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Article(id=1321927228158497543, tenantId=1146029695717560320, journalId=1220038251117760515, issueId=1321926982078681131, articleNumber=null, orderNo=null, doi=10.11868/j.issn.1001-4381.2024.000576, pmid=null, cstr=32421.14.j.issn.1001-4381.2024.000576, oa=null, hot=null, price=null, onlineType=0, articleFormat=0, articleType=null, articleTypeStr=research-article, receivedDate=1723478400000, receivedDateStr=2024-08-13, revisedDate=null, revisedDateStr=null, acceptedDate=1725292800000, acceptedDateStr=2024-09-03, onlineDate=1793101611412, onlineDateStr=2026-10-27, pubDate=1771516800000, pubDateStr=2026-02-20, doiRegisterDate=null, doiRegisterDateStr=null, onlineIssueDate=1793101611412, onlineIssueDateStr=2026-10-27, onlineJustAcceptDate=null, onlineJustAcceptDateStr=null, onlineFirstDate=null, onlineFirstDateStr=null, sourceXml=null, magXml=null, createTime=1793101611412, creator=13701087609, updateTime=1793101611412, updator=13701087609, issue=Issue{id=1321926982078681131, tenantId=1146029695717560320, journalId=1220038251117760515, year='2026', volume='54', issue='2', pageStart='1', pageEnd='311', issueExtLink='null', onlineDate='null', pubDate='1771516800000', pubDateStr='2026-02-20', beforeIssueId=null, nextIssueId=null, price=null, status=1, issueComplete=1, articleOrder=1, issueType=-1, specialIssue=null, createTime=1793101552742, creator='13701087609', updateTime=1793101552742, updator='13701087609', preIssue=null, nextIssue=null, articleTotal=null, ext=null, issueFiles=null, downloadFileDto=null}, startPage=234, endPage=241, ext={EN=ArticleExt(id=1321927228347241224, articleId=1321927228158497543, tenantId=1146029695717560320, journalId=1220038251117760515, language=EN, title=Influence of cyclic overheating on tensile strength and ductility of GH3230 alloy, columnId=1220689384450478826, journalTitle=Journal of Materials Engineering, columnName=RESEARCH ARTICLE, runingTitle=null, highlight=null, articleAbstract=

In light of the application scenarios where the combustion chamber and turbine components of aeroengines are repeatedly subjected to short-term overheating， and reusable spacecraft endure cyclic high-temperature conditions， an experimental study is conducted to investigate the effects of cyclic overheating on the tensile properties of GH3230 alloy. Additionally， the oxidation-related microstructural and compositional changes are characterized.The results reveal that the cracking of internal oxides during plastic deformation reduces the actual load-bearing area of the oxidized sample. Grain coarsening also occurs during thermal exposure. These two factors jointly contribute to a continuous decline in room-temperature tensile strength as the number of overheating cycles increases. After removing the surface layer， the tensile strength is restored to a certain degree. The oxidative decarburization zone that forms near the sample surfaces exhibits improved plastic deformability. As a result， it effectively blunts oxide cracks and prevents them from penetrating into the matrix. Consequently， the tensile elongation of the oxidized sample after 10-40 cycles of over-temperature remains at relatively high levels due to the avoidance of the notch effect caused by surface cracks.

, authors=Yawei ZHANG, Yu SHEN, Quan JU, Guohua XU, Ji ZHANG, authorsList=Yawei ZHANG, Yu SHEN, Quan JU, Guohua XU, Ji ZHANG, authorCompany=null, correspAuthors=Yawei 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, fund=null), CN=ArticleExt(id=1321927229928493849, articleId=1321927228158497543, tenantId=1146029695717560320, journalId=1220038251117760515, language=CN, title=循环超温对GH3230合金强度和塑性的影响, columnId=1220689384622445292, journalTitle=材料工程, columnName=研究论文, runingTitle=null, highlight=null, articleAbstract=

