Vortex control and aerodynamic performance improvement of a highly loaded compressor cascade via inlet boundary layer suction

Effects of inlet boundary layer suction on the vortex structure and cascade loss in a highly loaded compressor cascade were investigated experimentally. Ink-track visualization was undertaken on cascade endwall and the blade surface. Ten traverse planes from upstream to downstream of the cascade in a rectangular wind tunnel were measured by an L-shaped five-hole probe. These tested planes revealed the process of emergence, development and decline of several principal vortices as well as the corresponding additional losses. Details of ink-track visualization displaying the secondary flow behavior of boundary layer upon endwall and blade surface assist to make judgment on vortex evolution. Inspection of the vortex structure revealed that highly loaded compressor was characterized by large-scale vortices in the endwall region. After suction, these vortices are all well organized and under control. Among all of them, passage vortex is most sensitive to the variation of the inlet boundary layer, and its main function is to spread low-energy fluid rather than to produce loss. On the other hand, a wall vortex and a concentrated shedding vortex take place inside and after the cascade, respectively, and engender considerable accompanying loss as they dissipate. The effects of inlet boundary layer suction on them are correspondingly weaker. About one forth of the total loss in the baseline cascade was eliminated when boundary layer suction flow rate reaches 2.5 % of the inlet mass flow. The feasibility of simplifying the suction system is also verified through this work.