复合材料高低周复合疲劳试验技术

温班宁; 李少林; 石多奇; 向首亮; 曹端兴; 齐红宇

doi:10.13224/j.cnki.jasp.20230096

复合材料高低周复合疲劳试验技术

doi: 10.13224/j.cnki.jasp.20230096

温班宁^{1, 2,},
李少林^{1, 2},
石多奇^{1, 2},
向首亮^{1, 2},
曹端兴^{1, 2},
齐红宇^{1, 2,*, ,}

1.
北京航空航天大学能源与动力工程学院，北京 102206
2.
北京航空航天大学航空发动机结构强度北京市重点试验室，北京 102206

基金项目: 国家科技重大专项（2017-Ⅳ-0007-0044）

详细信息

作者简介:
温班宁（1996-），男，博士生，主要从事航空发动机强度与结构设计方面的研究。E-mail：694630235@qq.com

通讯作者:
齐红宇（1969-），男，教授，博士，主要从事非均匀材料结构的强度、寿命以及可靠性分析和航空绿色能源适航安全性等方面的研究。E-mail：qhy@buaa.edu.cn

中图分类号: V258.3
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出版历程
- 收稿日期: 2023-02-21
- 网络出版日期: 2024-05-24

Combined cycle fatigue test technology for composite materials

WEN Banning^{1, 2
,},
LI Shaolin^{1, 2},
SHI Duoqi^{1, 2},
XIANG Shouliang^{1, 2},
CAO Duanxing^{1, 2},
QI Hongyu^{1, 2,*
, ,}

1.
School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 102206，China
2.
Beijing Key Laboratory of Aero-Engine Structure and Strength，Beijing University of Aeronautics and Astronautics，Beijing 102206，China

摘要

摘要:
为了研究复合材料的高低周复合疲劳特性，本文综合分析了现有的高低周复合疲劳试验平台设计思路及研究进展，以搭建适用于复合材料的复合疲劳试验平台。结合复合材料疲劳失效特性，设计了非对称哑铃型的2维编织复合材料试件用于复合疲劳试验。试验结果显示：试件在特殊设计的疲劳考核区发生断裂失效。失效部位的应变曲线既展现了受低周疲劳载荷作用时低频高幅值的变化特征，也具有受高周疲劳载荷作用时高频低幅值的变化特征，证明失效部位在试验中受到非干涉高低周复合疲劳载荷的持续作用。疲劳试验的顺利开展表明该研究为复合材料的复合疲劳试验研究提出一种试验方法。
- 复合材料 /
- 高低周复合疲劳 /
- 复合疲劳试验平台 /
- 非对称哑铃型 /
- 疲劳考核区.
Abstract:
In order to research the combined cycle fatigue properties of composite, the design ideas and research progress of existing combined cycle fatigue test platforms were comprehensively analyzed, contributing to building a combined cycle fatigue test platform for composite materials. Based on the fatigue failure mode of composite, the 2D braided composite specimen was designed as the asymmetric dumbbell shape for the fatigue test. The test result showed that failure occurred in the fatigue assessment area of the specimen. The strain curve of the failure site showed the characteristics of low frequency and high amplitude caused by low cycle fatigue load, and also the characteristics of high frequency and low amplitude caused by high cycle fatigue load. The completion of fatigue test demonstrated a test method for the research of combined cycle fatigue test of composite materials.
- composite /
- combined cycle fatigue /
- combined cycle fatigue test platform /
- asymmetrical dumb-bell specimen /
- fatigue assessment area

HTML

图 1 风扇叶片复合疲劳载荷

Figure 1. Combined cycle fatigue load of fan blade

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图 2 波音777航空发动机起飞事故

Figure 2. Boeing 777 aircraft engine takeoff accident

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图 3 复合疲劳应力示意图

Figure 3. Schematic diagram of combined cycle fatigue stress

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图 4 简化后的复合疲劳载荷谱

Figure 4. Simplified combined cycle fatigue load spectrum

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图 5 多轴加载疲劳试验系统

Figure 5. Multi-axial loading fatigue test system

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图 6 PREMECCY计划试验系统及特征件

Figure 6. Test system and advanced specimen of PREMECCY program

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图 7 试验系统及载荷传递路径

Figure 7. Test system and load transfer path

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图 8 高低周复合疲劳试验系统

Figure 8. Combined cycle fatigue test system

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图 9 复合材料哑铃型疲劳试件

Figure 9. Composite dumb-bell fatigue specimen

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图 10 悬臂梁弯曲疲劳试件

Figure 10. Specimen cantilever bending fatigue test

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图 11 复合材料非对称哑铃型疲劳试件

Figure 11. Asymmetric dumb-bell fatigue test specimen of composite

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图 12 复合材料疲劳试件准备工作（单位：mm）

Figure 12. Preparation of composite fatigue specimen （unit：mm）

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图 13 复合疲劳载荷下的应变数据

Figure 13. Strain data under combined fatigue load

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图 14 非对称哑铃型试件复合疲劳失效

Figure 14. Combined cycle fatigue of asymmetrical dumb-bell specimen

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表 1 试验系统对比分析

Table 1. Comparison and analysis of test systems

试验系统	试验对象	试验特征
图5	风扇叶片	1、试验平台搭建便捷 2、开展拉弯或拉扭疲劳试验 3、载荷大小受尼龙带限制
图6	特征模拟件	1、几何相似性和应力分布相似性的思想设计试件 2、通过弯曲共振模态产生高周疲劳载荷 3、可进行高温试验
图7	涡轮叶片榫齿	1、轴承机构实现非干涉加载 2、检测叶尖振幅间接测算榫齿高周疲劳应力 3、可进行高温试验

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表 2 应变片测量结果

Table 2. Stain gauge measurement result

应变片	低周疲劳应力峰值/MPa	弯曲应力峰值（谷值）/MPa
①	447.8	37.8（-25.0）
②	526.0	24.7（-18.0）
③	586.8	5.4（-4.1）

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