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US 2013/0156602 A1Published application
Film cooled turbine component
AssigneeUnited Technologies Corporation
InventorsStephanie Santoro, Matthew A. Devore, Steven B. Gautschi
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AssigneeUnited Technologies Corporation
InventorsStephanie Santoro, Matthew A. Devore, Steven B. Gautschi
Estimating the term…
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.
An air-cooled turbine component comprising:
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:
Dependencies are inferred from the claim text.