整体离心叶轮叶片的振动可靠性分析  

Analysis of Integrated Centrifugal Impeller Blade Vibration Reliability

作　　者：金向明[1] 高德平[1] 蔡显新[2] 吴立强[2] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]中国航空动力机械研究所,湖南株洲412002

出　　处：《航空动力学报》2004年第5期610-613,共4页Journal of Aerospace Power

摘　　要：述及了整体离心叶轮的结构及其故障模式特点,在强迫振动放大系数模型的基础上提出了离心叶轮叶片的振动可靠性分析方法,结合固有频率灵敏度分析的叶片共振相干分析,通过厚度控制来调整整体叶轮叶片的固有频率,控制强迫振动放大系数使之避开危险性共振或强迫振动,给出了一实际算例,算例及试车试验表明本文方法是有效的。The characteristic of the integrated impeller blade structure and its failure mode is presented. A method for integrated impeller blade resonance reliability analysis based on forced vibration magnifying factor model combined with sensitivity analysis of natural frequency is proposed. Fatal resonance and forced vibration can be avoided by controlling the magnifying factor of forced vibration, and by controlling the natural frequency which is affected by the thickness of the integrated impeller blade. Finally, an example is presented. Compared with subsequent test result, it shows that the presented method is effective.

关 键 词：离心叶轮 叶片 可靠性 推进系统 航空航天 

分 类 号：V231.92[航空宇航科学与技术—航空宇航推进理论与工程]