Abstract: Based upon a through-flow code of streamline-curvature method and a quasi-3D arbitrary airfoil blading code, a diffusion loss model is employed in terms of the adjusted factor, a compound shock loss model in terms of Miller-lewis-Hartman (M-L-H) model is developed and a splitter blade positioning scheme is established. Thus, an inverse design system for splittered axial compressors is composed. Using this design system, a high-loaded backward swept fan with a stage pressure ratio of 2.20 is redesigned firstly as a backward swept and secondly as a forward swept splittered fan. The numerical simulations of both flow fields are carried out. In the situation of keeping the prescribed pressure ratio, the backward swept splittered fan has a higher flow rate and a higher stall margin with an approximate adiabatic efficiency compared to the original design. When prescribing a higher pressure ratio of 2.31 which is sustainable by the single conventional stator row, the forward swept splittered fan increases greatly the stall margin with a negligible decline of the adiabatic efficiency by about 0.3% and a lower flow rate. The two redesigns also prove the competence of this design system.

Key words: axial flow compressor, splittered rotor, streamline-curvature approach, loss model, swept blade, numerical simulation