| Citation: | WU Hong, YANG Dengwen. Aerodynamic and cooling performance of a novel step-shaped slot film cooling geometry[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(2): 264-272. doi: 10.13700/j.bh.1001-5965.2017.0384(in Chinese)
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In order to permanently reduce the coupling vortices in film cooling, a novel step-shaped slot cooling geometry with tangential coolant ejection was introduced and its aerodynamic and cooling performance was numerically investigated. The effects of slot location at the suction and pressure side of a turbine vane and cooling air blowing ratio on these performances were also analyzed. The results show that slot injection from the suction side near-throat region only increases the total pressure loss by about 2%, while injection from the pressure side decreases both the kinetic loss and total pressure loss by about 2.5% with the air exit angle increasing less than 0.1% for low blowing ratios. Meanwhile, the loss coefficient and the air exit angle are not sensitive to the variation of blowing ratios. Additionally, cooling effectiveness downstream of the slot on both suction side and pressure side is rather high and it reaches almost 1.0 for about 8% axial chord of the vane surface on average in high blowing ratio cases.
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