Experimental Study of Corner Stall in a Linear Compressor Cascade

摘要

To gain a better knowledge of the mechanisms and to calibrate computational fluid dynamics tools including both RANS and Large Eddy Simulation, a detailed and accurate experimental study of corner stall in a linear compressor cascade has been carried out. Data are taken at a Reynolds number based on blade chord of 3.82× 10s. At first, inlet flow boundary layer is surveyed using hot-wire anemometry. Then to study the effects of incidence, measurements using a five-hole probe at inlet and outlet of the cascade, with static pressure taps both on blade and endwall surfaces, have been acquired at five different incidences. The maximum losses as well as the extent of losses of the comer stall are increase with incidence. At last, oil visualization and two-dimensional Particle Image Velocimetry are used to investigate the flow filed at incidence equal to 4 degree. These data could be used to evaluate and to improve CFD tools.