The invention provides a
machining method of a remelted-layer removed gas film hole for an aero-engine
turbine blade, and belongs to the technical field of aero-engine
turbine blade
machining. The
machining method comprises the steps that a
turbine blade composite cooling structure is designed, gas film hole machining is conducted through an ultrafast
laser circumferential
cutting and
spiral scanning machining method,
abrasive flow machining is conducted, and a remelted layer is removed through a remelted
layer removal solution. According to the machining method of the remelted-layer removed gas film hole for the aero-engine
turbine blade, the ultrafast
laser circumferential
cutting and
spiral scanning machining method is adopted for gas film hole machining, the
thermal effect can be greatly reduced, the
surface integrity is improved, the machined gas film hole is few in burr, groove and microcrack, and the maximum thickness of the remelted layer is not greater than 25 [mu]m; abrasiveparticles evenly conduct
grinding on the surface or a corner of a channel under action of pressure, not only can the allowance be removed, but also the effects of burr removing, chamfering and finishing are achieved, the remelted layer can also be effectively reduced, the aperture increment is controlled to be 0.02 mm-0.04 mm, and the remelted layer and microcracks can be effectively controlled; and the remelted layer is further removed by adopting the remelted
layer removal solution, and the effect that no remelted layer residual occurs in an inlet and an outlet of the gas film hole can be achieved.