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Article(id=1246028559244968944, tenantId=1146029695717560320, journalId=1241755870837649424, issueId=1246028557319783390, articleNumber=null, orderNo=null, doi=10.19636/j.cnki.cjsm42-1250/o3.2024.008, pmid=null, cstr=null, oa=null, hot=null, price=null, onlineType=0, articleFormat=0, articleType=null, articleTypeStr=null, receivedDate=1708272000000, receivedDateStr=2024-02-19, revisedDate=null, revisedDateStr=null, acceptedDate=null, acceptedDateStr=null, onlineDate=1775005958615, onlineDateStr=2026-04-01, pubDate=1719244800000, pubDateStr=2024-06-25, doiRegisterDate=null, doiRegisterDateStr=null, onlineIssueDate=1775005958615, onlineIssueDateStr=2026-04-01, onlineJustAcceptDate=null, onlineJustAcceptDateStr=null, onlineFirstDate=null, onlineFirstDateStr=null, sourceXml=null, magXml=null, createTime=1775005958615, creator=13701087609, updateTime=1775005958615, updator=13701087609, issue=Issue{id=1246028557319783390, tenantId=1146029695717560320, journalId=1241755870837649424, year='2024', volume='45', issue='3', pageStart='289', pageEnd='426', issueExtLink='null', onlineDate='null', pubDate='null', beforeIssueId=null, nextIssueId=null, price=null, status=1, issueComplete=1, articleOrder=1, issueType=-1, specialIssue=null, createTime=1775005958156, creator=13701087609, updateTime=1775006058227, updator=13701087609, preIssue=null, nextIssue=null, ext={EN=IssueExt(id=1246028977123471371, tenantId=1146029695717560320, journalId=1241755870837649424, issueId=1246028557319783390, language=EN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=), CN=IssueExt(id=1246028977123471372, tenantId=1146029695717560320, journalId=1241755870837649424, issueId=1246028557319783390, language=CN, specialIssueTitle=, coverIllustrator=null, specialIssueEditor=, specialIssueAbout=)}, issueFiles=null}, startPage=392, endPage=400, ext={EN=ArticleExt(id=1246028559450489846, articleId=1246028559244968944, tenantId=1146029695717560320, journalId=1241755870837649424, language=EN, title=Design of Ultrasonic Fatigue Sample with Planar Section and Experimental Verification through Fatigue Life Testing, columnId=1244229834482757770, journalTitle=Chinese Journal of Solid Mechanics, columnName=Research Paper, runingTitle=null, highlight=null, articleAbstract=

Ultrasonic resonance technology is the most effective method for studying the ultra-high-cycle fatigue properties of metallic materials. Ultrasonic fatigue specimens typically need a distinctive geometric design to fulfill the resonance requirements. Conventional specimens, such as round rods and dog bones, do not have planar characteristics, making quantitative microscopic characterization difficult. This paper presents an ultra-high-cycle tensile fatigue specimen with a featured plane based on a traditional dog-bone tension-compression specimen design. Different from the traditional specimen design, the dog-bone specimen herein has a flat observation area, readily enabling quantitative microscopic characterization. Using GH4169 nickel-based alloy as an example, the proposed plane-featured dog-bone fatigue specimen design is validated. As expected, the ultrasonic fatigue test results show that the proposed dog-bone plane specimen can resonate at 20 kHz. The measured fatigue life data are basically consistent with available S-N results in the literature. The proposed method provides new ideas for the design of ultrasonic cycle fatigue specimens and helps in the study of micro-deformation mechanisms of ultra-high-cycle fatigue.

