To clarify the difference in aerodynamic performance and flow transition between compressors using highly-loaded design and general design (low-loaded)

the cascade experiments including suction side flow pattern and parameter measurement were performed. Based on the experimental boundary conditions

numerical researches on the suction boundary layer with γ-θ transition model were also conducted. Result showed that

compared with the low-loaded cascade

as the incidence angle increased

the flow boundary layer in highly-loaded cascade transformed from the attached flow to the separated flow

which enhanced wake width and loss and made wake integrate with corner separation loss region into a “strip-shape” loss region. Meanwhile

the flow boundary flow in low-loaded cascade was still an attached flow and the corner separation maintained open separation close to the endwall. The results indicated that highly-loaded design enhanced the inverse pressure gradient in the cascade

causing the flow more easily separated

the surface shape parameter presented a wide range of “peak” distribution

and the transition mode also changed from local bypass transition to all-span separation-induced transition.