Numerical Study of Surge Phenomenon with k-ε turbulence Model in Axial flow Compressors

Most Axial compressors performance in aerodynamic applications systems are limited, due to flow instability at low mass flow rate One of these Instabilities is surge phenomena. In the present study, analysis of three-dimensional unsteady Navier-Stokes equations in multistage turbomachinery is studied by Fluent software and (k-ε) turbulence model and SKE The results showed that this model compared with conventional types, to turbomachinery is more accurate and has faster convergence rate. And at investigate the compression system behavior when occurring phenomenon surge and changes of pressure and mass flow rate fluctuations over time, in different parts of the compressor performance is acceptable accuracy. So that the average mass flow rate calculated for the NASA Rotor 67 in the present study and the model SKE equal to 34/23 (kg /s) and laboratory data have shown the value of 34/61 (kg /s). It also became clear that under surge condition, by increasing the design round, vibration will have much decrease.