| 含支承松动故障的弹用涡扇发动机整机振动建模与机匣响应特征 |
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| 引用本文： | 王海飞,陈果,廖仲坤,张璋,邵伏勇.含支承松动故障的弹用涡扇发动机整机振动建模与机匣响应特征[J].航空动力学报,2015,30(3):627-638. |
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| 作者姓名： | 王海飞 陈果 廖仲坤 张璋 邵伏勇 |
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| 作者单位： | 1. 南京航空航天大学民航学院,南京,210016
2. 中国航天科工集团公司飞航技术研究院北京动力机械研究所,北京,100074 |
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| 基金项目： | 国家基础研究项目(613139); 国家自然科学基金(61179057); 江苏省研究生培养创新工程(KYLX_0295); 中央高校基本科研业务费专项资金 |
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| 摘 要： | 针对某型弹用涡扇发动机结构特点,建立了一种转子-支承-机匣整机模型,对转子与机匣采用有限元梁模型,支承采用集总质量模型,引入支承松动故障模型,利用数值积分方法求解耦合系统的响应.基于机匣加速度信号,研究了对称刚度以及不对称刚度模型下松动故障的冲击特征分析.结果表明:1松动故障所引发的机匣加速度时域波形具有上下不对称性冲击特征以及频谱中出现倍频特征;2仿真计算结果与实际弹用涡扇发动机试车数据时域波形特征以及频谱特征非常一致,而且验证了不对称刚度松动故障模型更适合弹用涡扇发动机的松动故障建模.
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| 关 键 词： | 动力学建模 松动故障 有限元模型 松动特征 支承松动 |
| 收稿时间： | 2013/10/26 0:00:00 |
Modeling for whole missile turbofan engine vibration with support looseness fault and characteristics of casing response |
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| WANG Hai-fei,CHEN Guo,LIAO Zhong-kun,ZHANG Zhang and SHAO Fu-yong.Modeling for whole missile turbofan engine vibration with support looseness fault and characteristics of casing response[J].Journal of Aerospace Power,2015,30(3):627-638. |
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| Authors: | WANG Hai-fei CHEN Guo LIAO Zhong-kun ZHANG Zhang and SHAO Fu-yong |
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| Institution: | College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China,College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China,Beijing Power Machinery Research Institue, Aerodynamic Missile Technology Academy, China Aerospace Science and Industry Corporation, Beijing 100074, China,Beijing Power Machinery Research Institue, Aerodynamic Missile Technology Academy, China Aerospace Science and Industry Corporation, Beijing 100074, China and Beijing Power Machinery Research Institue, Aerodynamic Missile Technology Academy, China Aerospace Science and Industry Corporation, Beijing 100074, China |
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| Abstract: | For the structural characteristics of a certain type of missile turbofan engine, a rotor-support-casing whole model established. The rotor and casing were modeled by means of the finite element beam model; the support was modeled by lumped-mass model; support looseness fault model was also introduced. The coupled system response was obtained by the numerical integral method. Impact characteristics of symmetrical stiffness and asymmetric stiffness models were analyzed based on casing acceleration signal. It is found that looseness fault could lead to acceleration time-domain waveform of casing with up-down asymmetrical impact characteristics and multiple frequency characteristics in frequency spectrum. Time-domain waveform and frequency spectrum characteristics of the simulation results and the actual missile turbofan engine test data are very consistent. Asymmetric stiffness looseness model is verified more suitable for missile turbofan engine looseness fault modeling. |
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| Keywords: | dynamic modeling looseness fault finite element model looseness characteristics support looseness |
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