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Experimental Study of Corner Stall in a Linear Compressor Cascade 被引量:10
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作者 MA Wei OTTAVY Xavier +2 位作者 LU Lipeng LEBOEUF Francis GAO Feng 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2011年第3期235-242,共8页
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 a... 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 comer 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 sur- faces measured by pressure taps and the total pressure losses of outlet flow measured by a five-hole pressure probe. The maxi- mum losses as well as the extent of losses of the comer stall are presented as a function of the investigated incidences. 展开更多
关键词 comer separation COMPRESSOR CASCADES INCIDENCE hot-wire anemometry computational fluid dynamics
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