Abstract: A method for integrated design of compressor blade and casing treatment is applied in the field of turbomachinery. The method includes: determining a parameterization method for blade and casing treatment based on a compressor blade model and a casing treatment model, respectively; obtaining an initial parameter set by using a sampling technology; and obtaining a design with a wide stability margin by using an advanced optimization algorithm without reducing a compressor efficiency. The method may couple an interaction between blades and casing treatment, greatly improving fitness of the casing treatment, so that the compressor may operate stably over a wide working range and R&D costs may be saved.