Numerical Simulation of Transonic Compressors with Different Turbulence Models

One of the most commonly used techniques in aerospace engineering is RANS (Reynolds average Navier–Stokes) approach for calculating transonic compressor flow field, where accuracy computation significantly affected by turbulence model used. In this work, we use SA, SST, k-ɛ, and PAFV developed based on side-biased mean fluctuations velocity strain rate tensor to numerically simulate NASA Rotor 67 evaluate modeling numerical calculations compressors. The simulation results demonstrate that four models are generally superior 67, which essentially satisfies requirements calculations; comparing analyzing ability predict aerodynamic performance compressors capture details inside rotor. errors clogging calculated with experimental data 0.9%, 0.8%, 0.7%, 0.6%, respectively. peak efficiencies 2.2%, 1.6%, 4.9%. SA SST were computational characteristics industry. Their stability better their outputs comparable. k-ɛ calculates pressure ratio efficiency closest data, but its field near wall surface not ideal because cannot accurately region high shear stresses. has a prediction complex phenomena such as rotor internal shock wave location, shock–boundary layer interaction, etc., due turbulent scale vector form, small.