In order to achieve uniform surface finishing of aero-engine blades and improve the performance of aeroengine compressor blades

the influence of container configuration and blade installation attitude on polishing effect was studied based on discrete element numerical simulation. The results show that within the range of experimental parameters

when the container height is 124 mm

the container width is 120 mm

the container length is 80 mm

and the blade surface is installed at 90° with the vibration direction

the wear depth and uniformity of the compressor blade finishing are better

which is the optimal container configuration size and installation attitude parameters. After finishing the compressor blade according to the optimal parameters obtained from the simulation

the surface burr and forged oxide of the compressor blade were removed; The sharp edge is passivated

the edge is rounded and neat; The surface is bright. The roughness grade of the blade surface is greatly improved

and the key dimensions of the blade are within the allowable range. The stress state is improved. The research method and results lay a foundation for the efficient and low-cost processing of compressor blades.