The surface quality of turbine blade in aviation gas turbine engine directly affects the overall performance of the engine. In view of the low geometric accuracy and unstable quality in the surface treatment of turbine blade at home and abroad

the magnetic abrasive technology with magnetic needle is introduced

and different types of magnetic needle

rotating speed of magnetic pole and grinding time are taken as variable factors. The surface roughness and residual stress of the blade are taken as the indexes

and the law between the change factors and the index parameters is analyzed through experiments. The results show that the residual stress on the surface of turbine blade changes from original tensile stress to compressive stress

and the compressive stress increases with the increase of magnetic needle length and magnetic pole speed. The surface roughness of turbine blade and the burr height around the gas film hole are improved obviously by magnetic needle grinding. The research results can provide a reference for improving the surface quality of turbine blade by magnetic needle grinding process.