镍基高温合金 GH4065A高温疲劳断裂机制研究
TG132.3+2%TG111.8%TB31; 针对新一代航空发动机涡轮盘用超低C,N含量的变形高温合金GH4065A,系统表征和定量统计了合金的夹杂物组织.对细晶态和粗晶态试样开展了 400 ℃和650 ℃不同载荷水平下的疲劳实验.通过对疲劳断裂源组织进行表征分析,研究了合金的疲劳断裂机制.结果表明,合金的夹杂物主要为氮化物.在细晶组织状态下,高温疲劳断裂机制为氮化物(单独和团簇态)起始断裂.高应变幅载荷下(≥0.9％),断裂源主要为试样表面氮化物,极少情况为表面硼化物和氧化物(Al2O3和MgSiO3),且只有Al2O3导致合金过早疲劳断裂;低应变幅载荷下(＜0.9％),断裂源为氮化物-解...
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| Published in | 材料工程 Vol. 53; no. 1; pp. 72 - 80 |
|---|---|
| Main Authors | , , , , , |
| Format | Journal Article |
| Language | Chinese |
| Published |
钢铁研究总院有限公司高温材料研究所,北京 100081
20.01.2025
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| Subjects | |
| Online Access | Get full text |
| ISSN | 1001-4381 |
| DOI | 10.11868/j.issn.1001-4381.2024.000321 |
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| Abstract | TG132.3+2%TG111.8%TB31; 针对新一代航空发动机涡轮盘用超低C,N含量的变形高温合金GH4065A,系统表征和定量统计了合金的夹杂物组织.对细晶态和粗晶态试样开展了 400 ℃和650 ℃不同载荷水平下的疲劳实验.通过对疲劳断裂源组织进行表征分析,研究了合金的疲劳断裂机制.结果表明,合金的夹杂物主要为氮化物.在细晶组织状态下,高温疲劳断裂机制为氮化物(单独和团簇态)起始断裂.高应变幅载荷下(≥0.9％),断裂源主要为试样表面氮化物,极少情况为表面硼化物和氧化物(Al2O3和MgSiO3),且只有Al2O3导致合金过早疲劳断裂;低应变幅载荷下(＜0.9％),断裂源为氮化物-解理面型,均在试样近表面/内部.两种不同的断裂方式分别导致高应变幅载荷下400 ℃疲劳寿命高于650 ℃疲劳寿命,低应变幅载荷下反之.统计发现,引起疲劳断裂的所有氮化物的尺寸全部达到/超过细晶组织平均晶粒尺寸.在粗晶组织状态下,400 ℃下疲劳断裂机制为准解理起始断裂.晶粒尺寸的增加极大降低了可能诱发疲劳开裂的夹杂物的有效数量,滑移诱发的解理断裂成为主导断裂机制. |
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| AbstractList | TG132.3+2%TG111.8%TB31; 针对新一代航空发动机涡轮盘用超低C,N含量的变形高温合金GH4065A,系统表征和定量统计了合金的夹杂物组织.对细晶态和粗晶态试样开展了 400 ℃和650 ℃不同载荷水平下的疲劳实验.通过对疲劳断裂源组织进行表征分析,研究了合金的疲劳断裂机制.结果表明,合金的夹杂物主要为氮化物.在细晶组织状态下,高温疲劳断裂机制为氮化物(单独和团簇态)起始断裂.高应变幅载荷下(≥0.9％),断裂源主要为试样表面氮化物,极少情况为表面硼化物和氧化物(Al2O3和MgSiO3),且只有Al2O3导致合金过早疲劳断裂;低应变幅载荷下(＜0.9％),断裂源为氮化物-解理面型,均在试样近表面/内部.两种不同的断裂方式分别导致高应变幅载荷下400 ℃疲劳寿命高于650 ℃疲劳寿命,低应变幅载荷下反之.统计发现,引起疲劳断裂的所有氮化物的尺寸全部达到/超过细晶组织平均晶粒尺寸.在粗晶组织状态下,400 ℃下疲劳断裂机制为准解理起始断裂.晶粒尺寸的增加极大降低了可能诱发疲劳开裂的夹杂物的有效数量,滑移诱发的解理断裂成为主导断裂机制. |
| Abstract_FL | GH4065A is a newly developed high-performance cast-wrought Ni-base superalloy with ultra-low C and N content used for advanced turbine engine disc.In this study,the alloy's inclusions of the alloy are characterized and statistically analyzed.To investigate the fatigue fracture mechanism,strain-controlled fatigue tests are conducted at 400℃ and 650℃ on the fine-grained and coarse-grained samples respectively.The results show that the alloy's inclusions of the alloy are mainly nitrides.For the fine-grained samples,discrete nitride particles and clustered nitrides both with a critical size larger than the average grain size are responsible for the fatigue crack initiation.When subjected to high-level strains(≥0.9％),fatigue failure primarily originates from surface nitrides,with rare occurrences of boride and oxide initiation.Surface crack induced by Al2O3,rather than boride or MgSiO3,is found to significantly reduce the fatigue life.Higher fatigue temperature results in reduced life cycles.When under lower levels of strain,however,subsurface/internal nitride-facet initiations dominate and fatigue life is prolonged by the elevated temperature.In the coarse-grained samples,fatigue failures at 400℃ are found to be initiated by quasi-cleavage cracking mechanism.Due to the increased grain size,the inclusion-induced crack initiation is suppressed while slip-induced cleavage cracking mechanism becomes predominant. |
| Author | 张继 张文云 田强 秦鹤勇 李林翰 张北江 |
| AuthorAffiliation | 钢铁研究总院有限公司高温材料研究所,北京 100081 |
| AuthorAffiliation_xml | – name: 钢铁研究总院有限公司高温材料研究所,北京 100081 |
| Author_FL | ZHANG Ji TIAN Qiang ZHANG Beijiang LI Linhan QIN Heyong ZHANG Wenyun |
| Author_FL_xml | – sequence: 1 fullname: LI Linhan – sequence: 2 fullname: ZHANG Ji – sequence: 3 fullname: ZHANG Wenyun – sequence: 4 fullname: TIAN Qiang – sequence: 5 fullname: QIN Heyong – sequence: 6 fullname: ZHANG Beijiang |
| Author_xml | – sequence: 1 fullname: 李林翰 – sequence: 2 fullname: 张继 – sequence: 3 fullname: 张文云 – sequence: 4 fullname: 田强 – sequence: 5 fullname: 秦鹤勇 – sequence: 6 fullname: 张北江 |
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| DOI | 10.11868/j.issn.1001-4381.2024.000321 |
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| DocumentTitle_FL | Fatigue fracture mechanism of Ni-base superalloy GH4065A at elevated temperatures |
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| Keywords | 氮化物 inclusion 镍基高温合金 fatigue nitride 断裂源 crack initiation 夹杂物 Ni-base superalloy 疲劳 |
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| Snippet | TG132.3+2%TG111.8%TB31; 针对新一代航空发动机涡轮盘用超低C,N含量的变形高温合金GH4065A,系统表征和定量统计了合金的夹杂物组织.对细晶态和粗晶态试样开展了 400 ℃和650... |
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| Title | 镍基高温合金 GH4065A高温疲劳断裂机制研究 |
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