Application of local indentations for film cooling of gas turbine blade leading edge
V.Yu. Petelchyts1, A.A. Khalatov2,3, D.M. Pysmennyi1, and Yu.Y. Dashevskyy1
1Gas Turbine Research and Production Complex «Zorya»-«Mashproekt», Mykolaiv, Ukraine
2Institute of Engineering Thermophysics, National Academy of Sciences of Ukraine, Kyiv, Ukraine
3National Technical University of Ukraine «I. Sikorskiy Kyiv Polytechnic Institute», Kyiv, Ukraine
E-mail: vypete@e-mail.ua, artem.khalatov@vortex.org.ua
Keywords: film cooling, blowing parameter, leading edge, cooling system, semi-spherical dimple, trench
Pages: 713–720
Abstract
The paper presents results of computer simulation of the film cooling on the turbine blade leading edge model where the air coolant is supplied through radial holes and row of cylindrical inclined holes placed inside hemi-spherical dimples or trench. The blowing factor was varied from 0.5 to 2.0. The model size and key initial parameters for simulation were taken as for a real blade of a high-pressure high-performance gas turbine. Simulation was performed using commercial software code ANSYS CFX. The simulation results were compared with reference variant (no dimples or trench) both for the leading edge area and for the flat plate downstream of the leading edge.
DOI: 10.1134/S0869864316050097
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