Investigation on Compressor Blade Load Distribution in Endwall Regions

In order to find out the effects of blade load distribution on the flow in endwall boundary layers,three sets of planar cascades were designed,in which the blade loads tending to blade front,middle and rear parts,are numbered as No 1,No 2 and No 3 respectively.The static pressure on the blades and the cascade outlet flow fields are investigated by experiments and three dimensional Navier Stokes equation methods.The following conclusions were drawn:The performance of the No cascade #3 is inferior to that of 2 cascades #1 and #2;In the endwall region of cascade #2,the flow outlet loss is smaller but the deviation angles are larger and the pressure elevating ability is weaker than those of cascade #1;In a given inlet endwall boundary layer,the variation of the blade force defect is positively correlative to the blade force variation;In the corner region formed by the blade suction surface and the endwall,corner vortex does not induce obvious decrease of pressure on the suction surface of blade rear part in the endwall region;The outlet vortex strength of cascade #2 is smallest.