Aircraft engine compressor blades are high-temperature, high-pressure, and high-speed rotating components. The working conditions are relatively harsh. The blade tips are prone to cavitation. If the amount of wear exceeds a certain amount, they will fail, reduce the compression ratio, and shorten their service life. Replacing new blades will greatly increase maintenance costs and cause many losses. Currently, the repair methods that can be considered and are theoretically feasible include arc welding, plasma welding, and laser powder 3D printing. Arc welding and plasma welding not only have a large amount of heat input but also cannot solve the micro-undercut phenomenon and cause serious deformation on the air inlet and outlet edges of the blades. Laser powder 3D printing to repair blade tips has low efficiency, high cost, and low qualification rate.

The adaptive laser cladding technology developed by Huirui for thin-walled variable cross-sections of compressor blades and the precise comparison technology of laser coaxial imaging systems can greatly improve the accuracy and quality of additive repair of aviation compressor blades.

Laser powder feeding 3D printing remanufacturing technology uses high-power laser beams focused by optical elements to obtain extremely high energy density, instantly melting the surface of the substrate, and at the same time completely melting the alloy powder that is preset or automatically sent to the surface of the substrate in synchronization with the laser beam. , to obtain a dense coating that is metallurgically bonded to the substrate. The bonding strength is generally not less than 95% of the original matrix material. The base material can achieve micro-melting on the surface during laser processing. The micro-melting layer is 0.05~0.1mm, and the heat-affected zone of the matrix is extremely small, generally 0.05~0.5mm. There is no coarse casting structure in the cladding layer and the substrate. The cladding layer and its interface have a dense structure, fine grains, no voids, inclusion cracks, and other defects. The temperature rise of the substrate during laser processing does not exceed 80°C. The deformation after laser processing is calculated as 0.01mm. After heat treatment and stress release after cladding, the deformation amount is calculated as 0.001mm, which can be completely omitted.

Due to the change in blade tip thickness, the middle thickness is the largest, requiring greater power during cladding. If the laser is used for cladding with the same power, the thinnest parts at both ends will be melted by the higher power and cannot be repaired. Therefore, in order to obtain the corresponding cladding width without melting the material at both ends of the blade, variable power cladding is used. Since both ends of the blade are extremely thin, the thickness of both ends of the 8-level blade is only 0.2mm. Undercutting is easy to occur during laser cladding, so special treatment is required at both ends to solve the undercutting problem. In low-power cladding, it is necessary to rely on the laser coaxial imaging system for accurate comparison. The currently repaired compressor rotor blades are in good condition.