An aerodynamic single disciplinary optimization and an aerodynamic/structural multidisciplinary optimization of an axial compressor blade are performed using evolutionary algorithms in this paper. The blade is optimized for maximizing its isentropic efficiency in the aerodynamic single disciplinary optimization. The isentropic efficiency of the optimum blade obtained from the aerodynamic single disciplinary optimization is 1.65% higher than that of the reference blade, however, the mechanical performance analysis indicates that it has a higher stress distribution and does not satisfy the vibration frequency constraint. In the multidisciplinary optimization, the maximum of the isentropic efficiency and the minimization of the maximum stress are selected as the design objectives. The analysis results indicate that the method of dealing with minimization of the maximum stress as a design objective is proper and that the presented multiobjective and multidisciplinary optimization method is more suitable for the optimization design of a real turbomachinery blade than the traditional heuristic aerodynamic-structural iteration.