纳米压痕法测量航空发动机关键材料残余应力的研究进展

doi:10.11896/cldb.22100300

材料导报

2024, Vol. 38

Issue (11): 22100300-13 https://doi.org/10.11896/cldb.22100300

金属与金属基复合材料

纳米压痕法测量航空发动机关键材料残余应力的研究进展

罗军^1,2,3,4, 李楠^1,2,3,4, 王曦^1,2,3,4, 刘昌奎^1,2,3,4,*

1 中国航发北京航空材料研究院,北京 100095
2 航空工业失效分析中心,北京 100095
3 航空材料检测与评价北京市重点实验室,北京 100095
4 中国航空发动机集团材料检测与评价重点实验室,北京 100095

Research Progress of Nanoindentation Methods for Measuring Residual Stress in Critical Materials of Aero-engine

LUO Jun^1,2,3,4, LI Nan^1,2,3,4, WANG Xi^1,2,3,4, LIU Changkui^1,2,3,4,*

1 AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China
2 AVIC Failure Analysis Center, Beijing 100095, China
3 Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation, Beijing 100095, China
4 Key Laboratory of Aeronautical Materials Testing and Evaluation, Aero Engine Corporation of China, Beijing 100095, China

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摘要随着航空发动机的需求日益增加,人们对合金性能的要求也越来越高。在制造和加工过程中引入的残余拉应力会严重影响合金的力学性能,从而缩短发动机的服役寿命。因此,残余应力的测量对发动机的可靠性和安全性起着关键性作用。本文系统归纳了纳米压痕技术的测量原理,包括接触深度、接触刚度、接触面积、硬度以及弹性模量的计算,介绍了纳米压痕测量残余应力计算模型(如Suresh、Lee、Xu、Wang、Kim以及Peng等模型)的分析过程,对比了计算模型之间的优缺点,详细综述了纳米压痕理论在航空发动机关键材料(如不锈钢、铝合金、钛合金、镍基高温合金)残余应力测量中的最新研究进展,总结了残余应力计算模型存在的不足,同时展望了纳米压痕法测量残余应力的发展方向。

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关键词: 纳米压痕计算模型残余应力航空发动机关键材料

Abstract: With the increasing demand for aero-engine, higher requirements are put forward for the performance of engine alloys. The residual tensile stress introduced by manufacturing and machining seriously affects the mechanical properties of the alloy and shortens the service life of the aero-engine. Hence, the measurement of residual stress plays a key role in the reliability and safety of aero-engine. In this paper, the nanoindentation measurement of contact depth, contact stiffness, contact area, hardness and elastic modulus are systematically summarized. The analysis process of residual stress calculation model, such as Suresh, David, Lee, Xu, Wang, Kim and Peng models are introduced. Moreover, the advantages and disadvantages of the calculation models are compared. The latest research progress of nanoindentation theory in residual stress measurement in critical materials of aero-engine, such as stainless steel, aluminum alloy, titanium alloy and nickel-base superalloy are reviewed in detail. The shortcomings of residual stress calculation model are also summarized, and the development of nanoindentation method for measuring residual stress is prospected.

Key words: nanoindentation calculation model residual stress aero-engine critical material

发布日期: 2024-06-25

ZTFLH:

TG133

基金资助: 国家重点研发计划(2021YFA1600600)

通讯作者: *刘昌奎,博士,研究员,博士研究生导师。主要从事材料与结构的失效分析与预防、材料服役条件下的损伤行为、材料组织结构与性能和工艺的关系、材料微观物理表征与评价等方面的研究工作,以及装备重大质量问题及等级事故的调查与失效分析。负责和参与了大量航空重大质量问题和飞机等级事故的事故调查与失效分析工作,负责课题20多项,发表学术论文60余篇,主编或参编专(编)著、教材6部,获授权发明专利4项。changkuiliu621@163.com

作者简介: 罗军,2021年1月获得北京航空航天大学材料学专业博士学位,现为中国航发北京航空材料研究院工程师,在刘昌奎研究员的指导下进行博士后研究。主要从事航空发动机关键材料及构件的微观组织分析及残余应力表征技术等方面的研究,以第一作者在Journal of Materials Science & Technology、Materials & Design、Materials Science and Engineering A、Measurement等SCI期刊发表多篇论文。

引用本文:

罗军, 李楠, 王曦, 刘昌奎. 纳米压痕法测量航空发动机关键材料残余应力的研究进展[J]. 材料导报, 2024, 38(11): 22100300-13.
LUO Jun, LI Nan, WANG Xi, LIU Changkui. Research Progress of Nanoindentation Methods for Measuring Residual Stress in Critical Materials of Aero-engine. Materials Reports, 2024, 38(11): 22100300-13.

链接本文:

http://www.mater-rep.com/CN/10.11896/cldb.22100300 或 http://www.mater-rep.com/CN/Y2024/V38/I11/22100300

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