针对航空发动机燃烧室、涡轮部件均会多次出现短时超温以及可重复使用航天器循环高温的应用背景，实验研究了循环超温热暴露对GH3230合金拉伸性能的影响，并观察分析氧化后表面及内部成分、组织发生的变化。结果表明：表面和内氧化产物在塑性变形过程中的开裂减少了有效承载面积，超温热暴露中晶粒粗化，使得氧化试样室温抗拉强度随超温次数的增加而逐次降低，机加工去掉氧化层后抗拉强度得到一定程度的恢复；该合金表面层形成的碳化物回溶区具有良好的塑性变形能力，可有效阻止氧化物裂纹进入基体，避免产生缺口约束塑性变形效应，使氧化试样保持了较好的拉伸塑性，循环超温10~40次氧化试样的伸长率还略有提高。

, authors=张亚玮, 沈宇, 鞠泉, 胥国华, 张继, authorsList=张亚玮, 沈宇, 鞠泉, 胥国华, 张继, authorCompany=null, correspAuthors=张亚玮, authorNote=null, correspAuthorsNote=
张亚玮（1981—），女，高级工程师，博士，主要从事高温合金研究，联系地址：北京市海淀区气象路9号（100081），E-mail：
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Acta Materialia， 2016， 107： 424-483., articleTitle=Failure of metals Ⅰ： brittle and ductile fracture, refAbstract=null)], funds=null, companyList=[AuthorCompany(id=1321927230180152090, tenantId=1146029695717560320, journalId=1220038251117760515, articleId=1321927228158497543, xref=null, ext=[AuthorCompanyExt(id=1321927230192735003, tenantId=1146029695717560320, journalId=1220038251117760515, articleId=1321927228158497543, companyId=1321927230180152090, language=EN, country=null, province=null, city=null, postcode=null, companyName=null, departmentName=null, remark=Gaona Aero Material Co. ，Ltd. ，Beijing 100081，China), AuthorCompanyExt(id=1321927230201123612, tenantId=1146029695717560320, journalId=1220038251117760515, articleId=1321927228158497543, companyId=1321927230180152090, language=CN, country=null, province=null, city=null, postcode=null, companyName=null, departmentName=null, remark=北京钢研高纳科技股份有限公司，北京 100081)])], figs=[ArticleFig(id=1321927233674007359, tenantId=1146029695717560320, journalId=1220038251117760515, articleId=1321927228158497543, language=EN, label=Fig.1, caption=Geometry of tensile specimen, figureFileSmall=ZiVEXMumsPsHfmWDRjTZaQ==, figureFileBig=Jhs444Cgv/+UWkwFLCB8Yg==, tableContent=null), ArticleFig(id=1321927233745310528, tenantId=1146029695717560320, journalId=1220038251117760515, articleId=1321927228158497543, language=CN, label=图1, caption=室温拉伸试样尺寸图, figureFileSmall=ZiVEXMumsPsHfmWDRjTZaQ==, figureFileBig=Jhs444Cgv/+UWkwFLCB8Yg==, tableContent=null), ArticleFig(id=1321927233963414337, tenantId=1146029695717560320, journalId=1220038251117760515, articleId=1321927228158497543, language=EN, label=Fig.2, caption=Relationship between room-temperature tensile strength retention rate， plasticity change rate of GH3230 alloy， and cyclic oxidation cycles after overheating cycles （a）tensile strength retention rate；（b）plasticity change rate, figureFileSmall=35x2dt7IEwUqz6QCKzo4+w==, figureFileBig=CZOEd/O4joAemGwMSTPxwA==, tableContent=null), ArticleFig(id=1321927234173129538, tenantId=1146029695717560320, journalId=1220038251117760515, articleId=1321927228158497543, language=CN, label=图2, caption=GH3230合金循环超温后室温抗拉强度保持率及塑性变化率与循环氧化次数的关系

（a）抗拉强度保持率；（b）塑性变化率

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（a）solution-annealed state；（b）40 overheating cycles；（c）100 overheating cycles；（d）processed sample after 100 overheating cycles

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（a）固溶态；（b）40 次循环超温；（c）100 次循环超温；（d）100次循环超温后加工试样

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（a），（b）solution-annealed state；（c），（d）100 overheating cycles

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（a），（b）固溶态；（c），（d）100 次循环超温

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（a）before tensile test；（b）after tensile test

