Modeling and analysis of mistuned bladed disk vibration: Status and emerging directions

被引:441
作者
Castanier, MP [1 ]
Pierre, C
机构
[1] Univ Michigan, Ann Arbor, MI 48109 USA
[2] McGill Univ, Montreal, PQ H3A 2K6, Canada
关键词
D O I
10.2514/1.16345
中图分类号
V [航空、航天];
学科分类号
08 [工学]; 0825 [航空宇航科学与技术];
摘要
The literature on reduced-order modeling, simulation, and analysis of the vibration of bladed disks found in gas-turbine engines is reviewed. Applications to system identification and design are also considered. In selectively surveying the literature, an emphasis is placed on key developments in the last decade that have enabled better prediction and understanding of the forced response of mistuned bladed disks, especially with respect to assessing and mitigating the harmful impact of mistuning on blade vibration, stress increases, and attendant high cycle fatigue. Important developments and emerging directions in this research area are highlighted.
引用
收藏
页码:384 / 396
页数:13
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