Numerical Simulation Of Tip Clearance Flow In Axial Compressor

This paper adopts third-order NND (non-osclillatory containing no free parameters and dissipative scheme) scheme compared with other NND schemes. This scheme is high resolving power in space. High resolving power and efficiency numerical analysis program is developed. NASA-37 transonic and NWPU-1 subsonic rotors are calculated by using this program. Results of calculation indicates that this program can admirably simulate rotor rows flow in axial compressors and distinguish passage shock, leakage vortex path and separation of boundary layer. Numerical analysis agrees well with experimental results. Consequently numerical analysis program is effective.