Controlling mechanisms of bowed and swept of rotor in transonic axial compressor

In a 1.5-stage transonic axial compressor, the controlling mechanism of bowed and swept blades was researched by 3-D numerical simulation when the compressor was working at different conditions. Results show that the combined scheme of sweepforward and positive bow is better than the combined scheme of sweepback and negative bow at the design speed, but its completely opposite at the part speed, because the controlling mechanisms of different bowed and swept schemes are different at the design speed and the part speed. The intensity and position of shock can be changed by the bowed and swept blades at the design speed, the same as the leakage vortex in the shroud gap and the spanwise C-shape pressure distribution; so the surge margin of compressor could be improved by combined action of three changed factors, but followed with the decrease of efficiency. However, the shock disappeared at the part speed, the reverse pressure gradient of the suction surface at the top of blade and the spanwise C-shape pressure distribution are changed, improving the aerodynamic stability of compressor and cutting down the efficiency.