Most studies of turbine airfoil film cooling in laboratory test facilities have used relatively large plenums to feed flow into the coolant holes. However, a more realistic inlet condition for the film cooling holes is a relatively small channel. Previous studies have shown that the film cooling performance is significantly degraded when fed by perpendicular internal crossflow in a smooth channel. In this study, angled rib turbulators were installed in two geometric configurations inside the internal crossflow channel, at 45 deg and 135 deg, to assess the impact on film cooling effectiveness. Film cooling hole inlets were positioned in both prerib and postrib locations to test the effect of hole inlet position on film cooling performance. A test was performed independently varying channel velocity ratio and jet to mainstream velocity ratio. These results were compared to the film cooling performance of previously measured shaped holes fed by a smooth internal channel. The film cooling hole discharge coefficients and channel friction factors were also measured for both rib configurations with varying channel and inlet velocity ratios. Spatially averaged film cooling effectiveness is largely similar to the holes fed by the smooth internal crossflow channel, but hole-to-hole variation due to inlet position was observed.
Rib Turbulator Effects on Crossflow-Fed Shaped Film Cooling Holes
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 19, 2018; final manuscript received October 4, 2018; published online January 21, 2019. Editor: Kenneth Hall.
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Fox, D. W., Jones, F. B., McClintic, J. W., Bogard, D. G., Dyson, T. E., and Webster, Z. D. (January 21, 2019). "Rib Turbulator Effects on Crossflow-Fed Shaped Film Cooling Holes." ASME. J. Turbomach. March 2019; 141(3): 031013. https://doi.org/10.1115/1.4041673
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