Abstract
In order to gain a better knowledge of the mechanisms and to calibrate computational fluid dynamics (CFD) tools including both Reynolds-averaged Navier-Stokes (RANS) and large eddy simulation (LES), 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 of 382 000 based on blade chord and inlet velocity. At first, inlet flow boundary layer is surveyed using hot-wire anemometry. Then in order to investigate the effects of incidence, measurements are acquired at five incidences, including static pressures on both blade and endwall surfaces measured by pressure taps and the total pressure losses of outlet flow measured by a five-hole pressure probe. The maximum losses as well as the extent of losses of the corner stall are presented as a function of the investigated incidences.
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