2250/141: circular - F05D 2260/202: by film cooling - F05D 2300/514: Porosity - F23R 2900/03042: Film cooled combustion chamber walls or domes - 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) - 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) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - 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 engine component, such as an airfoil, for a turbine engine having a hole, which can be a film hole, within the outer wall of the engine component where cooling air moves from an interior cavity through the hole to an outer surface of the engine component providing a cooling film on the outer surface of the engine component. ## Claims ### Claim 1 A component for a turbine engine 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; at least one film hole extending through the wall defining a passage extending between an inlet located in the first surface and an outlet located in the second surface, where the passage defines an inner surface having an upstream side and a downstream side with respect to the hot airflow, with one of the inlet and outlet having a non-occluded portion located on the downstream side; and a porous material located within the hole extending along at least a portion of the upstream side of the passage with respect to the hot airflow and at least partially defining a border of the non-occluded portion; wherein a remaining portion of the border is defined by the downstream side of the passage that is free of porous material. ### Claim 2 (depends on 1) The component of claim 1 wherein both the inlet and the outlet have a non-occluded portion and the porous material at least partially defines a border for both of the non-occluded portions. ### Claim 3 (depends on 2) The component of claim 2 wherein the porous material extends through the hole from the inlet to the outlet. ### Claim 4 (depends on 3) The component of claim 3 wherein the porous material comprises at least one of a trapezoid, or a sectioned cone. ### Claim 5 (depends on 3) The component of claim 3 wherein the porous material abuts an inner surface defining the hole. ### Claim 6 (depends on 1) The component of claim 1 wherein the porous material is spaced from an inner surface defining the hole. ### Claim 7 (depends on 1) The component of claim 1 wherein the porous material extends through the hole from the inlet to the outlet. ### Claim 8 (depends on 1) The component of claim 1 wherein the porous material comprises at least one of a trapezoid, or a sectioned cone. ### Claim 9 (depends on 1) The component of claim 1 wherein the porous material abuts an inner surface defining the hole. ### Claim 10 (depends on 1) The component of claim 1 wherein the porous material is spaced from an inner surface defining the hole. ### Claim 11 (depends on 1) The component of claim 1 further comprising at least one rib extending from an inner surface to the porous material. ### Claim 12 (depends on 1) The component of claim 1 wherein the hole comprises a passage connecting the inlet and the outlet, with the passage having a non-occluded passage portion extending from the inlet to the outlet, and the porous material forms a border of the non-occluded passage portion. ### Claim 13 (depends on 12) The component of claim 12 wherein the passage comprises a passage centerline and the porous material comprises a body axis. ### Claim 14 (depends on 13) The component of claim 13 wherein the passage centerline and the body axis are non-parallel. ### Claim 15 (depends on 14) The component of claim 14 wherein the body axis is curvilinear and the passage centerline is linear. ### Claim 16 (depends on 13) The component of claim 13 wherein a passage cross section perpendicular to the passage centerline is different in shape than a porous material cross section perpendicular to the body axis at the same location in the hole. ### Claim 17 (depends on 13) The component of claim 13 wherein a passage cross section parallel to the passage centerline is different in shape than a porous material cross section parallel to the body axis when the cross sections are in parallel planes. ### Claim 18 (depends on 1) The component of claim 1 wherein the porous material is located in the inlet at an upstream side of the cooling airflow. ### Claim 19 (depends on 18) The component of claim 18 wherein the porous material is located in the outlet at an upstream side of the hot airflow. ### Claim 20 (depends on 1) The component of claim 1 wherein the porous material comprises an insert located within the hole. ### Claim 21 (depends on 20) The component of claim 20 wherein the insert is secured to an inner surface forming the hole. ### Claim 22 (depends on 1) The component of claim 1 wherein the porous material is integrally formed with the wall. ### Claim 23 (depends on 22) The component of claim 22 wherein the wall and porous material are made by additive manufacturing. ### Claim 24 (depends on 1) The component of claim 1 wherein the porous material is randomly porous. ### Claim 25 (depends on 1) The component of claim 1 wherein the porous material is structured porous. ### Claim 26 (depends on 1) The component of claim 1 wherein the non-occluded portion has a volume of at least ⅓rd a volume of the porous material. ### Claim 27 (depends on 1) The component of claim 1 further comprising a hood extending into the passage proximate the outlet. ### Claim 28 (depends on 27) The component of claim 27 wherein the hood is formed along the upstream side of the passage. ### Claim 29 (depends on 27) The component of claim 27 wherein the hood is formed of a porous material. ### Claim 30 (depends on 29) The component of claim 29 wherein the hood is formed of at least two porous materials with different porosities. ### Claim 31 (depends on 27) The component of claim 27 wherein the hood is formed of a non-porous material. ### Claim 32 (depends on 27) The component of claim 27 wherein the hood comprises a curved edge. ### Claim 33 A method of controlling a momentum profile of a cooling air flow emitted from a hole defining a passage extending between an inlet on a cooled surface of an engine component and an outlet on a heated surface facing a hot airflow of the engine component where the passage defines an inner surface having an upstream side and a downstream side with respect to the hot airflow, the method comprising: introducing a cooling air flow into the inlet of the hole, emitting the introduced cooling air flow from a non-occluded portion of the hole along the downstream side of the passage free of porous material, and emitting the introduced cooling air flow from a partially-occluded portion of the hole defined by a porous material located in a sub-portion of the outlet along the upstream side of the outlet to modify the momentum profile of the emitted cooling air flow passing through the porous material where the emitted cooling air flow from the porous material has an emerging velocity less than the cooling air flow emitted from the non-occluded portion. ### Claim 34 (depends on 33) The method of claim 33 wherein controlling the momentum profile comprises emitting the cooling air through a porous material having a structured porosity. ### Claim 35 (depends on 33) The method of claim 33 wherein controlling the momentum profile comprises passing the cooling air through the partially-occluded portion and a non-occluded portion. ### Claim 36 (depends on 35) The method of claim 35 wherein the passing the cooling air comprises passing cooling air through the partially-occluded portion circumscribing the non-occluded portion. ### Claim 37 (depends on 35) The method of claim 35 wherein the passing the cooling air comprises passing cooling air through the non-occluded portion circumscribing the partially-occluded portion. ### Claim 38 (depends on 33) The method of claim 33 wherein controlling the momentum profile comprises emitting the cooling air through a non-occluded portion located on a downstream side of the outlet. ### Claim 39 (depends on 33) The method of claim 33 wherein controlling the momentum profile comprises emitting the cooling air through the hole having a diverging cross-sectional area. ### Claim 40 (depends on 33) The method of claim 33 further comprising controlling the momentum profile of fluid emitted from the outlet by at least one of the porosity and location of the partially-occluded portion. ### Claim 41 A component for a turbine engine 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; at least one film hole extending through the wall and having an inlet located in the first surface and an outlet located in the second surface, a passage connecting the inlet and the outlet, with the passage having a non-occluded passage portion extending from the inlet to the outlet; and with one of the inlet and outlet having a non-occluded portion; and a porous material located within the hole forming a border of the non-occluded passage portion and at least partially defining a border of the non-occluded portion; wherein the passage comprises a passage centerline, the porous material comprises a body axis, and a passage cross section is different in shape than a porous material cross section when either one of: the passage cross section is perpendicular to the passage centerline at the same location in the hole as the porous material cross section; or the passage cross section is parallel to the passage centerline, the porous material cross section is parallel to the body axis, and the cross sections are in parallel planes.