Based on arranging all previous axial flow compressor performance experimental results carried out on a compressor experimental facility

some typical abnormal aerodynamic physical phenomena presented in the experimental system were analyzed. Through analyzing experimental data and validating suppression methods

the formation mechanism of these compressor experimental abnormal aerodynamic phenomena was revealed initially. The research results indicate that the partial inlet guide vanes angle maladjustment produces disturbance on the outlet flow field

and lead to the performance and stability of the compressor deterioration. The inverse flow air occurred at the tip cavity channel of the compressor first rotor is the reason that the measurement value of the out wall static pressure is high before the first rotor. By inhibiting the inverse flow

the compressor aerodynamic performance can improve. The change of corrected mass flow versus the inlet throttling ratio

which is the effective method to determine the leakage problem of compressor experimental intake system. The research results can play an important role on guiding compressor performance experimental fault diagnosis and improving experimental analysis ability.