Film cooling passage with multidimensional diffusion
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United States of America Patent
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Feb 23, 2017
app pub date -
Aug 17, 2015
filing date -
Aug 17, 2015
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Abstract
A film-cooled component for a gas turbine engine includes a first surface of the component located at a gas path of a gas turbine engine, a second surface of the component defining a component passage, and a cooling airflow passage extending from the second surface to the first surface to convey a cooling airflow from the passage and emit the cooling airflow at the first surface. The cooling airflow passage is curvilinearly diffused in at least two directions relative to a local gas flow direction in the gas path. A method of cooling a component includes flowing a cooling airflow into an internal component passage of the turbine component, conveying the cooling airflow through a cooling airflow passage, diffusing the cooling airflow in at least two directions along the airflow passage, and emitting the cooling airflow at a gas path surface to cool the gas path surface of the component.
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