高压涡轮工作叶片缘板阻尼结构设计分析

吴向宇; 韩绪军; 张海洋; 王婧; 栾旭

doi:10.13224/j.cnki.jasp.2014.06.017

高压涡轮工作叶片缘板阻尼结构设计分析

doi: 10.13224/j.cnki.jasp.2014.06.017

1. 北京航空航天大学能源与动力工程学院, 北京 100191;
2. 中国航空工业集团公司沈阳发动机设计研究所, 沈阳 110015

详细信息

作者简介:
吴向宇（1969- ），女，陕西咸阳人，研究员，博士生，主要从事涡轮气冷叶片设计工作.

中图分类号: V231.92
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出版历程
- 收稿日期: 2014-04-02
- 刊出日期: 2014-06-28

Analysis and design of platform damper construction for high pressure turbine blade

1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China

摘要

摘要: 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%.
- 高压涡轮工作叶片 /
- 缘板阻尼 /
- 阻尼效果 /
- 正压力 /
- 振动响应
Abstract: Analyzed the damping effect of a real engine's platform damper structure of high pressure turbine blade (HPTB) through calculation and experiment, experimental results show that with the increase of positive pressure, damping ratio increase at first, then reduce, and then fluctuate within a certain range, peak of the damping ratio occurs between 100-280N. Calculated positive pressure under the condition of first order bending resonance is 123-158N, damping effect consist with experimental results. Classified the platform damper structures commonly used and compared their advantages and disadvantages.Improved the damper mass about 30% by increased thickness of the damping sheet, when excitation force is 1%, 3% and 5% mass of aerodynamic force, a reduction of vibration response is 31%, 21% and 16%.
- high pressure turbine blade /
- platform damper /
- damping effect /
- positive pressure /
- vibration response

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参考文献(16)

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