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对某高压涡轮工作叶片缘板阻尼结构进行了阻尼效果计算及试验分析,试验结果表明:随着正压力的增加,阻尼比基本呈现为先增加后降低,然后在一定范围内波动的规律,阻尼比峰值出现在100~280N之间.计算得到一弯共振下的正压力为123~158N,与阻尼效果试验基本一致.分类比较了常用缘板阻尼结构形式的优缺点,改进完善后的阻尼片结构质量增加约30%,在激振力占气动力百分比分别为1%,3%及5%时,振动响应减幅分别为31%,21%及16%.
The damping effect calculation and experimental analysis of the damping structure of the vane flange at a high pressure turbine are carried out. The experimental results show that with the increase of the positive pressure, the damping ratio basically increases firstly and then decreases, and then fluctuates within a certain range, damping The peak value appears in the range of 100-280 N. The positive pressure under a bending resonance is calculated to be 123-158 N, which is basically the same as the damping effect test.Compared the advantages and disadvantages of commonly used damping structures, The quality of the structure is increased by about 30%. The vibration response decreases by 31%, 21% and 16% respectively when the excitation force accounts for 1%, 3% and 5% of the aerodynamic force respectively.