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

A technology of aero-engine and turbine blades, which is applied in the field of aero-engines, can solve problems such as the surface integrity of shadow blades, the performance of blade materials, and the decrease in safety service life, so as to control remelting layers and microcracks, reduce thermal effects, and reduce remelting layer effect

Inactive Publication Date: 2018-03-20
宁国市华成金研科技有限公司
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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 seri

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

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[0027] The technical solutions in the present invention are clearly and completely described below in conjunction with the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0028] A method for processing air film holes in a remelted layer of an aeroengine turbine blade, comprising the following steps:

[0029] Step 1: The turbine blade is made of directional high-temperature casting alloy, and the blade body is precision cast without margin. Composite cooling structure of edge air film cooling, turbine blade cooling channels such as figure 1 , the cooling air is divided into two paths from the bottom of the tenon of the blade and enters the inner cavity of the blade, and then is discharged from the air film hole at the leading edge of the blade and the exhaust slot at the trailing edge of the blade thro...

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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...

Claims

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Application Information

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IPC IPC(8): B23P15/02
CPCB23P15/02
Inventor 程国华
Owner 宁国市华成金研科技有限公司
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