, correspAuthors=Zhen Zhang, authorNote=null, correspAuthorsNote=null, copyrightStatement=null, copyrightOwner=null, extLink=null, articleAbsUrl=null, sourceXml=null, magXml=null, pdfUrl=null, pdf=null, pdfFileSize=null, pdfExtLink=null, richHtmlUrl=null, mobilePdfUrl=null, reviewReport=null, pdfFirstPage=null, abstractGraph=null, abstractGraphContent=null, abstractVideo=null, citation=null, cebUrl=null, magXmlContent=null, mapNumber=null, authorCompany=null, fund=null, authors=null, authorsList=Lili Shu, Yuegang Li, Qiangang Xu, Zhen Zhang), CN=ArticleExt(id=1246028563716096170, articleId=1246028559244968944, tenantId=1146029695717560320, journalId=1241755870837649424, language=CN, title=超声疲劳狗骨平面试样设计与疲劳寿命实验研究, columnId=1241831201896469478, journalTitle=固体力学学报, columnName=研究论文, runingTitle=null, highlight=null, articleAbstract=

超声谐振技术是研究金属材料超高周长寿命疲劳性能的有效手段之一. 超声疲劳试样通常需要独特的几何设计以满足共振的要求. 常规疲劳试样如圆棒以及狗骨等不具备平面特征，在定量微观表征等方面存在困难. 本文介绍了一种基于狗骨型拉压疲劳试样的带平面超声拉伸疲劳试样及其设计方法、疲劳测试方法. 与传统超声疲劳试样设计不同的是，本文的狗骨平面试样具备平面试验段，具有利于定量微观表征的特征. 本文以GH4169镍基合金为例，开展狗骨平面疲劳试样设计. 通过超声疲劳试验结果表明，本文提出的基于理论解和数值方法的狗骨平面试件能在20 kHz产生共振，并且测得应力数据基本与现有材料S-N曲线相符. 本文方法为超声疲劳试样设计与超高周疲劳的微观变形机制研究提供了新思路.

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** E-mail：.
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超声疲劳狗骨平面试样设计与疲劳寿命实验研究
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舒力力 1 , 李岳刚 1 , 徐乾罡 1 , 张桢 1, 2, **
固体力学学报 | 研究论文 2024,45(3): 392-400
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固体力学学报 | 研究论文 2024, 45(3): 392-400
超声疲劳狗骨平面试样设计与疲劳寿命实验研究
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舒力力1, 李岳刚1, 徐乾罡1, 张桢1, 2, **
作者信息
  • 1华中科技大学航空航天学院，工程力学系，武汉，430074
  • 2华中科技大学工程结构分析与安全评定湖北省重点实验室，武汉，430074

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** E-mail：.
Design of Ultrasonic Fatigue Sample with Planar Section and Experimental Verification through Fatigue Life Testing
Lili Shu1, Yuegang Li1, Qiangang Xu1, Zhen Zhang1, 2, **
Affiliations
  • 1Department of Engineering Mechanics, School of Aerospace Engineering, Huazhong University of Science and Technology, Wuhan, 430074
  • 2Hubei Key Laboratory of Engineering Structure Analysis and Safety Assessment, Huazhong University of Science and Technology, Wuhan, 430074
出版时间: 2024-06-25 doi: 10.19636/j.cnki.cjsm42-1250/o3.2024.008
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摘要
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超声谐振技术是研究金属材料超高周长寿命疲劳性能的有效手段之一. 超声疲劳试样通常需要独特的几何设计以满足共振的要求. 常规疲劳试样如圆棒以及狗骨等不具备平面特征，在定量微观表征等方面存在困难. 本文介绍了一种基于狗骨型拉压疲劳试样的带平面超声拉伸疲劳试样及其设计方法、疲劳测试方法. 与传统超声疲劳试样设计不同的是，本文的狗骨平面试样具备平面试验段，具有利于定量微观表征的特征. 本文以GH4169镍基合金为例，开展狗骨平面疲劳试样设计. 通过超声疲劳试验结果表明，本文提出的基于理论解和数值方法的狗骨平面试件能在20 kHz产生共振，并且测得应力数据基本与现有材料S-N曲线相符. 本文方法为超声疲劳试样设计与超高周疲劳的微观变形机制研究提供了新思路.

