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

WU Xiang-yu; HAN Xu-jun; ZHANG Hai-yang; WANG Jing; LUAN Xu

doi:10.13224/j.cnki.jasp.2014.06.017

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

更新时间：2026-07-07

- Analysis and design of platform damper construction for high pressure turbine blade
- Issue 6, (2014)
- 作者机构：
  
  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
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.06.017
  CLC：
- Published：2014
- 稿件说明：
移动端阅览
吴向宇, 韩绪军, 张海洋, 王婧, 栾旭. 高压涡轮工作叶片缘板阻尼结构设计分析[J]. 航空动力学报, 2014, (6): 1376-1381. doi: 10.13224/j.cnki.jasp.2014.06.017

WU Xiang-yu, HAN Xu-jun, ZHANG Hai-yang, et al. Analysis and design of platform damper construction for high pressure turbine blade[J]. 2014, (6).
吴向宇, 韩绪军, 张海洋, 王婧, 栾旭. 高压涡轮工作叶片缘板阻尼结构设计分析[J]. 航空动力学报, 2014, (6): 1376-1381. doi: 10.13224/j.cnki.jasp.2014.06.017 DOI：

WU Xiang-yu, HAN Xu-jun, ZHANG Hai-yang, et al. Analysis and design of platform damper construction for high pressure turbine blade[J]. 2014, (6). DOI： 10.13224/j.cnki.jasp.2014.06.017.

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%.

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%.

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Related Institution

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