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（a）拉伸前；（b）拉伸后

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（a）solution-annealed state；（b）40 overheating cycles；（c）100 overheating cycles

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（a）固溶态；（b）40 次循环超温；（c）100 次循环超温

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Chemical composition analysis results of studied GH3230 alloy （mass fraction/%）

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MnSiAlCLaCrWMoFeCoNi
0.510.400.300.0790.02621.7714.221.330.311.51Bal.
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实验用GH3230合金成分检测结果（质量分数/%）

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MnSiAlCLaCrWMoFeCoNi
0.510.400.300.0790.02621.7714.221.330.311.51Bal.
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Quantitative test results by electron probe microanalysis at different positions in dissections of samples after 100 overheating cycles

, figureFileSmall=null, figureFileBig=null, tableContent=
PositionCrWMo
Point 121.015.470.99
Point 224.764.870.84
Point 326.794.850.84
Point 428.074.420.80
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100次循环超温试样剖面不同位置电子探针定量测试结果

, figureFileSmall=null, figureFileBig=null, tableContent=
PositionCrWMo
Point 121.015.470.99
Point 224.764.870.84
Point 326.794.850.84
Point 428.074.420.80
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Strengthening contribution of solid solution elements at different positions in dissections of samples after 100 overheating cycle

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PositionYield strength/MPa
Point 1303.7
Point 2300.6
Point 3305.0
Point 4300.5
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100次循环超温试样剖面不同位置固溶元素的强化贡献

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PositionYield strength/MPa
Point 1303.7
Point 2300.6
Point 3305.0
Point 4300.5
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循环超温对GH3230合金强度和塑性的影响
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张亚玮 , 沈宇 , 鞠泉 , 胥国华 , 张继
材料工程 | 研究论文 2026,54(2): 234-241
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材料工程 |研究论文 2026 , 54 (2) : 234 -241
循环超温对GH3230合金强度和塑性的影响
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张亚玮 , 沈宇, 鞠泉, 胥国华, 张继
作者信息
  • 北京钢研高纳科技股份有限公司，北京 100081
通讯作者:
张亚玮（1981—），女，高级工程师，博士，主要从事高温合金研究，联系地址：北京市海淀区气象路9号（100081），E-mail：
Influence of cyclic overheating on tensile strength and ductility of GH3230 alloy
Yawei ZHANG , Yu SHEN, Quan JU, Guohua XU, Ji ZHANG
Affiliations
  • Gaona Aero Material Co. ，Ltd. ，Beijing 100081，China
出版时间: 2026-02-20 doi: 10.11868/j.issn.1001-4381.2024.000576
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摘要
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针对航空发动机燃烧室、涡轮部件均会多次出现短时超温以及可重复使用航天器循环高温的应用背景，实验研究了循环超温热暴露对GH3230合金拉伸性能的影响，并观察分析氧化后表面及内部成分、组织发生的变化。结果表明：表面和内氧化产物在塑性变形过程中的开裂减少了有效承载面积，超温热暴露中晶粒粗化，使得氧化试样室温抗拉强度随超温次数的增加而逐次降低，机加工去掉氧化层后抗拉强度得到一定程度的恢复；该合金表面层形成的碳化物回溶区具有良好的塑性变形能力，可有效阻止氧化物裂纹进入基体，避免产生缺口约束塑性变形效应，使氧化试样保持了较好的拉伸塑性，循环超温10~40次氧化试样的伸长率还略有提高。

GH3230合金  /  超温热暴露  /  抗拉强度  /  拉伸塑性

In light of the application scenarios where the combustion chamber and turbine components of aeroengines are repeatedly subjected to short-term overheating， and reusable spacecraft endure cyclic high-temperature conditions， an experimental study is conducted to investigate the effects of cyclic overheating on the tensile properties of GH3230 alloy. Additionally， the oxidation-related microstructural and compositional changes are characterized.The results reveal that the cracking of internal oxides during plastic deformation reduces the actual load-bearing area of the oxidized sample. Grain coarsening also occurs during thermal exposure. These two factors jointly contribute to a continuous decline in room-temperature tensile strength as the number of overheating cycles increases. After removing the surface layer， the tensile strength is restored to a certain degree. The oxidative decarburization zone that forms near the sample surfaces exhibits improved plastic deformability. As a result， it effectively blunts oxide cracks and prevents them from penetrating into the matrix. Consequently， the tensile elongation of the oxidized sample after 10-40 cycles of over-temperature remains at relatively high levels due to the avoidance of the notch effect caused by surface cracks.