超高周疲劳  /  超声振动  /  狗骨  /  平面试样

Ultrasonic resonance technology is the most effective method for studying the ultra-high-cycle fatigue properties of metallic materials. Ultrasonic fatigue specimens typically need a distinctive geometric design to fulfill the resonance requirements. Conventional specimens, such as round rods and dog bones, do not have planar characteristics, making quantitative microscopic characterization difficult. This paper presents an ultra-high-cycle tensile fatigue specimen with a featured plane based on a traditional dog-bone tension-compression specimen design. Different from the traditional specimen design, the dog-bone specimen herein has a flat observation area, readily enabling quantitative microscopic characterization. Using GH4169 nickel-based alloy as an example, the proposed plane-featured dog-bone fatigue specimen design is validated. As expected, the ultrasonic fatigue test results show that the proposed dog-bone plane specimen can resonate at 20 kHz. The measured fatigue life data are basically consistent with available S-N results in the literature. The proposed method provides new ideas for the design of ultrasonic cycle fatigue specimens and helps in the study of micro-deformation mechanisms of ultra-high-cycle fatigue.

ultra-high-cycle fatigue  /  ultrasonic vibration  /  dog bone  /  planar sample
舒力力, 李岳刚, 徐乾罡, 张桢. 超声疲劳狗骨平面试样设计与疲劳寿命实验研究. 固体力学学报, 2024 , 45 (3) : 392 -400 . DOI: 10.19636/j.cnki.cjsm42-1250/o3.2024.008
Lili Shu, Yuegang Li, Qiangang Xu, Zhen Zhang. Design of Ultrasonic Fatigue Sample with Planar Section and Experimental Verification through Fatigue Life Testing[J]. Chinese Journal of Solid Mechanics, 2024 , 45 (3) : 392 -400 . DOI: 10.19636/j.cnki.cjsm42-1250/o3.2024.008
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0　引言
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随着对航空发动机服役性能要求的日益提升，发动机安全可靠性标准和服役寿命需求也越来越高. 发动机叶片、叶盘等关键部件在工作时会承受高频气动荷载，对疲劳寿命的要求会超过109次循环[1]. 所以，关于高温镍基合金GH4169等发动机典型材料的超高周疲劳性能研究是发动机长寿命设计不可或缺的. 为了保证发动机的运营安全，除了在理论上要确保关键部件的疲劳寿命满足设计要求，还需要对典型发动机材料进行超高周疲劳测试，排除可能发生的疲劳失效故障. 利用超声波加载的方法是开展超高周疲劳试验研究极具竞争力的方法之一. 完成109次循环加载，传统的100 Hz疲劳试验机需要115天，1000 Hz的电磁振动系统需要11天，而20 kHz频率的超声振动试验系统仅需不到14小时. 利用超声振动的方式大大缩短了超高周疲劳试验研究的测试周期.
超声波加载最早在20世纪初被用于疲劳实验，这些研究工作为现代超声疲劳试验技术的发展奠定了理论基础. Mason等[2]利用压电陶瓷材料电致伸缩的原理，采用超声波谐振技术研制了超声疲劳试验系统，使疲劳试验加载频率达到15～22 kHz，为材料疲劳损伤与长寿命疲劳性能的研究提供了新试验方法. Neppiras等[3]将超声疲劳试验技术应用于材料疲劳寿命S-N曲线的测定，在对称循环载荷下开展了材料疲劳寿命和疲劳极限的研究. Mitsche等[4]对超声疲劳中的裂纹扩展问题进行了研究，得到材料裂纹扩展的da/dN-ΔK曲线. 近几十年来，随着超声疲劳试验技术的进一步发展，该技术已逐渐成为一种可靠的试验方法，为确定材料超高周疲劳强度提供了更高效的解决方案，其应用领域也越来越广阔.
