In order to spread the advanced technotogy of aeropropfan

skewed swept rotor blades are applied to axial flow fan and compressor.The diactuartor disc theory model is adopted to calculate the main flow of the skewed swept rotor blades in such a manner

as all blades forces affect on the first actuator disc

but the radial forces of blades vanish abruptly on the second actuator disc.Then the radial distribution of the boundary layer thickness (wake thickness) on the outlet surface of the rotor blade is taken as aerodynamic and aeroacoustic characteristic vectors.The effects of the secondary flow

endwall boundary layer

blades rotation and skewed swept regularity (mainly radial forces of blades) are corrected according to plane cascade testing statistical curves.In addition

the results of four calculations demonstrate the effects of the second actuator disc

radial force and corrected outlet flow angle on magnitudes of the calculation results separately.The aerodynamic and acoustic tests show a good agreement of the calculation results with test data.