Design method for improving aerodynamic damping of compressor blades

GUO Xue-lian; LI Lin

Chinese

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Design method for improving aerodynamic damping of compressor blades

更新时间：2026-07-07

- Design method for improving aerodynamic damping of compressor blades
- Vol. 27, Issue 8, (2012)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院,北京,100191
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2012
- 稿件说明：
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GUO Xue-lian, LI Lin. Design method for improving aerodynamic damping of compressor blades[J]. 2012, 27(8).
DOI：

GUO Xue-lian, LI Lin. Design method for improving aerodynamic damping of compressor blades[J]. 2012, 27(8). DOI：

摘要

针对气动阻尼在强迫响应分析中的应用现状

提出了一种在叶型基本确定的条件下进一步设计气动阻尼的方法.该方法只对叶片基元级的积叠轴做微小的调整

这种调整对叶栅流场气动特性和固有频率的影响很小

可以忽略不计.研究了积叠轴调整对叶片气动阻尼的影响

得出在不需要大量流场计算的条件下

即可判断如何调整叶片积叠轴以达到增加气动阻尼目的的结论.在分析中用振型相似度衡量叶片模态振型与气动阻尼比的关系

相似度越小气动阻尼比越大.

Abstract

Considering the situation of the application of aerodynamic damping in the forced response

an aero-damping design method based on basic blade profile was proposed.It was revealed that a slight adjustment to the blade-stacking axis of blade can change the aero-damping

meanwhile

the effect on the fluid filed can be confined to the minimum.The relationship between the adjustment and the aero-damping was established.Owing to such a relationship

a large quantity of fluid calculations could be avoided and an improveing of the aero-damping by adjusting the stacking axis can be obtained.In this way

the shape similarity was used to connect the mode shape and aerodynamic damping.The smaller the similarity

the bigger the aero-dynamic.

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