Design methodology of vibration reduction experiment of aero-turbine blades with underplatform damping
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摘要:
为了深入了解叶片-盘系统的振动特性、检验已有阻尼装置减振效果是否满足技术指标，有必要设计开展带干摩擦阻尼真实叶片减振特性试验。真实叶片振动特性试验相较模拟叶片试验而言，在设计过程中会遇到更多挑战，以定型带缘板阻尼涡轮叶片为例，设计了真实涡轮叶片组减振特性试验方案，通过开展涡轮叶片组减振特性试验，得到不同正压力下受激叶片的频响函数曲线。试验数据表明：缘板阻尼装置在设计频率范围内对叶片组振动有明显的抑制效果，最佳减振效果能使受激叶片共振幅值减小60%以上。
Abstract:In order to understand the vibration characteristics of the blade-disc system and to check whether the damping effect meets the technical specifications, it is necessary to design and carry out dry friction damping blade vibration characteristics experiment. Real blade vibration characteristics experiments encounter more challenges in the design process than simulated blade experiments. A certain type of turbine blade with underplatform damper was taken as an example to design an experimental programme for the vibration damping characteristics of real turbine blades. The frequency response function curves of excited blades under different positive pressures were obtained by carrying out vibration damping characteristic experiments of turbine blades. The data showed that underplatform damping device within the design frequency range of the blade group vibration had a significant inhibition effect, the best vibration damping effect can reduce the excited blade co-vibration amplitude up to 60%.
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图 2 各正压力下受激叶片频响函数曲线
Figure 2. Frequency response function curves of excited blades under various positive pressures
图 12 激振力幅值5 N受激叶片频响函数曲线
Figure 12. Frequency response function curves of excited blades under excited force 5 N
图 13 仿真计算和减振试验结果对比
Figure 13. Comparison of simulation and vibration reduction experiment
表 1 扫频测试结果
Table 1. Sweep experiment results
监测点 共振频率/Hz 第1阶 第2阶 第3阶 受激叶片监测点 1510 1608 1648 中间叶片监测点 1518 1610 1648 
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表 2 相对共振振幅和减振效率随正压力变化表
Table 2. Variation of relative resonance amplitude and damping efficiency with positive pressure
正压力P/N 相对共振振幅$\overline{X} $/% 减振效率$ \eta $/% 20 45.40 54.60 50 36.40 63.70 100 44.30 55.70 200 46.50 53.50 300 53.50 38.70
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