超声疲劳试验系统如图1所示，该系统能以20 kHz频率进行超声振动实验. 由于超声疲劳试验机是利用超声振动激励的方式使试样产生共振，所以超声疲劳测试试样设计需要满足共振条件[5]. 试样在振动过程中的位移、应变和应力分布是由试样的几何形状决定的固有特性. 因此，相对于其他材料力学实验而言，试样的设计很大程度上决定着超高周疲劳试验的有效性. 目前，国内外针对超声疲劳试验试样设计的研究成果丰富[6,7]. 通过对目前超声疲劳试样的统计发现，超声疲劳试样类型主要集中于沙漏型试样、狗骨型试样、薄板试样. 其中，沙漏型试样的应变随其形状和尺寸的变化非常明显，应变在圆弧变截面上快速下降，仅在试样最中间的位置达到最大应力，研究人员难以结合沙漏试样开展微观疲劳变形的研究. 狗骨型试样的应变ε在试验体积内变化很小，几乎都处于最大应力状态，但从试验段过渡到圆弧变截面段时应变变化显著. 这会提高裂纹由此位置萌生的可能性. 由于形状限制，对圆柱形试样进行裂纹扩展速率观测很困难. 因此利用板状试样进行超高周疲劳裂纹扩展试验可行性较高. 在板状试样中，更容易使用应变片测量试验应力的大小，也可以更有效地观测并测量裂纹扩展速率. 但是板状试样的位移放大系数相对较小，限制了试验的应力水平，同时由于超高周疲劳失效会在夹杂物附近存在一个圆形区域，在板状试件中，无法通过花纹特征判定裂纹的走向[8]. 近年来，微观定量表征方法如扫描电镜（SEM）及电子背散射衍射分析（EBSD）在超高周疲劳失效研究中应用广泛. 其中，EBSD是入射电子束与样品表层区发生作用，而形成高角菊池花样. 所以，EBSD样品检测时需要倾转70°，通过减小背散射电子射出表面的路径以获取足够强的背散射衍射信号. 为了确保使电子背散射衍射强度足够大，检测面法线和入射电子束之间的夹角要保持约为70°. EBSD检测的样品需要保持平面. 而且对试样表面微观表征时，EBSD试样需要抛光处理去除表面氧化层和残余应力层，曲面无法抛光[9]. 另外，采用微观数字图像相关技术等其他表征方法，曲面试件无法有效地成像. 因此，上述传统超声疲劳试件可用于完成材料常规的超高周疲劳性能及寿命测试，但是由于不具备平面试验段，难以进行微观定量表征从而对于超高周微观变形机制进行有效研究.
针对现有超声试件设计的不足，本文提出了一种带有平面试验段的超声拉伸疲劳试样设计方法，其目的在于使试样能够在超声疲劳试验机上发生谐振，并有助于定量表征材料微观变形特性和疲劳失效机理. 同时，为了验证提出的疲劳试件设计方法的有效性，本文针对典型航空发动机材料镍基高温合金GH4169开展超高周疲劳试验.
1　超声疲劳试样的设计
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1.1　传统狗骨型试样
在拉压循环荷载作用下，为了使试样中部产生应力集中从而加速试验进程，实际采用的超声疲劳试样通常为等截面圆弧状的狗骨型试样，如图2所示. 这样可以使试样的振幅放大超过10倍，并使其最大应力产生于试件中间横截面. 若试样中间部分为指数形式的曲线，则可以通过解析计算求出试样谐振长度[10]. 采用传统狗骨型试样可实现金属材料超声拉压疲劳性能测试. 因此，当试验条件或者材料发生变化时，超声疲劳试样只需要在尺寸上做出调整，即可开展对样品的疲劳试验. 相比于板状试样，狗骨试样具有更大的应力位移系数. 这意味着通过较小的振幅变化能实现较大的测试应力范围. 另外，狗骨试样外形简单便于加工，因此应用更加广泛，但传统的狗骨状试样为圆弧曲面，无法有效地描述典型微观疲劳特征，如材料组织形貌，晶体结构和取向等，难以准确地通过显微技术表征材料微观疲劳失效机理.