GH3230 alloy  /  cyclic overheating  /  tensile strength  /  tensile ductility
张亚玮, 沈宇, 鞠泉, 胥国华, 张继. 循环超温对GH3230合金强度和塑性的影响. 材料工程, 2026 , 54 (2) : 234 -241 . DOI: 10.11868/j.issn.1001-4381.2024.000576
Yawei ZHANG, Yu SHEN, Quan JU, Guohua XU, Ji ZHANG. Influence of cyclic overheating on tensile strength and ductility of GH3230 alloy[J]. Journal of Materials Engineering, 2026 , 54 (2) : 234 -241 . DOI: 10.11868/j.issn.1001-4381.2024.000576
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GH3230合金是一种固溶强化型Ni-Cr基变形高温合金，具有优异的抗氧化性能、热强性、热稳定性和工艺性能，长时使用温度1050 ℃［1-2］，轧制的板材已大量应用于现役和在研的航空发动机燃烧室火焰筒等复杂薄壁零件［3］。近期发现，某些极端的飞行或实验工况下航空发动机燃烧室、涡轮部件均会多次出现短时超温的现象［4］，研究超温对高温合金组织和性能的影响日渐受到重视［5-7］。另一方面，可重复使用航天飞行器应用高温合金板材有助于克服陶瓷材料易热震开裂、易脱落等难题［8］，但飞行器进出大气层时剧烈摩擦产生的热气流［9］会使大面积热防护材料表面温度高达1200 ℃，研究短时反复超温对GH3230合金承载能力的影响是其在可重复使用航天器应用的重要基础。
高温合金在超过其抗氧化温度服役时，其表面氧化膜极易出现开裂和剥离［5，10］，高温下失去氧化膜保护的材料将产生剧烈的氧化反应，形成的氧化损伤以及成分、组织变化会明显降低材料的强度和塑性［6，11-13］。而且，高温合金强度和塑性的衰减随超温温度的增加而加剧［14-15］，如GH3033合金超温后晶界碳化物溶解使晶粒快速长大，合金抗拉强度和塑性大幅度下降［14］；K465合金超温后晶界残余共晶组织发生初熔［15］，会导致合金失去再次承载的能力。
GH3230合金在900~1100 ℃空气中氧化产物Cr2O3或Cr2O3/Ni（Mn）Cr2O4混合物具有良好的附着性，氧化动力学遵循抛物线规律［16-17］。但在1093 ℃停留30 min后冷却至室温的循环氧化实验中发现，循环超过48次后表面氧化层出现剥离现象，使较多的O原子进入基体产生一定量的Al2O3内氧化物［18］。近期开展的1200 ℃/60 min循环氧化实验中发现［19］，增加氧化物生长应力和增大冷却温差产生的热应力导致了氧化膜不断开裂和剥离，使GH3230合金的氧化动力学表现为氧化失重，基体内氧化和成分、组织变化程度随循环次数的增加而明显增强。目前，鲜见循环超温影响GH3230合金再次承载能力和塑性水平的研究报道。
本工作对循环升温至1200 ℃热暴露10~100次后的GH3230合金试样进行拉伸实验，与原始固溶态和100次循环热暴露后再加工到尺寸试样对比，研究评价氧化损伤和组织变化对该合金抗拉强度和塑性的影响规律。通过试样表层和心部成分-组织分析、拉伸断口和中断拉伸试样的解剖观察，讨论揭示超高温循环热暴露影响GH3230合金拉伸性能的规律和机理。
1 实验材料与方法
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1.1 实验材料
实验所用试样取自厚度为15 mm的GH3230合金热轧板，板材的成分分析结果见表1，固溶热处理制度为1220 ℃/0.5 h油冷。
1.2 实验方法
室温拉伸实验按GB/T 228.1—2021《金属材料拉伸实验第1部分：室温试验方法》进行测试，试样尺寸如图1所示。
沿板材纵向切取7组Φ14 mm ×66 mm试棒用于加工室温拉伸试样，每组保证3个平行试样。1组原始固溶态试棒加工到尺寸后进行室温拉伸实验；5组试样标距部分加工到尺寸后装入1200 ℃、空气充分的箱式电阻炉中，入炉60 min后出炉空冷至室温，室温停留5 min后进行下一个循环，分别循环10、20、40、60、100次后将试样夹持部位加工到标样尺寸，随后进行室温拉伸实验，增加100次循环氧化试样一件，拉伸至10%塑性应变量后中断实验用于解剖分析；另一组试棒进行相同过程的100次循环后加工到标样尺寸再进行室温拉伸实验。
