The invention belongs to the technical field of aero-engines, and discloses a compressor blade machining method. The compressor blade machining method includes the steps that step 1, three-dimensionalmeasurement is carried out, specifically, a crest curve and a trough curve are built by extracting actual curve crest points and trough points of cross sections according to a three-dimensional diagram of a compressor blade; virtual curves of a blade body and a jog are built; step 2, point cloud is extracted, specifically, curvatures of the actual curve, the crest curve and the trough curve of the step 1 are analyzed, and the curves of the crest curve and the trough curve are regulated according to actual curve curvatures; a center line is built according to the crest curve and the trough curve; step 3, a hook face is rebuilt, specifically, a mesh hook face is built with center lines of the cross sections to generate a three-dimensional digital model; step 4, procedures are regulated, specifically, the blade three-dimensional digital model is imported to a three-dimensional software and corrected compared with blade master body data scanned by the three-dimensional software; and step5, numerical control machining is carried out, specifically, numerical control programming is carried out according to the blade three-dimensional digital model of the step 4, and a blade is subjectedto numerical control milling with a ball end milling. According to the compressor blade machining method, the blade precision and the surface roughness of a compressor can be effectively ensured.