Upstream Endwall Film-Cooing in a Vane Cascade with Cylindrical Shape Holes

What is it about?

Vane and blade passage walls of the gas turbine engines require cooling by the film-cooling flow to have their thermal-stresses reduced. We have tested two cylindrical hole shapes to supply the film-cooling flow in a simulated vane passage in a wind tunnel. The results show the diffused cylindrical hole performs better than the straight cylindrical hole.

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