# US 2013/0156602 A1 · Film cooled turbine component > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2013/0156602 A1 - Document ID: US20130156602A1 - Status: Published application - Kind: A1 - Application number: 13/328,733 - Filed: 2011-12-16 - Published: 2013-06-20 - Earliest claimed: 2011-12-16 - Assignees: United Technologies Corporation - Inventors: Stephanie Santoro; Matthew A. Devore; Steven B. Gautschi - Web page: https://patentgrep.com/patent/US20130156602A1 ## CPC - F01D 5/186: {Film cooling (F01D5/187 takes precedence)} - F05D 2250/231: cylindrical - F05D 2250/38: angled, e.g. sweep angle - 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 Film cooling of turbine component surfaces, such as high-lift airfoil surfaces, is achieved by a flow of cooling air through film cooling holes of generally constant cross-sectional area, which extend from the surfaces to a radial cooling passage within the airfoil. The film cooling holes are angularly offset from that portion of the radial cooling passage immediately upstream of the film cooling holes by an acute angle which effects a radial reversal of the flow of cooling air into the film cooling holes from the radial cooling passage to reduce the momentum of airflow through the film cooling holes to reduce separation of cooling air film from the surface. ## Claims ### Claim 1 An air-cooled turbine component comprising: an outer surface adapted to be cooled by a film of cooling air flowing thereover; a radial cooling air passage extending through the interior of said component; and a plurality of film cooling holes extending between said outer surface and said radial cooling passage; each of said film cooling holes having a substantially constant cross-sectional area along the length thereof; each of said film cooling holes intersecting said radial cooling passage such that said film cooling hole and that portion of said radial cooling passage immediately upstream from said intersection thereof with said film cooling hole defining an acute angle, whereby cooling air entering said film cooling hole from said radial cooling passage is angularly displaced greater than 90° from the flow of cooling air through said radial cooling passage for decreasing the momentum of airflow through said film cooling hole and any tendency of cooling air discharged from said film cooling hole at said outer airfoil surface to separate therefrom. ### Claim 2 (depends on 1) The air-cooled turbine airfoil of claim 1 wherein said acute angle is approximately 25°. ### Claim 3 (depends on 1) The air-cooled turbine airfoil of claim 1, wherein said turbine component comprises a rotor blade. ### Claim 4 (depends on 3) The air-cooled turbine airfoil of claim 3, wherein said surface comprises a concave airfoil pressure surface. ### Claim 5 (depends on 3) The air-cooled turbine airfoil of claim 3, wherein said airfoil surface comprises a convex suction surface. ### Claim 6 (depends on 3) The air-cooled turbine airfoil of claim 3, wherein said surface is an airfoil surface of a shape wherein under normal operation conditions, working fluid flow over said airfoil surface has a ratio of static pressure to total pressure greater than approximately 0.9 over a substantial portion of the entire airfoil surface. ### Claim 7 (depends on 1) The air-cooled turbine component of claim 1, wherein said turbine airfoil comprises a stator vane. ### Claim 8 (depends on 7) The air-cooled turbine airfoil of claim 7, wherein said surface is an airfoil surface of a shape wherein under normal operating conditions, working fluid flow over said airfoil surface has a ratio of static pressure to total pressure greater than approximately 0.9 over a substantial portion of the entire airfoil surface. ### Claim 9 An air-cooled turbine component having an outer airfoil surface of an airfoil shape wherein under normal operating conditions, working fluid flow over said airfoil surface has a ratio of static pressure to total pressure greater than approximately 0.9 over a substantial portion of the entire airfoil surface, said air-cooled turbine component comprising: a radial cooling passage defined by a continuous sidewall extending through the interior of said airfoil; and at least one film cooling hole defined by a continuous sidewall and extending between said outer airfoil surface and said radial cooling passage; said film cooling hole having a substantially constant cross-sectional area along the length thereof; said turbine component further comprising a flow diverter at the intersection of said film cooling hole and said radial cooling passage for the substantial reversal of the radial component of cooling air flow into said film cooling hole from cooling airflow through said radial cooling passage. ### Claim 10 (depends on 9) The air-cooled turbine component of claim 9, wherein said flow diverter comprises an intersection of the sidewalls of said film cooling hole and said radial cooling passage. ### Claim 11 (depends on 10) The air-cooled turbine component of claim 10, wherein said flow diverter angularly displaces the flow of cooling air entering said film cooling hole from said radial cooling passage substantially between 90° and 180°. ### Claim 12 (depends on 11) The air-cooled turbine component of claim 11, wherein said turbine component comprises a rotor blade. ### Claim 13 (depends on 12) The air-cooled turbine component of claim 12, wherein said airfoil surface comprises a concave pressure surface. ### Claim 14 (depends on 12) The air-cooled turbine component of claim 12, wherein said airfoil surface comprises a convex suction surface. ### Claim 15 (depends on 11) The air-cooled turbine component of claim 11, wherein said turbine component comprises a stator vane.