Numerical investigation on effect of rotor blade lean angle variation on single stage fan stability

Modern day research is striving towards the improvement of stability margin of Fans and Compressors. Flow control techniques are implemented to enhance the performance and increase the stability margin however the control mechanism complexity can be reduced if performance enhancement is built into design of turbomachinery with minimum possible design variables. In this paper numerical investigation on single stage low speed fan has been presented with effect of blade lean angle variation to be the design variable. The said fan has been designed for test rig to be installed at School of Power and Energy, Northwestern Polytechnic University (NWPU).