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TURBINE-09. Proceedings of International Symposium on Heat Transfer in Gas Turbine Systems
August, 9-14, 2009, Antalya, Turkey

DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst


ISBN Print: 978-1-56700-263-8

COMPARISON OF FILM COOLING IN THE PRESENCE OF VARIOUS MAINSTREAM PRESSURE GRADIENTS

page 18
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.330
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要約

In the present paper, experimental and numerical investigations have been carried out on the film cooling characteristics of cylindrical hole, laid-back fan shaped hole and double-fan shaped holes in the presence of various mainstream pressure gradients. Three momentum ratios: 1, 2 and 4, were measured. The pressure gradients, especially the adverse pressure gradient, improve the jet coverage and the jet lateral spread for cylindrical hole film cooling and 45° inclined double-fan shaped hole film cooling, especially under large momentum ratios. However, the effect of pressure gradient on the film cooling effectiveness of 90° inclined double-fan shaped hole is different from that of 45° inclined double-fan shaped hole. The film cooling effectiveness under favorable pressure gradient is the highest for 90° inclined hole. The effect of pressure gradients on the film cooling effectiveness of laid-back fan shaped hole and 20° inclined double-fan shaped hole is weak because of the jets’ good attachment on the wall. For all the holes, the normalized heat transfer coefficient h/h0 under favorable mainstream pressure gradient is the highest under all the momentum ratios. Relative to the h/h0 of zero pressure gradient, the h/h0 of adverse pressure gradient is lower or close in the upstream region, but higher in the downstream region.

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