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Film cooling technology is a commonly used method for thermal protection of gas turbines' hot sections. A new, shaped, film cooling hole is proposed in this study. The geometry is made of a straight-through cylindrical feed hole at an inclination angle of 30° followed by an expansion section. The expansion section is created by the rotation of the same circular hole on the inclination plane about an axis normal to that plane which passes through the center of the feed hole exit area. This shapedoi:10.1155/2022/9913692 doaj:66c910a560ae4205b2408c4e6bbbc256 fatcat:x2p3demuengabludfpgjbmsyfu