The paper investigates the effect of non-equilibrium behaviour of boundary layers on the profile loss of a compressor. The investigation is undertaken using both direct numerical simulation (DNS) of a mid-height section of a compressor blade and a reduced order model, MISES. The solutions are validated using experimental measurements made in the embedded stage of a multistage low speed compressor. The paper shows that up to 35% of the suction surface boundary layer of the compressor blade exhibits non-equilibrium behaviour. The size of this region reduces as the Reynolds number is increased. The non-equilibrium behaviour was found to reduce profile loss in most cases, however, in a range of cases where transition occurs through a small separation the presence of non-equilibrium behaviour was found to increase profile loss.
The Effect of Non-Equilibrium Boundary Layers on Compressor Performance
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Wheeler, APS, Dickens, AMJ, & Miller, RJ. "The Effect of Non-Equilibrium Boundary Layers on Compressor Performance." Proceedings of the ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. Volume 2B: Turbomachinery. Charlotte, North Carolina, USA. June 26–30, 2017. V02BT41A040. ASME. https://doi.org/10.1115/GT2017-64635
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