1.2　带平面试验段的超声拉压疲劳试样
本文提出了带平面试验段的超声疲劳试样的设计方法，基本的设计步骤如下：首先，根据解析解初步设计出等截面的传统狗骨型试样. 狗骨试样的设计频率f可定为能够使其在超声疲劳试验机上发生谐振的频率. 其次，为了使传统狗骨试件具有可用于微观表征的平面试验段，本文在传统狗骨状试样的中间试验区段切出带倾斜侧面的U型槽，经切割后的试验区段不再是圆形等截面的结构. 在传统超声试件设计方法中，试样的试验区段须保持为等截面才能够保证刚度分布均匀并获得较好的测试数据. 因此，无论是板状试样还是狗骨状试样，中间的试验区段均设计为等截面. 本文提出的平面试样设计方法与常规设计思路不同的是，在狗骨型试样的圆形截面试验区段切出U型槽，虽然经切割后的试验区段不再是圆形等截面结构，但是本文控制切割尺寸在较小的范围内，经有限元验证分析发现切割对试验区段刚度的影响较小，在可控范围内，不计. 最后，通过有限元分析新的平面试样的轴向模态固有频率，并反馈微调谐振长度，使新的带平面实验段的试样的固有频率再次逼近设计频率f，从而使得新的狗骨平面试样能够在～20 kHz频率下发生谐振.
1.2.1　狗骨试样解析解
初步设计的试样为呈中心对称结构且固有频率逼近设计频率f的狗骨型试样，形貌参考传统的狗骨型试样. 狗骨型试样中间位置为圆柱形的试验区段、两侧分别为圆柱形的谐振区段，试验区段和谐振区段之间通过变截面段过渡连接，试验区段的横截面半径R1小于谐振区段的横截面半径R2.
首先，本文根据已有的狗骨试样设计的解析解方法进行试样的初步设计[8]. 根据弹性体中波的传播理论，材料满足理想弹性条件，在一维振动状态下，假定坐标原点为试样轴向中心，取试样轴向为x轴，则试样的纵波方程为：
其中，，ρ为材料密度；x为沿轴向的位移；t为时间；S（x）为x处的截面面积；u（x，t）为试样轴向x处t时刻的纵向位移；f（x，t）为作用在x截面上的力；Ed为材料的动态弹性模量. 若试验满足疲劳试验机超声振动的谐振条件，可将u（x，t）设为：
其中，U（x）为试样振幅，ω为试样振动的角频率，则式（1）可化简为：
其中，令p（x）=S′（x）/S（x），弹性波在材料中的传播速度，k=ω/c. 在下面的计算中，令U0（x），U1（x），U2（x）分别为试样试验区段、变截面段、谐振区段的振幅，，，分别为试样试验区段、变截面段、谐振区段应变.
由于试样是对称的，可以只计算右半部分，试样右半部分沿轴向各截面的面积分布可表示为：
其中为了能够得到解析解，在计算时变截面段以悬链线代替圆弧进行计算，其误差能控制在3%以内，悬链线参数α=cosh-1（R2/R1）/L1，在试样设计时圆弧半径满足，右半边试样总长L=L0+L1+L2.
将式（5）带入波动方程，并结合超声疲劳试样共振的边界条件，假设试样最大振幅为A0，则可以解得试样的应变分布函数：
其中，令β=（α2-k2）0.5，Fs为待定系数，表示试样应力位移系数. 由此可解得狗骨型试样谐振长度L2公式及应力放大系数Fs：
综上，狗骨型试样试验区段的长度2L0和横截面半径R1、各变截面段的长度L1和圆弧半径R0、各谐振区段的横截面半径R2和谐振长度L2、预期的设计频率f，谐振长度L2需满足式（7）.
