Numerical Simulation for Steady Flow Field of CounterRotating Axial Fan

To enhance the stability and accurate when calculated the complicated turbomachinery rows, an inlet/outlet condition as called general boundary condition and an advanced strongly implicit iterative method named MSIP were presented. Based on rotational arbitrarily curved coordinate and RNG improved k-ε turbulence model, the three-dimensional calculating for a counter-rotating axial fan indicate that it is not appropriate to allocate the maximum load at the blade tip when make an aerodynamic design for axial fan or compressor, especially for counter-rotating system.