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Laser impact processing method for hole structure

A technology of laser shock and shock treatment, which is applied in the field of laser processing, can solve problems such as the inconspicuous strengthening effect of hole corners, and achieve the effect of improving the strengthening effect and improving the life of the structure

Active Publication Date: 2008-02-20
BEIJING AVIATION MFG ENG INST CHINA AVIATION NO 1 GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method has no obvious strengthening effect on the hole corner

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0021] Example 1: laser shock treatment is performed on a φ2.5mm hole in 2024 aluminum alloy with a thickness of 3mm, and a φ2.5mm rivet of the same material is transition-fitted into the hole. The nail head is flush with the surface to be treated, and the periphery of the hole is flush The rivet section is coated with about 0.01mm thick black paint in the range of about φ15mm. After the black paint is dried, place the workpiece flat and fix it. Use a tap to draw deionized water to flow in the black paint part. The water layer is about 1mm thick. Use 30J, 30ns The pulsed laser gathers a light spot of about φ6mm on the surface of the workpiece for laser shock treatment. After the impact, due to plastic deformation, the rivet and the hole fit more closely, but after the rivet is carefully removed, the size of the inner hole changes little and is effectively strengthened. After one side is strengthened, the other side is strengthened by the same process, but the used rivets cannot...

Embodiment 2

[0022] Example 2: Laser shock treatment is performed on a φ4mm hole in a 7050 aluminum alloy with a thickness of 4mm, and a φ4mm steel pin is transition-fitted into the hole. The range of the test piece is placed vertically, and the deionized water is led to flow on the aluminum foil tape with a tap. The water flow layer is about 1.5mm thick. A 40J, 30ns pulsed laser is used to gather a light spot of about φ6mm on the surface of the workpiece for laser shock treatment. Plastic deformation, the pin fits more closely with the hole, but the size of the inner hole hardly changes after the pin is squeezed out, but the strengthening indentation is obvious. After strengthening one side, carry out the same process on the other side, but the used pins cannot be used.

Embodiment 3

[0023] Example 3, laser shock treatment is performed on a φ20mm hole in TC4 titanium alloy with a thickness of 20mm, and a custom-made φ20×20mm No. 45 steel rod is used to fit it into the hole. Scope, the test piece is placed horizontally, and deionized water is drawn to flow on the aluminum foil with a tap. The water flow layer is about 2mm thick. A 45J, 30ns pulsed laser is used to gather a spot of about φ5mm on the surface of the workpiece for laser shock treatment. The center of the spot circle is at the circumference of φ20mm. On the above, the distance between the spot and spot is about 2.5mm. After 25 overlapping spots, one side is strengthened, and then the other side is done. Due to the plastic deformation after the impact, the steel rod fits more closely with the hole, and the steel rod needs to be carefully knocked out to take out the steel rod. The strengthening indentation on the surface of the titanium alloy and the steel rod is very obvious.

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PUM

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Abstract

The invention pertains to laser processing technique, relating to an improved treatment for porous structure laser shock. Steps of the treatment are as follows: a mandril or a bush is positioned; an absorption layer and a constraint layer are arranged; the laser shock is treated; the absorption layer constraint layer is cleaned up; the mandril or the bush is taken out from the treated porestructure. The invention improves strengthening effect of angle of the pole, so as to prolong structural life of airplane. The invention especially solves the problem of strengthening a pole of diameter less than 2.5mm which is hard to be strengthened by the prior art.

Description

technical field [0001] The invention belongs to the laser processing technology and relates to the improvement of the laser shock processing method for the hole structure. Background technique [0002] There are tens of thousands of hole structures on the aircraft. These hole structures become typical stress concentration structural details, and fatigue cracks are easily generated under alternating loads. These fatigue crack sources are mostly distributed at the edges of the hole corners. The fatigue performance is greatly affected. At present, shot peening and cold extrusion are used to strengthen the pore structure, but for the pore structure below 2.5mm, the strengthening effect of shot peening and cold extrusion process is not ideal. The United States once used laser shock treatment to strengthen the hole structure. The method is to concentrically impact the hole structure with an annular spot slightly larger than the hole diameter. In order to avoid the pressure rele...

Claims

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Application Information

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IPC IPC(8): C21D1/09
Inventor 邹世坤曹子文
Owner BEIJING AVIATION MFG ENG INST CHINA AVIATION NO 1 GRP
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