| 高压压气机转子叶片断裂分析 |
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| 引用本文： | 李彦,都建京,陈星,刘新灵,李佳佳. 高压压气机转子叶片断裂分析[J]. 失效分析与预防, 2019, 14(3): 188-192. DOI: 10.3969/j.issn.1673-6214.2019.03.010 |
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| 作者姓名： | 李彦 都建京 陈星 刘新灵 李佳佳 |
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| 作者单位： | 中国航发北京航空材料研究院,北京100095;航空材料检测与评价北京市重点实验室,北京100095;中国航空发动机集团材料检测与评价重点实验室,北京100095;中国航发北京航空材料研究院,北京100095;航空材料检测与评价北京市重点实验室,北京100095;中国航空发动机集团材料检测与评价重点实验室,北京100095;中国航发失效分析中心,北京100095;中国航发四川燃气涡轮研究院,成都,610500 |
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| 摘 要： | 对断裂叶片进行材质和断口等综合分析,确认高压压气机Ⅰ、Ⅱ级叶片断裂的特征和失效模式,明确叶片断裂失效与材料的力学性能等冶金因素无关。结果显示:高压压气机Ⅰ级叶片断裂为疲劳断裂,为首断件和肇事件;Ⅱ级叶盘所有叶片均为大应力作用下的疲劳断裂,为受害件。Ⅰ级叶盘叶片断裂与承受较大的共振应力有关,属于结构设计问题。进一步的分析表明,压气机Ⅰ级叶盘叶片叶型厚度超差,使得K=3激起的一阶弯曲共振转速更靠近慢车转速区域。疲劳断裂叶片在裂纹萌生处存在明显的横向加工痕迹,降低了疲劳性能。叶片表面较明显的加工损伤对Ⅰ级转子叶片断裂起到一定的促进作用。
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| 关 键 词： | 高压压气机叶片 整体叶盘 1Cr12Ni2WMoVNb钢 共振 |
| 收稿时间： | 2019-03-23 |
Failure Analysis of Rotor Blades in High-pressure Compressor |
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| LI Yan,DU Jian-jing,CHEN Xing,LIU Xin-ling,LI Jia-jia. Failure Analysis of Rotor Blades in High-pressure Compressor[J]. Failure Analysis and Prevention, 2019, 14(3): 188-192. DOI: 10.3969/j.issn.1673-6214.2019.03.010 |
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| Authors: | LI Yan DU Jian-jing CHEN Xing LIU Xin-ling LI Jia-jia |
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| Affiliation: | (AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China;Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation,Beijing 100095,China;AECC Key Laboratory of Science and Technology on Aeronautical Materials Testing and Evaluation,Beijing 100095,China;AECC Failure Analysis Center,Beijing 100095,China;AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China) |
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| Abstract: | The fracture characteristics and failure modes of the first- and second-stage blades in a high-pressure compressor were confirmed by comprehensive analysis on the material and fracture surface of the fractured blades.The results show that the fracture of the blades has nothing to do with the material.The first-stage blades of the high-pressure compressor first fractured,and their failure mode is fatigue fracture.The failure mode of all the second-stage blades is fatigue fracture by larger stress,so they are victims.The fracture of the first-stage blades is mainly related to larger resonance stress,which belongs to structural design problem.Further analysis shows that the thickness of the first-stage blades is excessive,making the first-order bending resonance speed caused by K=3 closer to the speed range of slow car.There are obvious transverse machining marks near the crack source of the fatigue fracture blades,which reduced the fatigue performance.The obvious machining damage on the blade surface promoted the fracture of the first-stage blades. |
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| Keywords: | high-pressure compressor rotor blade blisk blade 1Cr12Ni2WMoVNb steel resonance |
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