采用扫描电子显微镜（SEM）观察拉伸试样的断口和表面形貌。中断拉伸的试样在Secotom-15 精密切割机上以0.005 mm/s的进刀速率沿轴向解剖，SEM观察试样内部裂纹的产生、扩展和钝化过程。用于观察循环氧化对表面和内部组织影响的试样尺寸Φ5 mm×20 mm，经磨削和抛光后表面粗糙度（Ra）值控制在0.63~1.25 μm进行氧化实验，沿轴向切取金相试样，研磨抛光后以20 g氯化铜+100 mL盐酸+100 mL酒精腐蚀液擦蚀，光学显微镜（OM）和SEM背散射像观察氧化前、后的组织形貌，按照GB/T 6394—2017金属平均晶粒度测定方法测试晶粒度，以电子探针（EPMA）定量分析循环氧化后截面上元素分布及相组成的变化。
2 结果与分析
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2.1 循环超温对抗拉强度和塑性的影响
将氧化试样屈服强度、抗拉强度与原始试样强度的比值作为强度保持率绘在图2（a）中，氧化试样与固溶态试样塑性伸长率、断面收缩率的比值作为塑性变化率绘在图2（b）中。其中，100次循环氧化后加工到尺寸试样标记为100 M（Machined）。
随超温热暴露次数的增加，GH3230合金氧化试样的屈服强度和抗拉强度均有所降低（图2（a）），100次热暴露后加工试样的抗拉和屈服强度恢复到热暴露10次试样的水平，说明循环超温热暴露影响该合金强度的程度主要取决于表面和表面层组织的变化。值得注意的是，循环超温后屈服强度降低的程度相对较大，使其屈强比变得低于固溶态试样、接近超低屈强比高强钢的水平［20］。屈强比可以反映材料应变硬化的能力，屈强比越低、材料破断前产生稳定塑性变形能力越高；该合金超温达到100次时的强度保持率仍接近90%，表明其多次超温后仍可具有良好的结构可靠性。
另一方面，循环超温后GH3230合金氧化试样表现出的室温拉伸塑性与其他高温合金材料［7，12-14］明显不同。其伸长率先是随超温热暴露次数的增加而有所提高，在40次循环时达到最高值。热暴露次数增加至60次时，伸长率有所降低，继续增加至100次时伸长率并未见进一步地下降。同时注意到，断面收缩率随超温热暴露次数变化的规律与伸长率基本一致。这种高的塑性保持比率有利于燃烧室火焰筒和航天飞行器大面积热防护等结构的可靠性。
2.2 拉伸断口特征
不同状态试样拉伸断口宏观形貌如图3所示，首先观察了试样的拉伸断口特征，发现超温氧化试样与光滑试样的断裂模式是相同的，均是主裂纹由心部区域起源向周边扩展，不同的是氧化试样断口上次生裂纹的数量和尺寸明显多于光滑试样、且随循环氧化次数的增加而增加。
不同状态试样拉伸断口韧窝的微观形貌如图4所示。观察发现，固溶态试样断口外缘部位存在数量较多的抛物线形韧窝，表明试样的外缘是最后开裂的，在剪切应力的作用下韧窝被拉长而呈抛物线形［21］（图4（a），（b））。而氧化试样断口外缘韧窝的数量较少，形状为椭圆形、底部可见异质颗粒，尺寸和深度均较大（图4（c），（d））。说明表面层的γ固溶体在正应力作用下首先发生了塑性变形，为释放内氧化物颗粒的应力集中而产生了较大的塑性应变［21-22］，而其主裂纹扩展至试样拉伸失效的机制有待于对中断拉伸试样的解剖观察。
2.3 中断拉伸试样的解剖观察
氧化试样的横截面上未见循环变温产生的热应力使表面氧化物和内氧化物条带开裂的现象（图5（a）），氧化试样拉伸实验前表面和内部都是完整的。然而，沿轴向解剖拉伸至10%塑性应变后中断实验的100次超温氧化试样发现，表面氧化物和内氧化物大多发生开裂（图5（b））。这些裂纹主要存在于表面和内氧化物内部，裂纹可沿内氧化物连通，影响试样的有效承载面积，但已明显钝化并未扩展进入基体。由此可见，氧化试样的拉伸失效过程应该是心部主裂纹向外缘扩展至与内氧化物裂纹连通，氧化物的早期开裂未改变试样的宏观拉伸失效模式。
2.4 组织变化的影响
不同状态试样心部的OM显微组织如图6所示。观察发现，随超温热暴露次数增加，GH3230合金试样心部组织变化不大，而试样表面层组织中碳化物回溶、晶粒明显粗化。
