Numerical simulation was conducted to explore the inlet pre-swirl design methodology and its influence on aerodynamic performance for highly loaded inlet stage fan rotor at full speeds

as well as the typical part speeds characteristic with optimum inlet pre-swirl distribution.The fan rotor was designed to produce a total pressure ratio of 2.55 and loading coefficient of 0.42 at a tip speed of 480m/s.The result indicates that conventional rotor has capability of achieving this loading level

but inlet guide vane is necessary in design.The adoption of positive pre-swirl and low reaction degree increases the tip performance effectively

negative pre-swirl is required at hub for stator based on conventional design method;rotor with aforementioned pre-swirl design has favorable performance at typical part speeds.