| 引用本文: | 张弛,周文龙,王敏涓,付雪松,黄浩,陈国清.SiCf/TC17复合材料的疲劳断裂机理研究[J].材料科学与工艺,2025,33(4):14-21.DOI:10.11951/j.issn.1005-0299.20240011. |
| ZHANG Chi,ZHOU Wenlong,WANG Minjuan,FU Xuesong,HUANG Hao,CHEN Guoqing.Study on fatigue fracture mechanism of SiCf/TC17 composites[J].Materials Science and Technology,2025,33(4):14-21.DOI:10.11951/j.issn.1005-0299.20240011. |
|
| |
|
|
| 本文已被：浏览 22次 下载 6次 |
![本文二维码信息]()
码上扫一扫！ |
|
|
| SiCf/TC17复合材料的疲劳断裂机理研究 |
|
张弛1,周文龙1,王敏涓2,付雪松1,黄浩2,陈国清1
|
|
(1.大连理工大学 材料科学与工程学院,辽宁 大连 116024; 2.中航发北京航空材料研究院 钛合金研究所,北京100095)
|
|
| 摘要: |
| 纤维增强钛基复合材料因其具有较高的比强度和比模量,同时具有良好的耐高温性能,被广泛应用于航空涡轮发动机叶环等结构件。由于其断裂失效形式比较复杂,为了探究其疲劳失效机制,本文利用疲劳试验机对SiCf/TC17复合材料开展了室温疲劳实验,通过扫描电子显微镜观察了SiCf/TC17复合材料的断裂行为,研究了连续SiC纤维增强TC17合金复合材料的疲劳性能,分析了SiCf/TC17复合材料在交变载荷下的疲劳断裂机理。结果表明:SiCf/TC17复合材料的疲劳寿命波动较大。在室温交变载荷条件下,SiCf/TC17复合材料疲劳裂纹萌生于TC17合金包套的次表层处,且为多个疲劳源；随着疲劳裂纹向前扩展,在疲劳裂纹扩展区呈现疲劳条带及二次裂纹,在扩展过程中,当裂纹前端遇到SiC纤维时,在SiCf/基体界面发生偏转和界面脱粘,裂纹绕过纤维继续在基体中扩展,产生纤维桥接效应,纤维分担了基体中的载荷,有利于复合材料的抗疲劳性能；在疲劳后期的瞬断区,TC17合金基体发生塑性变形,SiC纤维发生断裂,脱粘的纤维呈拔出形态,复合材料完全断裂失效。研究结果可为SiCf/TC17复合材料设计与工艺优化提供指导和依据。 |
| 关键词: SiC纤维 钛基复合材料 疲劳断裂机理 裂纹扩展 纤维桥接 |
| DOI：10.11951/j.issn.1005-0299.20240011 |
| 分类号:TB333 |
| 文献标识码:A |
| 基金项目:国家科技重大专项项目(HT-J2019-VI-0007-0121). |
|
| Study on fatigue fracture mechanism of SiCf/TC17 composites |
|
ZHANG Chi1, ZHOU Wenlong1, WANG Minjuan2, FU Xuesong1, HUANG Hao2, CHEN Guoqing1
|
|
(1.School of Materials Science and Engineering, Dalian University of Technology, Dalian 116024, China; 2.Titanium Alloy Research Institute, AECC Beijing Institute of Aeronautical Materials, Beijing 100095, China)
|
| Abstract: |
| Fiber-reinforced titanium matrix composites are widely used in structural parts such as leaf rings of aviation turbine engines because of their high specific strength and specific modulus, as well as good high temperature resistance. However, the fracture failure mode is complex.In order to explore the fatigue failure mechanism, this study conducted the fatigue test of SiCf/TC17 composites at room temperature by fatigue testing machine.The fracture behavior of SiCf/TC17 composites was observed by scanning electron microscopy, and the fatigue properties of continuous SiC fiber reinforced TC17 alloy composites were studied. The fatigue fracture mechanism of SiCf/TC17 composites under alternating load was analyzed. The results show that the fatigue life of SiCf/TC17 composites fluctuates greatly.Under the alternating load conditions at room temperature, the fatigue cracks of SiCf/TC17 composites originate at the subsurface layer of the TC17 alloy of the sample, and multiple fatigue initiations are observed.As the fatigue cracks propagate, fatigue striations and secondary cracks appear in the fatigue crack propagation region.During the propagation process, when the crack front end encounters SiC fibers, deflection and interfacial debonding occur at the SiCf/matrix interface. The crack bypasses the fiber and continues to propagate in the matrix, resulting in fiber bridging effect.The fiber shares the load in the matrix, which is conducive to the fatigue resistance of the composite. In the final stage of fatigue, the TC17 alloy matrix undergoes plastic deformation, and the SiC fiber fractures with the debonded fiber exhibiting a pull-out morphology due to debonding.The composite material breaks completely and fails in fatigue transient zone.The research results in this paper can provide guidance and a basis for the design and process optimization of SiCf/TC17 composites. |
| Key words: SiC fiber titanium matrix composites fatigue fracture mechanism crack propagation fiber bridging |
|
|
|
|
