Machining method of remelted-layer removed gas film hole for aero-engine turbine blade

Abstract

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.

Description

technical field [0001] The invention belongs to the technical field of aero-engine turbine blade processing, in particular to an aero-engine [0002] A machining method for removing gas film holes in remelted layers of turbine blades. Background technique [0003] The turbine blade is the part with the largest thermal load and mechanical load in the aero-engine, and its working environment is harsh. [0004] To withstand the impact of high-temperature and high-pressure gas after combustion, its manufacturing technology is listed as the key technology of modern aero-engines. Among them, blade casting technology and gas film hole processing technology are the main difficulties. At present, the processing technology of blade air film holes mainly includes long pulse laser drilling, electric spark drilling, electro-hydraulic beam drilling and other methods. Among them, the first two methods belong to hot-melt processing, which will produce recasting layer and microcracks on th...

AI Technical Summary

Problems solved by technology

Among them, the first two methods belong to hot-melt processing, which will produce recasting layer and micro-cracks on the hole wall, which seriously affects the surface integrity of the blade, and finally leads to the decline of the material performance and safe service life of the blade.

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