碳/碳复合材料室温和700℃面内剪切疲劳试验  

Experimental Investigation of in-Plane Shear Fatigue behavior of Carbon/Carbon Composite at Room Temperature and 700℃

作　　者：陈波 刘晓倩 杨兴林 温卫东[2] 翁晶萌 张俊苗 CHEN Bo;LIU Xiao-qian;YANG Xing-lin;WEN Wei-dong;WENG Jing-meng;ZHANG Jun-miao(College of Energy and Power,Jiangsu University of Science and Technology,Zhenjiang Jiangsu 212100,China;College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Xi’an Aerospace Propulsion Institute,Xi’an 710100,China)

机构地区：[1]江苏科技大学能源与动力学院,江苏镇江212100 [2]南京航空航天大学能源与动力学院,南京210016 [3]西安航天动力研究所,西安710100

出　　处：《航空发动机》2023年第4期168-174,共7页Aeroengine

基　　金：江苏科技大学科研启动资金(1142931905)资助。

摘　　要：为了研究高温环境碳/碳复合材料面内剪切疲劳特性,以含防氧化涂层的[±45]4S铺层碳/碳复合材料为研究对象,开展了室温和700℃下的拉/拉疲劳试验。结果表明:碳/碳复合材料面内剪切剩余刚度变化呈横向的“S”形,对比室温环境,在700℃下碳/碳复合材料面内剪切疲劳在中期损伤时的刚度降低趋势更为明显,在室温时发生疲劳断裂的剩余刚度为初始刚度的82%,而在700℃下则降低至初始刚度的68%;在室温环境下碳/碳复合材料在33%和66%循环数后的面内剪切剩余强度分别为初始强度的95.20%和85.70%,当温度升高为700℃时,分别为96.43%和85.59%。基于损伤因子的刚度和强度表征,考虑温度、应力水平的影响,建立了碳/碳复合材料剩余刚度、剩余强度模型,较好地拟合了试验数据,高精度地获得了室温和700℃下碳/碳复合材料面内剪切疲劳剩余刚度、剩余强度理论曲线,为后续复杂碳/碳复合材料结构件疲劳寿命预测提供了重要数据。In order to study the high-temperature in-plane shear fatigue characteristics of carbon/carbon composites,[±45]4S laminat⁃ed carbon/carbon composites with anti-oxidation coating were experimentally investigated by conducting tensile/tensile fatigue tests at room temperature and 700℃.The test results show that the in-plane shear residual stiffness of carbon/carbon composites exhibits a trans⁃verse"S"shape.Compared with room temperature,the mid-term decreasing trend of the in-plane shear fatigue stiffness is more pro⁃nounced at 700℃.The residual stiffness of fatigue fracture at room temperature is 82%of the initial stiffness,but decreases to 68%of the initial stiffness at 700℃.At room temperature,after 33%and 66%cycles,the in-plane shear residual strengths are 95.20%and 85.70%of the initial strength,respectively.When the temperature rises to 700℃,they are 96.43%and 85.59%,respectively.Based on the stiffness and strength characterization of the damage factor,considering the influence of temperature and stress level,the residual stiff⁃ness and residual strength models of carbon/carbon composites were established,which well fitted the experimental data.The theoretical curves of in-plane shear fatigue residual stiffness and residual strength of carbon/carbon composites at room temperature and 700℃ were obtained with high precision,which provides important data for subsequent fatigue life predictions of complex carbon/carbon composites.

关 键 词：碳/碳复合材料 面内剪切 疲劳试验 剩余刚度 剩余强度 逐渐损伤 

分 类 号：V231.91[航空宇航科学与技术—航空宇航推进理论与工程]