Titanium alloy fatigue life prediction method based on microscopic scratches

A technology of fatigue life and prediction method, which is applied in the direction of measuring device, using repeated force/pulsation force to test material strength, instruments, etc., to achieve the effect of simple method and convenient test

Inactive Publication Date: 2020-03-24
DALIAN UNIV OF TECH
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

However, existing Most of the applications are based on artificial surface gaps with large size, that is, visible to the naked eye

Method used

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  • Titanium alloy fatigue life prediction method based on microscopic scratches
  • Titanium alloy fatigue life prediction method based on microscopic scratches
  • Titanium alloy fatigue life prediction method based on microscopic scratches

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Embodiment Construction

[0031] The present invention will be further described below in conjunction with accompanying drawing and specific embodiment:

[0032] In the embodiment, the material is TC17 titanium alloy.

[0033] The method comprises the steps of:

[0034] Step 1: Use the ZYGO three-dimensional interferometer to observe the microscopic scratches on the surface of the sample, such as figure 1 As shown in a), it is determined that there is a scratch in the observation area.

[0035] Step 2: Determine the width W and depth D of the scratch.

[0036] Select three scratch sections with larger dimensions as measurement targets, namely section 1-1, 2-2, 3-3, see figure 1 a); Measure the width and depth data of the three sections respectively to obtain w 1 ,w 2 ,w 3 and d 1 , d 2 , d 3 ,See figure 1 b); then the width W and depth D of the scratch can be calculated by formula (1).

[0037] The Murakami theory defines the surface defect damage parameter as the square root of the area obt...

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Abstract

The invention discloses a titanium alloy fatigue life prediction method based on microscopic scratches, belongs to the technical field of metal material fatigue life prediction, and relates to the titanium alloy fatigue life prediction method based on the microscopic scratches. The prediction method is based on the Murakami theory, fatigue damage quantitative characterization parameters caused byevaluation of microscopic scratches are provided, and the fatigue damage quantitative characterization parameters are defined as the square root of the cross section triangle area of the microscopic scratches. The corresponding fatigue damage parameters can be obtained by measuring the depth and width data of the cross section of the microscopic scratch, and a titanium alloy fatigue life prediction model considering the influence of the microscopic scratch is established in combination with a Paris formula. According to the prediction model, the fatigue life of the titanium alloy under the microscopic scratches can be predicted only by measuring the depth and width data of the sections of the microscopic scratches. The method is a practical and novel method for evaluating the fatigue lifeof the titanium alloy blade considering the microscopic scratches, and is simple and convenient to test.

Description

technical field [0001] The invention belongs to the technical field of metal material fatigue life prediction, and relates to a titanium alloy fatigue life prediction method based on microscopic scratches. Background technique [0002] Titanium alloy has high specific strength, high toughness, good corrosion resistance and creep performance, and is an important material for manufacturing dual-performance blisks. The blisk is a key component of modern advanced aero-engines, and its blades bear huge and complex centrifugal and aerodynamic loads at high rotational speeds. Although the surface quality of titanium alloy blisk blades is strictly controlled in engineering manufacturing, there are still microscopic scratches at the micron level on the surface of the parts. These micromechanical scratches are usually caused by accidents or misoperations during the manufacturing, transportation and assembly of blades, and during service. Stress concentrations at the geometric discon...

Claims

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Application Information

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IPC IPC(8): G01N3/06G01N3/32
CPCG01N3/068G01N3/32
Inventor 张元良丁明超杨贺李泽新咸宏伟胡宁贾海生宫迎娇葛志鹏
Owner DALIAN UNIV OF TECH
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