The structures of flow and vortices, especiallyt separated flow, on and near the blade surfaces of an annular compressor cascade under different incidences have been studied based on the oil-film images obtained in an experiment. The structures of the separated flow on the blade surfaces have been given. The results indicate that there are three different separation regions, namely, the top, middle and low separation region, in the annular compressor cascade. The low region is the largest and most important one. The top one is very small. The vortices near the blade tail may concentrate, intensify and even drop off with the increase of the incidence.
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