1.2.2　狗骨平面试样设计
在初步设计出等截面狗骨型试样的具体尺寸后，为了满足微观定量表征的需求，在狗骨试样试验段设计平面[9]，已有部分学者在沙漏型试样的基础上，设计平面沙漏试样[11]，但该试样不具备狗骨试样应力位移系数较大的优点. 考虑所需平面段的大小，在试验区段的两侧分别向内相向切出U型槽，形成图3所示的带平面试样，其中，图3（a）和（b）为斜切面过渡和圆弧过渡狗骨平面试样的设计图，图3（c）为狗骨平面试样（a）和（b）的俯视图. 如图3所示，其倾斜侧面为呈θ角的倾斜平面. 由于几何形状突变会引起应力集中，所以转折处将采取圆弧过渡. 如图3（b）所示，其倾斜侧面为开口处切线呈θ角、半径为R3的弧形侧面. 如图3（c）所示，U型槽的底面为与XY平面平行的长为a，宽为b观测平面、侧面为开口处切线呈θ角的倾斜侧面. 为了降低凹槽对试样性能的影响，同时使试样能够正常用于疲劳测试及微观表征测试，对凹槽的切割尺寸进行了限定，限定U型槽的底面面积与试验区段纵截面面积之比处于[3/10，6/10]的范围内，切角θ的范围为[10°，30°]，切深h范围为[R1/6，R1/3]，以使平面的大小应适中，保证试验区段刚度变化较小，平面面积较大便于观测. 当然也可以根据试验需要，这里的尺寸调节也可采用其他尺寸，只要保证最终能够发生共振即可.
考虑到狗骨平面试件由于几何突变可能产生应力集中问题，可根据实际需要在上述基础上，在试样的侧面设计圆弧切面并增大平面面积. 通过较小的截面面积变化，以实现试验段存在应变的小梯度变化，从而使最大应力位置处于试样中部. 改进后的狗骨平面侧切圆弧试样如图4所示，所以，侧向圆弧切面可以将超高周疲劳裂纹的萌生位置控制在中部附近.
本文基于传统狗骨试件理论解的设计方法，在狗骨平面试样设计过程中，利用有限元方法分析获取狗骨平面试样的轴向固有频率f1. 然后，根据轴向固有频率f1对新试件的谐振长度进行修正，以使狗骨平面试样的轴向固有频率f1逼近设计频率f. 值得注意的是，本文设计步骤中对原始传统狗骨型试样进行了局部切割，导致试样尺寸和形貌均有所变动，所得到的狗骨平面试样的固有频率有所变化. 由于局部形状复杂，单独使用解析解的设计方法不再适用. 而且，相对于单独使用有限元方法进行试算设计，解析解结合有限元方法显著提高了新试件的设计效率. 初始的解析解设计方法建立了试件的大致尺寸. 进一步的有限元设计方法对试样谐振长度L2进行修正，以使固有频率逼近设计频率f，以满足与超声疲劳试验机共振的条件.
2　带平面超声拉伸疲劳试样设计实例及试验
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考虑到镍基高温合金GH4169作为发动机涡轮盘和叶片的典型材料，其超高周疲劳性能研究具有较高的理论价值和实际工程意义. 本小节基于GH4169介绍狗骨平面的超声疲劳试样的设计方法. 基于该套设计方法，设计人员在确定几何尺寸之后加工新试样，并采用超声疲劳试验机进行超高周疲劳测试，以验证本文设计的有效性. 值得注意的是，超高周试验可以将凹槽底面取为观测面，对试样进行微观定量表征，分析试样失效机理.
2.1　镍基合金平面试样设计流程
通过实验可确定镍基合金材料的动态弹性模量为Ed=199.9 GPa和密度为ρ=8240 kg/m3. 根据超声疲劳试验机的工作频率确定试样的设计频率f. 采用解析解的设计方法，初步设计的传统狗骨试样的固定频率能逼近设计频率f. 为了减小应力集中，可令变截面段圆弧与试验区段相切，几何形状光滑过渡，变截面段半径需满足：. 在本实例中，疲劳试验机的工作频率设为20 kHz，因此，本实例确定的试样设计频率也为f=20 kHz. 根据解析解设计方法初步设计出狗骨型试样的变截面段圆弧半径R0=15 mm、试验区段横截面半径R1=2 mm、谐振区段截面半径R2=5 mm、试验区段L0=5 mm、变截面段长度L1=9 mm，谐振长度L2通过上述步骤结合解析解和有限元分析得到L2=13.75 mm. 在试样试验区段以θ角度对称切出一块矩形的观测平面，其中b=6 mm，a=3.06 mm，过渡弧面半径R3为15 mm，并增加侧面圆弧切面，其半径R4=17.43 mm. 具体尺寸设计如图4所示，该狗骨平面试样为呈中心对称结构，且轴向振型对应的固有频率逼近设计频率f，满足[20 kHz-20 Hz，20 kHz+20 Hz]的范围，试样的应力位移系数比可以根据有限元分析试样轴向自由振动模态得到. 从而完成整个试样的设计. 本试样可通过增加端部螺孔或者连接螺杆，实现试样与试验机相连.
