Crack initiation and expansion method in restraint structural component based on laser shock peening

A technology of laser shock strengthening and expansion method, which is applied in the field of repairing metal structural parts, can solve the problem that the fatigue life of structural parts cannot be well guaranteed, and achieve the effects of preventing the initiation of micro-cracks, suppressing the formation of notch cracks, and rapidly repairing and prolonging life.

Inactive Publication Date: 2016-02-24
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Abstract
  • Description
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Problems solved by technology

[0003] Aiming at the deficiency that the repair methods of metal structural parts commonly used in the prior art cannot guarantee the fatigue life of the structural parts well, the technical problem to be solved by the present invention is to provide a

Method used

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  • Crack initiation and expansion method in restraint structural component based on laser shock peening
  • Crack initiation and expansion method in restraint structural component based on laser shock peening
  • Crack initiation and expansion method in restraint structural component based on laser shock peening

Examples

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Effect test

Embodiment 1

[0061] Specimen material (i.e. structural parts, such as Figure 3A , 3B Shown): 6082 aluminum alloy standard tension-compression fatigue specimen with a length of 55mm and a thickness of 3mm, with a 0.1mm-long scratch damage;

[0062] Before the strengthened surface of the structural part is covered with the absorbent layer, the structural part is placed in an ultrasonic cleaning machine with deionized water at a temperature of 22 ° C, and the ultrasonic frequency is 38 kHz, and cleaned for 15-20 minutes; Dry, and then put it in a drying oven at 70°C for 20 minutes.

[0063] Cover a layer of 120μm black tape on the surface of the titanium alloy structure, and then apply a 2mm deionized water confinement layer on the surface of the black tape. Pre-shock strengthening treatment: pulse width 12ns, wavelength 532nm, laser energy 5J, a laser beam with a repetition frequency of 2 Hz and a beam diameter of 2 mm is subjected to pre-shock strengthening treatment, where the overlap r...

Embodiment 2

[0066] Specimen material: 6082 aluminum alloy standard tension-compression fatigue specimen with a length of 55mm and a thickness of 3mm, with a notch damage of 0.05×0.05×0.05mm;

[0067] Before the strengthened surface of the structural parts is covered with the absorbent layer, put the structural parts into an ultrasonic cleaning machine with deionized water at a temperature of 24°C and an ultrasonic frequency of 47kHz for 20 minutes; Dry in a drying oven at 70°C for 20 min.

[0068] Cover a layer of 120μm black tape on the surface of the titanium alloy structure, and then apply a 2mm deionized water confinement layer on the surface of the black tape. Pre-shock strengthening treatment: pulse width 12ns, wavelength 532nm, laser energy 5J, a laser beam with a repetition frequency of 2 Hz and a beam diameter of 2 mm is subjected to pre-shock strengthening treatment, where the overlap rate is 30%, and the impact is 1 time. Then, a laser beam with a pulse width of 12 ns, a wavel...

Embodiment 3

[0071] Specimen material: 6082 aluminum alloy standard tension-compression fatigue specimen with a length of 55mm and a thickness of 3mm, pit corrosion with a diameter of 0.09mm and a depth of 1mm;

[0072] Before the strengthened surface of the structural parts is covered with the absorbent layer, put the structural parts into an ultrasonic cleaning machine with deionized water at a temperature of 24°C and an ultrasonic frequency of 47kHz for 20 minutes; Dry in a drying oven at 70°C for 20 min.

[0073] Cover a layer of 120μm black tape on the surface of the titanium alloy structure, and then apply a 2mm deionized water confinement layer on the surface of the black tape. Pre-shock strengthening treatment: pulse width 12ns, wavelength 532nm, laser energy 5.5J, a laser beam with a repetition rate of 2 Hz and a beam diameter of 2 mm is subjected to pre-shock strengthening treatment, and the overlap rate is 30%, and the impact is 1 time. Then, a laser beam with a pulse width of ...

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Abstract

The invention relates to a crack initiation and expansion method in a restraint structural component based on laser shock peening. The crack initiation and expansion method comprises the following steps that pretreatment is carried out on the structural component with a damage spot; the damage spot of the structural component is subjected to surface enhancing and is covered with an absorption layer; a restraint layer is applied to the structural component covered with the absorption layer; shock peening pretreatment is carried out on the structural component; shock peening treatment is carried out on the structural component; aftertreatment is carried out on the peened structural component; and according to shock peening treatment on the structural component, a laser beam with the pulse width of 8-20 ns, wavelength of 535-1,064 nm, laser energy of 7-15 J, repeated frequency of 1-2 Hz and beam diameter of 0.5-3 mm is used for shock life-extension treatment. According to the method, scratches and gap cracks formed on the metal structural component are reduced, and extension of cracks is restrained and slows down; micro crack initiation of the damage spot of the structural component is effectively avoided; and the metallographic structure or shape of a damage area is not changed, and no machining is needed.

Description

technical field [0001] The invention relates to a repair technology for metal structural parts, in particular to a method for suppressing crack initiation and propagation in structural parts based on laser shock strengthening. Background technique [0002] With the development of modern industry, components are required to work continuously under high temperature, high pressure, high speed, alternating stress load and acid corrosive medium or dust environment, so the surface performance requirements of mechanical product structural parts are getting higher and higher. By improving the surface properties of materials or repairing worn or partially damaged parts in time, the service life of structural parts can be effectively extended, which is more and more favored by researchers. Today, when repairing cracks, scratches or gaps in metal structural parts, there are mainly two forms according to the healing method: material supply and energy supply. From the cracks of common me...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C21D1/09
CPCC21D1/09
Inventor 高宇乔红超张恭轩李伟剑陈亚莉
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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