压气机叶片气动阻尼的改善设计

郭雪莲; 李琳

压气机叶片气动阻尼的改善设计

郭雪莲,
李琳

北京航空航天大学能源与动力工程学院,北京 100191

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出版历程
- 收稿日期: 2011-09-07
- 刊出日期: 2012-08-28

Design method for improving aerodynamic damping of compressor blades

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

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.
- 压气机叶片 /
- 气动阻尼 /
- 重心线调节 /
- 相似度 /
- 设计方法
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.
- compressor blade /
- aerodynamic damping /
- gravity center modification /
- similarity /
- design method

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参考文献(12)

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