Five steady blade rows interface methods were adopted to investigate an extraordinary turbomachinery—contra-rotating compressor. The whole performance

near design condition and near stall condition flow field of contra-rotating compressor were analyzed in combination with experimental data

so as to make a quantitative comparison of the effect on blade row interface parameters transmission among different interface methods. Results validate: (1) the whole compressor efficiency shows obvious difference among different interface methods

while the pressure ratio agrees with experimental data very well. (2) Under the near design condition

the parameters transmission on different interfaces are uniform for conservative coupling by pitchwise rows method. Local conservative coupling method and matching mixing plane methods behave better along downstream interface

while non reflecting 1-D method and full non matching frozen rotor method perform just the opposite. (3) Under the near stall condition

the high entropy loss area surrounding blade leading edge of non reflecting 1-D method and full non matching frozen rotor method expands much bigger. Mainstream and overflow interface within the blade tip twists into an arc closer to the upstream blade row interface.