The application relates to the technical field of aero-engines and discloses a damping structure for an aero-engine, which comprises multiple pairs of lug ears on a rear mounting joint, multiple flanges of a hanger, and claw pins transversely inserted and connected with the corresponding lug ears and flanges, multiple counterbores are symmetrically arranged in two end faces of each lug ear, the damping structure further comprises a
ball joint, an energy-absorbing ring and multiple
vibration isolation flanges, a connecting hole for inserting and fixing the claw pin is arranged in the middle of the
ball joint, the connecting hole is larger than the outer
diameter of the claw pin, a fixing sleeve is arranged on the claw pin and tightly fixed with the inner wall of the
ball joint through an outer arc surface, the fixing sleeve is used for absorbing vibration
kinetic energy transmitted by the claw pin through deformation, the multiple
vibration isolation flanges are connected with the two end faces of each lug ear one by one, the
vibration isolation flange comprises a chuck used for fixing the claw pin, multiple force-bearing shafts welded and fixed on the same side end face of the chuck and multiple soft vibration isolation sleeves arranged on the force-bearing shafts, and each force-bearing shaft is arranged in a corresponding
counterbore. The application can reduce the vibration force transmitted from the engine to the wing.