Machining method for aluminum alloy turbine blade of aero-engine

A technology for aero-engine and turbine blades, which is applied in the processing field of aluminum alloy aero-engine turbine blades, can solve the problems of blade material performance and safety service life decline, and affect the surface integrity of blades, so as to reduce thermal effects, improve surface integrity, Good cutting performance

Inactive Publication Date: 2018-04-27
安徽恒利增材制造科技有限公司
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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.

Method used

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Embodiment Construction

[0025] The technical solutions in the present invention will be clearly and completely described below with reference to the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0026] A processing method of an aluminum alloy aero-engine turbine blade, comprising the following steps:

[0027] Step 1: aluminum alloy smelting, the aluminum alloy contains the following chemical components by weight: Cu4.87%, Mn0.5%, Ti0.27%, Cd0.16%, V0.12%, Fe2 Cl 6 Refining, let stand for 20min, pour the turbine blade at 720℃, the pouring temperature is 250-300℃, the turbine blade is cast with precision and no margin, the tenon adopts three pairs of fir tree-shaped tenon teeth, and the inner cavity of the blade adopts "U" ” type backflow convection cooling and composite cooling structure of blade leading edge and trailing ed...

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Abstract

The invention discloses a machining method for an aluminum alloy turbine blade of an aero-engine, and belongs to the technical field of machining for turbine blades of aero-engines. The machining method comprises the following steps: casting the aluminum alloy turbine blade, carrying out film hole machining through a machining method of ultrafast laser annular cutting and spiral scanning, and removing a remelted layer through abrasive particle flow machining and a melted layer removal solution. According to the machining method disclosed by the invention, the film hole machining is carried outthrough the machining method of ultrafast laser annular cutting and spiral scanning, so that the heat effect can be greatly reduced and the surface integrity is improved, the machined film hole has few burrs, grooves and micro-cracks, and the maximum thickness of the remelted layer is not greater than 25[mu]m. Abrasive particles uniformly grind the surface or the corners of a channel under a pressure effect, so that allowance can be removed, the effects of deburring, chamfering and polishing can also be acted, the remelted layer can also be effectively reduced, a hole diameter increment is controlled to be 0.02mm to 0.04mm, and the remelted layer and the micro-cracks can be effectively controlled. The remelted layer is further removed through the remelted layer removal solution, so that no remelted layer residue at the inlet-outlet of the film hole can be achieved.

Description

technical field [0001] The invention belongs to the technical field of aero-engine turbine blade processing, and in particular relates to a processing method of an aluminum alloy aero-engine turbine blade. Background technique [0002] Turbine blades are the most thermally and mechanically loaded components in aero-engines. They have harsh working environments and withstand the impact of high-temperature and high-pressure gas after combustion. is the main difficulty. 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. The first two methods belong to hot melt processing, which will produce recast layers and micro-cracks on the hole wall, which will seriously affect the surface integrity of the blade, and ultimately lead to the decline of the material performance and safe service life of the blade. SUMMARY OF THE INVENTION [0003] In order to so...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/02
CPCB23P15/02
Inventor 夏建强常峰
Owner 安徽恒利增材制造科技有限公司
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