Research on foreign object damage and grinding repair schemes of compressor blades

Foreign object damage (FOD) on compressor blades of aero-engines lowers the capacity of blades and poses a serious threat to civil aviation safety, so the repair of blades with FOD deserves more attention. The finite element model of the aero-engine compressor blade was established, and the finite element analysis was carried out on the damaged blades with FOD notches and the blades after grinding and repair. The natural frequencies of different types of blades and the global and local peak stress under rotating conditions were compared. It was confirmed that the stiffness of the repaired blades was acceptable, and the optimal grinding repair scheme was selected.