Abstract
In this paper, the blade tip phantom cooling performance was experimentally studied with different cooling hole configurations on the blade surface. Three spanwise angles for leading-edge (LE) cooling holes, and with or without compound angles for pressure-side (PS) cooling holes were included. Pressure sensitive paint (PSP) technique was adopted to obtain the cooling effectiveness contours under four coolant blowing ratios. Computational simulations were performed to help analyze the flow characteristics at near-tip region. Measurements indicated that LE ejections mainly cause phantom cooling phenomenon at tip front portion. Increasing spanwise angle would deteriorate the phantom cooling performance here. The tip surface could be well covered with combined LE and PS coolant ejections. In addition, the cooling effectiveness on the tip rear portion would be increased when the compound angle of PS cooling holes is applied. The aerodynamic comparisons showed that a smaller spanwise angle obtains the lowest loss, and higher loss was observed with a compound angle for PS cooling holes.
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