首先，循环超温后试样心部组织中基体γ相的晶粒尺寸有所增加，在超温热暴露少于40次时晶粒长大较为明显，而进一步增加超温热暴露次数后晶粒尺寸的变化很小。定量金相法测得的原始固溶态晶粒度7级、平均晶粒尺寸27.2 μm，超温40次后时晶粒度5.5级、平均晶粒尺寸增加至50.7 μm，超温60次和100次后晶粒度均为5.0级、平均晶粒尺寸仅增加了4.0 μm。GH3230合金试样在1200 ℃热暴露，相当于进行二次固溶处理。本工作合金板材1220 ℃/0.5 h固溶处理时间较短，再结晶不够完全，则1200 ℃下残留的储存能会驱动晶粒长大［23］，而随着储存能的释放，心部组织的晶粒尺寸趋于稳定。
对应平均晶粒尺寸由27.2 μm增加到54.7 μm，100次超温热暴露后加工试样的屈服强度和抗拉强度相比固溶态试样分别降低了19.0 MPa和29.4 MPa，表明基体相晶粒粗化造成了GH3230合金约3%~5%的强度损失。因而，进一步优化固溶处理制度，减少固溶态组织储存能，将有助于增强GH3230合金超温条件下的组织稳定性、提高其强度保持率。
100次循环超温试样剖面组织的SEM图像如图7所示。表面层因碳化物回溶，晶粒长大程度很高，100次循环氧化后晶粒尺寸已超过150 μm，接近碳化物回溶区的深度（220 μm）。相应地，超温100次氧化试样的屈服和抗拉强度相比固溶态分别降低了35.0和74.3 MPa，表面层内氧化和组织粗化分别该合金的强度损失增加到9.0%~10.5%。
2.5 成分变化的作用
根据氧化行为研究［19］中发现的碳化物回溶区Cr、W、Mo元素由表及内的浓度变化规律，在100次循环超温试样中选取碳化物回溶区近表面、中部、与心部组织交界以及正常组织中的固溶体基体位置点进行了Cr、W、Mo元素的电子探针定量分析，如图8所示。
根据电子探针定量分析的结果（表2），引用合金元素固溶强化效果与该类合金屈服强度关系的经验公式［24］ΔσSS=∑ki1ncin（其中，ci 为固溶元素的原子分数；GH3230合金中W、Cr、Mo元素对应的ki 经验值分别为 977、377、1015 MPa·%（atom）-0.5；n为0.5），计算得出碳化物回溶区γ固溶体和心部组织屈服强度值见表3。结果表明，由于W、Mo元素的强化因子很大，碳化物回溶增加的W、Mo元素可弥补Cr元素贫化对固溶强化效果的不利影响，超温热暴露产生的成分变化不会明显降低碳化物回溶区主要合金元素的固溶强化效果，因而超温热暴露后GH3230合金可具有较高的强度保持率。
第一性原理计算的镍基合金中过渡族元素与其弹性模量关系［25-26］表明，具有d电子半占据数的Cr元素对弹性模量的贡献量高于5 d周期的W元素及4 d周期的Mo元素，则超温氧化产生的成分变化会使碳化物回溶区的弹性模量变小，加上心部组织中的硬质碳化物还有增加材料刚度［27］的作用，氧化试样表面层的弹性模量应明显低于心部材料。根据轴向拉伸载荷作用下同轴双晶体变形的应变连续性原则［12］，轴向应变和剪切应变在完整的同轴双晶体的界面上均是连续的，其他两个方向上的应变会因弹性模量的差异而有所不同，这种应变差会在两者交界面上产生应力集中，使变形抗力相对较大的区域在低于其屈服强度下发生塑性变形。因而，本实验结果中氧化试样的屈服强度降低相对较多，使其表现出超低的屈强比。
有研究表明，增加W的固溶量可显著降低fcc结构相的层错能［28］，显著抑制变形过程中应变局部化、增加变形的均匀程度［29-30］。本工作氧化试样表面层的碳化物回溶增加了Ni-Cr基fcc结构固溶体中的W含量，使得碳化物回溶形成的单相γ固溶体具有较好的塑性变形特性，有效钝化了氧化物裂纹，阻止其扩展成为长裂纹。因而，拉伸实验中超温氧化试样碳化物回溶表面层的充分塑性变形，使其呈现出与固溶态试样相同的拉伸失效模式，而且钝化的表面裂纹不会产生缺口约束塑性变形的效应［31］，则超温一定次数的氧化试样可能产生比固溶态试样更好的塑性。
3 结论
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（1）GH3230合金在1200 ℃进行10~100次循环热暴露后，氧化试样的强度保持率仍接近90%，而拉伸塑性则表现为40次前有所增加、60次后略有降低、100次热暴露后加工试样的强度和塑性均有所回升。
（2）超温热暴露使固溶态GH3230合金晶粒粗化和内氧化产物开裂、减少有效承载面积是导致氧化试样屈服强度、抗拉强度降低的组织因素；超温热暴露后表面层Cr、W、Mo含量的变化未明显降低基体相的固溶强化效果，是氧化试样具有较高强度保持率的成分因素。
（3）氧化试样表面层碳化物回溶、W元素固溶量增加使其具有良好的塑性变形特性，有效钝化了氧化物裂纹、阻止其扩展成为长裂纹，钝化的表面裂纹未产生约束塑性变形的缺口效应，使得多次超温热暴露后的氧化试样仍具有良好的拉伸塑性。

