Method and device for rapidly predicting crack propagation life of laser shock peening component
A technology of laser shock strengthening and crack extension life, applied in design optimization/simulation, instrumentation, computer-aided design, etc., can solve the problems of low practicability and low accuracy of fatigue life prediction
Active Publication Date: 2021-06-04
AVIC BEIJING AERONAUTICAL MFG TECH RES INST
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[0006] The embodiment of the present invention provides a method and device for rapidly predicting the crack growth life of a laser shock strengthened component. Through experimental verification, finite element numerical simulation and theoretical derivation, the correlation between laser shock strengthening process parameters and fatigue life is established, and the obtained results from laser shock The rapid integrated detection of parameters to fatigue life solves the existing technical problems of low accuracy and low practicability of fatigue life prediction, and fills the technical gap of crack growth life prediction of laser shock strengthened components
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[0056] Embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings and examples. The detailed description and accompanying drawings of the following embodiments are used to illustrate the principles of the present invention, but cannot be used to limit the scope of the present invention, that is, the present invention is not limited to the described embodiments, without departing from the spirit of the present invention Any modification, substitution and improvement of parts, components and connection methods are covered under.
[0057] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.
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The embodiment of the invention provides a method and device for rapidly predicting the crack propagation life of a laser shock peening component, and the method comprises the steps: carrying out a laser shock peening test on a target component through employing preset laser parameters, and obtaining a residual stress depth distribution result; then, carrying out simulation in a finite element numerical simulation environment according to the obtained residual stress depth distribution result, determining external loads according to laser parameters, and according to the theoretical derivation relation between the external loads and the crack strength factor value, the crack strength factor range and the fatigue life, and finally, obtaining rapid integrated prediction from the laser shock parameter to the fatigue life. The technical defects are finally solved, and the technical blank of crack propagation life prediction of the laser shock reinforced component is filled.
Description
technical field [0001] The invention relates to the field of anti-fatigue manufacturing technology, in particular to a method and device for rapidly predicting the crack propagation life of a laser shock strengthened component. Background technique [0002] Anti-fatigue manufacturing refers to the manufacturing technology that improves the fatigue life of parts by changing the microstructure and stress distribution state of the material during the manufacturing process without changing the material and size of the parts. As an advanced high-energy beam surface modification and anti-fatigue manufacturing technology, laser shock peening uses intense pulsed laser bombardment on the surface of metal materials covered with absorbing layers and confinement layers to generate high-temperature, high-pressure plasma shock waves that transmit to the interior of the material, and are combined with The rapid, non-equilibrium, and violent interaction of the material induces high-amplitud...
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IPC IPC(8): G06F30/23C21D10/00G06F111/04G06F119/02G06F119/08G06F119/14
CPCG06F30/23C21D10/005G06F2119/02G06F2119/14G06F2111/04G06F2119/08Y02P10/20
Inventor 孙汝剑曹子文车志刚邹世坤吴俊峰
Owner AVIC BEIJING AERONAUTICAL MFG TECH RES INST