| 摘要 |
A gas turbine engine component includes a wall having first and second wall surfaces and a cooling hole extending through the wall. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet, a first diffusing section extending downstream from the metering section, and a second diffusing section extending downstream from the first diffusing section to the outlet. The second diffusing section includes first and second lobes, each lobe diverging longitudinally and laterally relative to the metering section, and a trailing edge.
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