带冠预扭涡轮叶片模态分析及动应力测试验证

袁巍; 陈国智; 张红晓

doi:10.13224/j.cnki.jasp.2020.10.019

带冠预扭涡轮叶片模态分析及动应力测试验证

doi: 10.13224/j.cnki.jasp.2020.10.019

基金项目: 装备预先研究项目（41410010202）

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- 被引次数: 0
出版历程
- 收稿日期: 2020-01-07
- 刊出日期: 2020-10-28

Modal analysis and dynamic stress test verification of shrouded pretwist turbine blade,

1.
Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China
2.
Aviation Key Laboratory of Aero-engine Vibration Technology,Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China

摘要

摘要: 介绍了航空发动机带冠预扭涡轮叶片非线性接触预应力模态分析机理,并以ANSYS软件为平台,对某型涡轴发动机动力涡轮叶片进行了模态分析。结果表明：非线性接触预应力模态分析方法得到的叶片盘9～13节径1阶频率与动应力测试频率在变化规律上保持一致,差别基本稳定在12%～13%,计算精度较传统方法有了明显的提高。
- 带冠预扭涡轮叶片 /
- 模态分析 /
- 动应力测试 /
- 非线性接触预应力 /
- 摩擦阻尼
Abstract: The non-linear contact prestress modal analysis mechanism of aero-engine shrouded pretwist turbine blade was introduced. The modal analysis of a turboshaft engine power turbine blade was carried out on the platform of ANSYS software. The results showed that the first order frequencies of 9-13 nodal diameter of blade blisk obtained by non-linear contact prestress modal analysis method were consistent with dynamic stress test frequencies, and the difference was basically stable at about 12%-13%. The results indicate that the calculation accuracy is improved obviously compared with the traditional method.
- shrouded pretwist turbine blade /
- modal analysis /
- dynamic stress test /
- non-linear contact prestress /
- friction damping

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参考文献(18)

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