| 摘要 |
A rotating blade for a gas turbine engine is provided which is configured to uniformly diffuse cooling air from an internal cavity about the tip of the rotating blade. The rotating blade includes a secondary cavity interposed between an internal cavity and the peripheral edge of the blade tip, wherein the secondary cavity steps down the cooling air pressure, decreasing the momentum of the cooling air exiting the rotating blade tip. The cooling air is diffused about the tip of the rotating blade into cooling slots aligned along the peripheral edge, such that a sub-boundary layer of cooling air is built-up adjacent to surface of the airfoil.
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