2.2　镍基合金平面试样超声疲劳试验
本文设计实例的GH4169超声疲劳试样如图4所示，尺寸能满足频率f=20 kHz±200 Hz的谐振条件. 通过有限元分析试样轴向自由振动的结果如图5所示，其固有频率为20 kHz. 通过试样最大应力和最大位移的比可以计算得到试样的应力位移系数比为27 GPa/μm，相同大小狗骨试样为19 GPa/μm. 超声试样端部通过螺栓与放大器固定，使得试样、螺栓与超声疲劳试验的杆件系统同轴. 在加载平均应力水平σm=0，应力比R=-1的情况下，本文在常温下开展了高周和超高周阶段的疲劳实验，考虑疲劳寿命在105到1010周次循环范围. 在疲劳实验的整个加载过程中，本文对GH4169试样通过压缩冷空气来冷却试样，以间歇加载方式测试，控制试件和测试系统使其温升较小，以减小温度变化对镍基高温合金的高周和超高周疲劳行为的影响.
如图6所示，本文最终得到GH4169的应力水平和疲劳寿命S-N曲线的试验数据[12,13]，应力幅σa的有效取值在超高周阶段介于330 MPa到390 MPa之间. 在107次循环附近，以应力幅σa表示的疲劳抗力显示出较大的分散性. 但所得到的样品疲劳强度试验结果与Yan[12]和Zhao等[13]文献中数据基本相符. 由此可见，本文设计方法是有效的，可操作性强.
试样断口分析如图7所示，试样加载应力幅值为370 MPa，得到最终疲劳寿命为3.602×107次循环. 从图中可以看出裂纹萌生于试样次表面的夹杂位置，扩展区能发现明显的疲劳条纹，瞬断区存在镍基合金典型的韧窝形貌，说明本文设计的试样断口形貌与传统试样无区别.
2.3　狗骨平面试样的优点
经实验验证，本文设计的狗骨平面试样不仅能够用于超声超高周疲劳测试，还呈现出以下优势：
（1）带平面试验段的试样，其应力放大系数进一步增大1.4倍，有利于后续进行超高周疲劳测试；
（2）使用狗骨平面的试样进行超声超高周拉压疲劳测试时，试样裂纹萌生位置可控，易形成于平面段中部；
（3）平面相比于圆弧表面而言，更便于对试样的组织形貌和晶体结构取向等微观表征进行定量分析.
3　总结
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本文建立了一种带有平滑观测面的超声疲劳试样设计方法，以及超高周疲劳实验测试技术和研究方法. 对于超声疲劳试样设计方法，本文基于一维弹性波理论推导了控制方程，并给出了传统狗骨试样的设计公式. 基于此，本文进一步利用有限元方法设计了狗骨平面试样. 最后本文的设计方法通过GH4169镍基高温合金超声疲劳实验得到了验证. 采用本文提出的狗骨平面试件测试得到的试验结果与现有的实验数据相比，趋势符合典型的超高周疲劳寿命S-N曲线特征. 试验检验表明本文设计方法便捷有效.
基金
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  • 国家科技重大专项(J2019-IV-0010-0078)
  • 国家自然科学基金项目(12172139)
文献
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2024年第45卷第3期
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doi: 10.19636/j.cnki.cjsm42-1250/o3.2024.008
  • 接收时间：2024-02-19
  • 首发时间：2026-04-01
  • 出版时间：2024-06-25
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  • 收稿日期：2024-02-19
基金
国家科技重大专项(J2019-IV-0010-0078)
国家自然科学基金项目(12172139)
作者信息
    1华中科技大学航空航天学院，工程力学系，武汉，430074
    2华中科技大学工程结构分析与安全评定湖北省重点实验室，武汉，430074

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