| 复合材料风扇叶片高周疲劳薄弱点位置预测 |
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| 引用本文： | 唐旭,张煜坤,陈勇.复合材料风扇叶片高周疲劳薄弱点位置预测[J].航空动力学报,2021,36(3):498-508. |
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| 作者姓名： | 唐旭 张煜坤 陈勇 |
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| 作者单位： | 1.School of Mechanical Engineering,Shanghai Jiao Tong University, Shanghai 200240,China |
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| 摘 要： | 提出了一种复合材料风扇叶片高周疲劳薄弱点位置预测方法。利用铺层信息文件,在ACP(ANSYS Composite Pre-Post)中通过壳单元法向拉伸建立全尺寸风扇叶片有限元模型,基于ANSYS-Workbench和Tecplot底层函数接口,开发的后处理程序完成铺层叶片有限元数据提取和数据库建立。根据复合材料CLD(constant life diagram)模型,采用薄弱点指标来预测叶片高周疲劳失效的位置。算例结果表明:叶片失效位置高度均不超过整个叶高的40%。1阶弯曲模态、1阶扭转模态、2阶扭转模态最先失效应力为层间正应力，2阶、3阶弯曲模态、弦向弯曲模态最先失效应力为层间切应力。叶片弯曲模态层间正应力薄弱点位于弦向中部;扭转模态振动应力幅值点全部为结构层,S3薄弱点靠近尾缘。压缩平均应力会导致叶片的高周疲劳破坏,具有较小静应力值的区域会成为薄弱点。
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| 关 键 词： | 高周疲劳 复合材料风扇叶片 复合材料CLD模型 振动应力裕度 薄弱点 |
| 收稿时间： | 2020/7/7 0:00:00 |
Prediction of composite fan blade high cycle fatigue weak-link point location |
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| TANG Xu,ZHANG Yukun,CHEN Yong,ZHANG Yukun,CHEN Yong.Prediction of composite fan blade high cycle fatigue weak-link point location[J].Journal of Aerospace Power,2021,36(3):498-508. |
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| Authors: | TANG Xu ZHANG Yukun CHEN Yong ZHANG Yukun CHEN Yong |
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| Affiliation: | 1.School of Mechanical Engineering,Shanghai Jiao Tong University, Shanghai 200240,China2.Engineering Research Center of Gas Turbine and Civil Aero Engine,Ministry of Education,Shanghai Jiao Tong University,Shanghai 200240,China |
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| Abstract: | A method for predicting the high cycle fatigue weak-link point location of composite fan blade was proposed. Using the layup information file, a full-scale fan blade finite element model was established by normal extruding shell elements in ACP (ANSYS composite pre-post). Based on ANSYS-Workbench and Tecplot application program interface, the developed post-processing program completed the layup blade finite element data extracts and database creation. According to the composite material CLD (constant life diagram) model, the weak-link point index was applied to predict the location of blade high cycle fatigue failure. Case results showed that the blade failure location height did not exceed 40% of the entire blade height. First failure stress of 1st bending mode，1st torsion mode and 2nd torsion mode was layer normal stress, while 2nd bending mode, 3rd bending mode and stripe mode failures first occurred in layer shear stress. The layer normal stress weak-link point of blade bending mode was located in chord middle; the torsional mode vibration stress amplitude points were all structural plys, and S3 weak-link point was near the trailing edge. Compressive average stress could cause high cycle fatigue blade failure, and the area with a smaller static stress value could become a weak-link point. |
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| Keywords: | high cycle fatigue composite fan blade composite material CLD model vibration stress margin weak-link point |
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