Numerical investigation of the effects of swept blade on the aerodynamic performance of a highly loaded transonic two-stage fan

Both conventional and swept schemes are adopted to design a highly-loaded transonic two-stage fan. The effects of swept blade on the aerodynamic performance of the fan are investigated using the three-dimensional numerical simulation method. The results indicate that; the adiabatic efficiency and the stall margin of the swept scheme are increased by 0. 63% and 7. 1% respectively than the conventional scheme; the corner separation of the flow in the second stator passage is suppressed effectively by the swept stator; the stage matching problem that the second stage has already reached its stall condition while the first stage still has certain levels of stall margin at near design point in the conventional scheme has been improved by the swept design in the swept scheme; in this highly-loaded two-stage fan, the first stage does not start its stalling process until the second stage reaches its near stall condition and the fan starts to stall when both the first and second stages reach their stall conditions; the distance of the shock location from the leading edge of the forward-swept rotor is farther, and the shock moving upstream velocity due to the increasing backpressure is slower than that in the conventional rotor.