| 航空发动机辅助安装节吊耳结构优化及试验验证 |
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| 引用本文： | 刘长春,刘莹,储建恒,曹航,张勇,杨雷.航空发动机辅助安装节吊耳结构优化及试验验证[J].航空发动机,2015,41(5):58-61. |
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| 作者姓名： | 刘长春 刘莹 储建恒 曹航 张勇 杨雷 |
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| 作者单位： | 1. 中航工业沈阳发动机设计研究所，沈阳110015；2. 北京航天动力研究所，北京100076 |
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| 基金项目： | 国家重大基础研究项目资助 |
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| 摘 要： | 安装节是航空发动机的关键件,若其失效将导致发动机从飞机上脱开的严重后果。基于安全性和可靠性考虑,同时不改变安装节整体外廓结构尺寸,对某型航空发动机的辅助安装节吊耳进行了结构优化设计。基于有限元应力分析以及静强度和疲劳寿命试验,对原结构和优化后的辅助安装节吊耳进行了对比,结果表明:其静强度和疲劳寿命均大幅提高,优化后的结构更合理。
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| 关 键 词： | 辅助安装节 吊耳 优化设计 疲劳寿命 试验验证 航空发动机 |
Optimization and Experimental Validation of Rear-Mount Structure for an Aeroengine Auxiliary Installation System |
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| Authors: | LIU Chang-chun LIU Ying CHU Jian-heng CAO Hang ZHANG Yong YANG Lei |
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| Abstract: | Installation system is a key part in aeroengine, which failure would cause engine detached from aircraft. In consideration of security and reliability, the structure optimization of rear-mount for an aeroengine auxiliary installation system was designed on unchanging its overall structure size conditions. Based on finite stress analysis, static strength and fatigue experiment, and the optimized structure of rear-mount for auxiliary installation system was compared with that of the primary structure. The results show that the static strength and fatigue life are increased, and the optimized structure is more reasonable. |
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