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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

EFFECT OF THE GEOMETRY OF FILM COOLING HOLES ON HEAT TRANSFER COEFFICIENT IN CONDITION OF VARIOUS MAINSTREAM PRESSURE GRADIENTS

page 16
DOI: 10.1615/ICHMT.2009.HeatTransfGasTurbSyst.350
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SINOPSIS

According to the pressure distribution on the blade surface, three various test sections of the flat plate have been made produced the zero, favorable or adverse mainstream pressure gradients, respectively. A new type film cooling hole has been presented that both the entrance and the exit are expanded, called the bidirectional expanded holes. The effect of the geometry of film cooling holes on the nominal heat transfer coefficient, h/h0, has been investigated experimentally under three various mainstream pressure gradients utilizing a conventional temperature measurement technique named metal film & thermocouple. Result showed that plane angles, α, and radial angles, β, are the dominant influencing factors of noticeable effects on h/h0, however the pitch between the adjacent holes, p, is secondary factor. A trend is seen mostly that h/h0 for various mainstream pressure gradients are decreased with the distant from the exit of the film hole, x/d, increasing; in the vicinity of the hole the drastically altered flow-field has a strong impact and can result in a substantial augmentation of the heat transfer.

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