用无损损伤指标评价Inconel 718损伤程度

Q4 Engineering
J. Krysztofik
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引用次数: 1

摘要

摘要本文介绍了静力拉伸试验和蠕变试验中累积塑性应变损伤程度的定量评价结果。为了检测材料结构的变化,为了确定材料的降解,使用了非破坏性的方法,即超声波和涡流法。在超声检测中,以衰减和声双折射作为损伤指标。在涡流法的情况下,观察到材料中阻抗相角的变化。试验材料为因康乃尔718合金。铬镍铁合金经常被发现在极端的工作条件下的应用,包括在电力工程工业,航空和航天。试验采用了一种新型试样,其测量部分的截面积是可变的。这使得研究人员能够获得塑性应变的连续分布,并能够对材料进行不同损伤程度的分析。确定了以变形量表示的损伤程度与无损指标值之间的相关性。在此基础上,得到了表明材料在超过屈服极限载荷作用下的降解程度无损评价能力的依赖关系。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Evaluation of Damage Degree of Inconel 718 using Nondestructive Indicators of Damage
Abstract This paper presents the results of the quantitative evaluation of the degree of damage caused by plastic strain accumulated in static tensile tests and creep tests. To detect changes in the structure of the material and in order to determine the degradation of the materials, nondestructive methods were used, namely the ultrasonic and eddy current methods. In ultrasonic testing, attenuation and acoustic birefringence were used as damage indicators. In the case of the eddy current method, changes in the phase angle of impedance were observed in the material. The material tested was Inconel 718 alloy. Inconel alloys are often find application in extreme working conditions including in the power engineering industry, aviation and aerospace. A new type of specimen with the variable cross-sectional area of the measuring part was used in the tests. This allowed researchers to obtain a continuous distribution of plastic strain and enabled analysis of the material with respect to different damage degrees. The correlation between the degree of damage, expressed by the measure of deformation, and the value of nondestructive indicators was determined. On the basis of it, the dependence indicating the ability to nondestructive evaluation of the degradation degree of the material, subjected to loads exceeding the yield limit was obtained.
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来源期刊
Fatigue of Aircraft Structures
Fatigue of Aircraft Structures Engineering-Safety, Risk, Reliability and Quality
CiteScore
0.40
自引率
0.00%
发文量
0
期刊介绍: The publication focuses on problems of aeronautical fatigue and structural integrity. The preferred topics include: full-scale fatigue testing of aircraft and aircraft structural components, fatigue of materials and structures, advanced materials and innovative structural concepts, damage tolerant design of aircraft structure, life extension and management of ageing fleets, structural health monitoring and loads, fatigue crack growth and life prediction methods, NDT inspections, airworthiness considerations.
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