Film-cooling prediction on turbine blade tip with various film hole configurations
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Different film hole arrangements on the plane and squealer tips of a turbine blade are investigated using a Reynolds stress turbulence model and nonequilibrium wall function. The three film hole configurations considered are 1) the camber arrangement, where the film-cooling holes are located on the mid-camber line of the tips; 2) the upstream arrangement, where the film holes are located upstream of the tip leakage flow and high heat transfer region; and 3) the two-rows arrangement, which is a combination of the camber and upstream arrangements. Calculations were performed first for the nonrotating cases under low inlet/outlet pressure ratio conditions with three different blowing ratios. The predicted heat transfer coefficients are in good agreement with the experimental data, but the film-cooling effectiveness is somewhat overpredicted downstream of the film-holes. Simulations were then performed for the nonrotating and rotating camber line film hole configuration under high inlet/outlet pressure ratio conditions, which are close to engine conditions. It is found that the rotation decreases the plane tip film-cooling effectiveness but only slightly affects the squealer tip film cooling. However, the rotation significantly increases heat transfer coefficient on the shrouds. Copyright 2006 by the American In stitute of Aeronautics and Astronautics, Inc. All rights reserved.
