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Abstract
Computational results are presented for a row of coolant injection holes on each side of a symmetrical turbine blade model near the leading edge. Four film cooling configurations, (Citation1) a cylindrical film hole, (Citation2) a forward diffused film hole, (Citation3) a cylindrical film hole within a transverse slot, and (Citation4) a forward-diffused film hole within a transverse slot, are used. Also, the effect of slot width is investigated. All simulations are at a fixed density ratio of 1.0, a blowing ratio of 0.5, and a pitch-to-diameter ratio of 5.0. Computational solutions of the steady, Reynolds-averaged Navier-Stokes equations are obtained using a finite-volume method. It is found that the shape of the hole and the integration of the holes with a continuous slot can significantly affect the film cooling flow over the protected surface. Also, it is found that when the slot width is almost equal to the elliptic footprint major axis, where the film hole exit is located, the shaped hole within the slot has the highest cooling effectiveness, but in other slot widths the advantage of this kind of hole configuration disappears.