| 基于小裂纹断裂力学的冷端盘燕尾槽疲劳全寿命预测技术研究 |
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| 引用本文： | 刘绍伦,吴学仁,黄宏发,刘建中,丁传富,韩希鹏,杨士杰,蔚夺魁,刘湘生.基于小裂纹断裂力学的冷端盘燕尾槽疲劳全寿命预测技术研究[J].航空动力学报,1999,14(4):375-381. |
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| 作者姓名： | 刘绍伦 吴学仁 黄宏发 刘建中 丁传富 韩希鹏 杨士杰 蔚夺魁 刘湘生 |
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| 作者单位： | 1.北京航空材料研究院 |
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| 摘 要： | 本文通过对航空发动机冷端盘燕尾槽子构件及其材料钛合金ＴＣ１１ 的小裂纹扩展行为和疲劳的试验研究，燕尾槽子构件小裂纹的应力强度因子权函数解的分析研究，并利用塑性诱导的Ｎｅｗ ｍ ａｎ 裂纹闭合模型，建立起从裂纹开始萌生的燕尾槽槽底疲劳全寿命预测模型。结果表明，该模型预测子构件的疲劳寿命的误差在工程所允许的二倍寿命以内
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| 关 键 词： | 航空发动机 裂纹 疲劳寿命 预测 |
| 收稿时间： | 2/1/1999 12:00:00 AM |
FATIGUE LIFE PREDICTION OF TENONS IN AEROENGINE COLD-SECTION DISCS BASED ON SMALL CRACK GROWTH |
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| Liu Shaolun,Wu Xueren,Huang Hongf,Liu Jianzhong,Ding Chuanfu,Han Xipeng,Yang Shijie,Wei Duokui.FATIGUE LIFE PREDICTION OF TENONS IN AEROENGINE COLD-SECTION DISCS BASED ON SMALL CRACK GROWTH[J].Journal of Aerospace Power,1999,14(4):375-381. |
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| Authors: | Liu Shaolun Wu Xueren Huang Hongf Liu Jianzhong Ding Chuanfu Han Xipeng Yang Shijie Wei Duokui |
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| Institution: | 1.Lab of mechanical properties, Beijing Institute of Aeronautics Materials,Beijing 1000952.Research Institute of Aeroegine,Shengyang 110015 |
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| Abstract: | Tests for small and large crack growth were conducted on substructure model of tenon in the aeroengine cold section disc which was made of Titanium alloy TC11.Stress intensity factor solution of the substructure was obtained by FEM and its weight functions were analyzed.Plasticity introduced Newman Crack Closure model was used to predict the total fatigue life of the substructure,in which small crack was initiated from swallow-tailed groove bottom.Prediction results are in good agreement with tested results. |
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| Keywords: | Aeroengine Cracks Fatigue life Prediction |
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