Effects of Microsurface Riblets on Aerodynamic Performance of Compressor Cascade
In order to reduce the profile loss,the streamwise symmetric V-type microsurface riblets are applied on the compressor cascade blade.The numerical method is adopted to study the effects of riblets width and tip angle,riblets spacing,riblets cover-age,inlet turbulent intensity and inlet Mach number on the aerodynamic performance of compressor cascade.The results show that the total pressure loss reduction is mainly caused by the riblets on blade suction surface.By properly matching the riblets ge-ometry parameters,riblets coverage position and inlet flow parameters,the optimum total pressure loss reduction can be obtained.For riblets on blade suction surface within partial blade chord range,the loss reduction of riblets without spacing is better than that of riblets with spacing at the same incidence angle.For the riblets without spacing,when the tip angle is 60°the loss reduc-tion is the best.For the same riblets structures,the loss reduction is related with the incidence angle.The increase of inlet turbu-lent intensity will enlarge the total pressure loss at the same incidence angle for both smooth blade and blade with riblets.For the same riblets structure,the loss reduction at the same incidence angle and the incidence angle corresponding to the optimum loss reduction are related with the inlet turbulent intensity.When the incidence angle is fixed,the loss reduction generally decreases with the increase of inlet Mach number.The dimensionless riblets width corresponding to the optimum loss reduction and the range of riblets dimensionless width with loss reduction are different.When the dimensionless width of riblets and other parameters of riblets are fixed,the optimum loss reduction and its corresponding incidence angle at different inlet Mach numbers are differ-ent.The optimum loss reduction at lower Mach number is more obvious.The microsurface riblets can reduce the near wall average shear stress and turbulent kinetic energy,and alleviate the turbulent boundary loss.The boundary flow separation can also be delayed,and the blade pro-file loss is reduced.
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