Study on Stacking of Re-Camber in Subsonic Compressor Cascade

To ameliorate the flow matching of end region in compressor cascade, by numerical simulation, with straight blade and positive bowed blade compressor cascade as application background, different stacking of re-camber blade have been adopted for comparative study of their effect on compressor cascade aerodynamic performance. The results show that, in subsonic compressor cascade, leading edge (LE) re-camber can reduce the incidence effectively. Subject to the same re-camber angle, trailing edge (TE) stacking is the most effective way by fixing the TE immobile. No matter what kind of stacking has been adopted, front or rear blade will be locally bowed, affecting on flow field in compressor cascade similar to bowed blade. Applied in positive bowed blade, TE stacking re-camber will partly counteract the effect of positive bowed on front blade, but not entirely suppress the effeteness. While LE stacking re-camber will promote the effect of positive bowed on rear blade. It is recommended that LE stacking re-camber can be applied in subsonic straight blade, and TE stacking re-camber can be applied in subsonic positive bowed blade.