Method for predicting initiation location or expansion direction of cracks on metal surface

A technology of propagation direction and metal surface, applied in the field of predicting the crack initiation position or propagation direction of metal surface, which can solve the limited testing accuracy and experimental conditions of DIC equipment, cannot accurately characterize the behavior of small deformation in micro-area, and predict crack initiation and propagation. behavior and other issues, to achieve the effect of strong operability, wide range of use and wide applicability

Active Publication Date: 2020-01-17
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The amount of deformation in the micro-area of ​​metal materials is directly related to the crack initiation and propagation behavior. By establishing the relationship between crystal orientation and deformation distribution, it is helpful to reveal the failure mechanism and life prediction of metal materials. At present, DIC experiments are mostly used for the collection of full-field strain distribution on the surface of materials. However, limited by the test accuracy and experimental conditions of the DIC equipment, it is impossible to accurately characterize the small deformation behavior of the micro-area
[0004] With the urgent n

Method used

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  • Method for predicting initiation location or expansion direction of cracks on metal surface
  • Method for predicting initiation location or expansion direction of cracks on metal surface
  • Method for predicting initiation location or expansion direction of cracks on metal surface

Examples

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Embodiment 1

[0043] A method of predicting the location of crack initiation or the direction of propagation on a metal surface, such as figure 1 , 2 shown, prepared by the following steps:

[0044] 1) The cast titanium alloy fatigue crack growth sample is prepared by machining method, the surface of the sample is polished and corroded to show the microstructure morphology, cleaned with alcohol and then dried;

[0045] 2) Uniformly coat a layer of photoresist with a thickness of 0.5 μm on the surface of the titanium alloy by using the glue-spinning method (the rotation speed is 800 rpm), and then dry it. Cover the mask plate (single grid side length 20 μm) on the photoresist, use a photolithography machine to expose the mask plate and photoresist on the surface of the material for 60 seconds and then develop, forming a grid morphology on the surface of the titanium alloy;

[0046] 3) Put the titanium alloy in 2) in the electron beam evaporator, the parameters are: the vacuum degree of the e...

Embodiment 2

[0052] A method for predicting the micro-area fatigue crack initiation position of titanium alloy is obtained by measuring the grid deformation of titanium alloy surface micro-area, combined with the description of structure morphology, crystal orientation and slip line characteristics. Contains the following steps:

[0053] 1) Prepare the cast titanium alloy fatigue sample by machining method, polish and corrode the surface of the sample to show the microstructure morphology, clean it with alcohol and dry it;

[0054] 2) Uniformly coat a layer of photoresist with a thickness of 50 μm on the surface of the titanium alloy by using the glue-spinning method (3000 rpm), and then dry it. Cover the mask plate (single grid side length 20 μm) on the photoresist, use a photolithography machine to expose the mask plate and photoresist on the surface of the material for 600s and then develop, forming a grid morphology on the surface of the titanium alloy;

[0055] 3) Put the titanium al...

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Abstract

The invention relates to a method for predicting an initiation location or an expansion direction of cracks on a metal surface, and belongs to the technical field of mechanical behaviors of materials,and the method comprises the following steps of observing the microstructure after electrochemical polishing and corrosion on the surface of the metal material to be measured, and depositing a layerof metal in the physical vapor phase on the metal surface after exposure and development of the mask plate and photoresist on the metal surface by a photoengraving machine, so as to form a regular grid shape; using SEM-EBSD to characterize the crystal orientation of the material surface in the grid area to be measured; measuring the change of the relative coordinate values of grid node before andafter plastic deformation of the material surface, and accordingly calculating and analyzing the information such as the strain concentration distribution of the micro area, the strain concentration area and plastic deformation direction, and determining the dislocation slip direction of the material surface, so as to predict the initiation location and expansion direction of cracks on the metal surface. The invention realizes the method for predicting an initiation location or an expansion direction of cracks on a metal surface by the combination of a physical vapor deposition mesh method anda SEM-EBSD method.

Description

technical field [0001] The invention relates to a method for predicting the initiation position or extension direction of a metal surface crack, belonging to the technical field of material mechanical behavior. Background technique [0002] As the aviation industry has higher and higher requirements for long life and high reliability of the engine, the research on the failure behavior of the engine structural materials under the action of unidirectional or multidirectional static and alternating loads has also attracted more and more attention from researchers. General structural materials (polycrystalline materials, composite materials, thin film materials) are aggregated from characteristic structures with different shapes and randomly distributed orientations, and often exhibit isotropic uniformity in macroscopic mechanical properties. However, due to the different crystal structures, physical and mechanical properties of the characteristic structures of each composition,...

Claims

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Application Information

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IPC IPC(8): G01N3/00G01N3/06G01N1/28G01N1/32
CPCG01N3/00G01N3/06G01N1/28G01N1/286G01N1/32G01N2203/0064G01N2203/0066G01N2203/0075G01N2203/0641G01N2203/0682
Inventor 冯新莫晓飞丁贤飞朱郎平南海
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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