Convex Curvature Effects on Film Cooling Adiabatic Effectiveness

Abstract

Surface curvature is known to have significant effects on film cooling performance, with convex curvature inducing increased film effectiveness and concave curvature causing decreased film effectiveness. Generally, these curvature effects have been presumed to scale with 2r/d at the film cooling hole location, where r is the radius of curvature and d is coolant hole diameter. In this study, the validity of this scaling of curvature effects are examined by performing experiments in regions of large and low curvature on a model vane. Single rows of cylindrical holes were placed at various locations along the high curvature section of the suction side of the vane. For the first series of experiments, a single row of holes was placed at two locations with different local surface curvature. The coolant hole diameters were then adjusted to match 2r/d values. Results from these experiments showed that there was better correspondence of film performance when using the 2r/d scaling, but there was not an exact matching of performance. A second series of experiments focused on evaluating the effects of curvature downstream of the coolant holes. One row of holes was placed at a position upstream of the highest curvature, while another row was placed at a downstream position such that the radius of curvature was equivalent for the two rows of holes. Results indicated that the local radius of curvature is not sufficient in understanding the performance of film cooling. Instead, the curvature envelope downstream of the coolant holes plays a significant role on the performance of film cooling for cylindrical holes.

On Film Cooling of Turbine Guide Vanes : From Experiments and CFD-Simulations to Correlation Development

“…It is worth mentioning that Winka et al [74] have reported that, consistent with the results in [62] and [75] the AFE for the row of holes located in the strong convex curvature region is higher than the low curvature position for cylindrical holes and when the momentum flux ratio is less than unity. The obtained results here confines with these studies when cylindrical holes with blowing ratios higher than 0.6 are considered.…”