带平台下阻尼器的多片旋转叶片强迫扭振响应研究

IF 0.1 4区 工程技术 Q4 ENGINEERING, AEROSPACE Aerospace America Pub Date : 2023-08-19 DOI:10.3390/aerospace10080725
Yanan Wu, H. Xuan, Changyao Wu, D. Mi, Mingmin Qu, Tao Jin
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引用次数: 1

摘要

平台下阻尼器(upd)是干摩擦阻尼器的一种,通常用于涡轮叶片的减振。本文研究了多叶片系统中upd对涡轮叶片强迫扭振响应的影响。将预应力有限元模态分析与谐波平衡法相结合,计算了带和不带upd系统的强迫扭振响应。然后在一个有和没有upd的旋转多叶片系统上进行了实验,重点研究了质量堆积对阻尼性能的影响。结果表明,平台下减振器的安装增加了叶片扭转振动最大响应对应的频率,并产生了多个振动响应峰值,这些峰值随upd质量的不同而变化。在适当的法向力作用下,平台下阻尼器可有效降低叶片扭振68.9%。但upd的法向力过大会导致多个较大的振动峰,在工程实践中应尽量避免。此外,带upd的旋转多叶片系统的强迫扭振响应的数值计算结果与实验结果较为接近,表明该计算方法可以有效地应用于带阻尼器的旋转叶片强迫振动的非线性预测。
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Study on the Forced Torsional Vibration Response of Multiple Rotating Blades with Underplatform Dampers
Underplatform dampers (UPDs), a type of dry friction damper, are commonly used for vibration reduction of turbine blades. This study investigated the effect of UPDs on the forced torsional vibration response of turbine blades within a multi-blade system. Pre-stressed finite element modal analysis and the harmonic balance method were combined to calculate the forced torsional vibration responses of a system with and without UPDs. The experiments were then carried out on a rotating multi-blade system with and without UPDs, with a focus on the effect of mass stacking on damping performance. The results showed that the installation of underplatform dampers could increase the frequency corresponding to the maximum response of the blade torsional vibration and cause multiple peaks that varied in the vibration response based on the mass of the UPDs. With an appropriate normal force, the underplatform dampers could effectively reduce the blade torsional vibration by 68.9%. However, excessive normal force of UPDs could lead to multiple large vibration peaks, which should be avoided in engineering practice. Additionally, the numerical results for the forced torsional vibration response of the rotating multi-blade system with UPDs were relatively close to the experimental results, indicating that the calculation method could be effectively applied to the nonlinear prediction of forced vibrations of rotating blades with dampers.
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来源期刊
Aerospace America
Aerospace America 工程技术-工程:宇航
自引率
0.00%
发文量
9
审稿时长
4-8 weeks
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