Computation of leading edge film cooling from a
CONSOLE geometry (converging slot
hole)В
A. Guelailia,
A. Khorsi, andВ M.K. Hamidou
University of Sciences and Technologies, Oran, Algeria
E-mail: guelailia@yahoo.fr
Keywords: gas turbine blade, film cooling efficiency, numerical simulation, mass flow rate, cylindrical and converging slot holes
Pages: 33–42
Abstract
The aim of this study is
to investigate the effect of mass flow rate on film cooling effectiveness
and heat transfer over a gas turbine rotor blade with three staggered rows
of shower-head holes which are inclined at 30° to the spanwise direction,
and are normal to the streamwise direction on the blade. To improve
film cooling effectiveness, the standard cylindrical
holes, located on the leading edge region, are replaced with
the converging slot holes (console). The ANSYS CFX has been
used for this computational simulation.
The turbulence is approximated by a k-e model. Detailed film effectiveness distributions
are presented for different mass flow rate. The numerical results are
compared with experimental data.
DOI: 10.1134/S0869864316010042
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