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2026年第54卷第2期
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doi: 10.11868/j.issn.1001-4381.2024.000576
  • 接收时间：2024-08-13
  • 首发时间：2026-10-27
  • 出版时间：2026-02-20
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  • 收稿日期：2024-08-13
  • 录用日期：2024-09-03
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    北京钢研高纳科技股份有限公司，北京 100081

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张亚玮（1981—），女，高级工程师，博士，主要从事高温合金研究，联系地址：北京市海淀区气象路9号（100081），E-mail：
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2种不同金属材料的力学参数
科
Family		 属数
Number of
genus		 种数
Number of
species		 占总种数比例
Percentage of
total species (%)		 属
Genus		 种数
Number of
species		 占总种数比例
Percentage of total
species (%)
鹅膏菌科Amanitaceae 2 11 5.26 鹅膏菌属 Amanita 10 4.78
小菇科 Mycenaceae 2 12 5.74 丝盖伞属 Inocybe 5 2.39
多孔菌科 Polyporaceae 8 14 6.70 蜡蘑属 Laccaria 5 2.39
红菇科 Russulaceae 3 23 11.00 小皮伞属 Marasmius 6 2.87
小菇属 Mycena 11 5.26
光柄菇属 Pluteus 5 2.39
红菇属 Russula 17 8.13
栓菌属 Trametes 5 2.39
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