In the processing of manufacturing the compressor blade, there are always the tolerances of blade profile and twist angle, which affects compressor aerodynamic performance. Numerical investigations of S1 surface and three dimensional calculations were conducted to study the influence of the blade profile and twist angle tolerance on compressor aerodynamic performance. The results show that increase of the blade profile results in the growth of airfoil loss and reduction of choke mass flow. At the condition of 0.08 millimeter blade profile, the reduction of choke mass flow is 1%. Peak efficiency gradually decreases a little. The influence of twist angle difference on compressor performance results from the change of throat area caused by blade leading edge twist and exit flow angle caused by blade trailing edge twist. Twist angle has little influence on airfoil loss. Besides, twist angle between positive and minus 0.35 degree has little impact on loss budget. When increase twist angle at the direction of opening leading edge, the performance curve of mass flow and pressure ratio goes to upward and right direction. The choke mass flow and maximum pressure ratio grow. When increase twist angle at the direction of closing leading edge, the performance curve of mass flow and pressure ratio goes to downward and left direction. The choke mass flow and maximum pressure ratio decrease. The reduction of choke mass flow is 0.67% at the condition of twist angle difference 0.35 degree. The influence of twist angle on peak efficiency is trivial.