Fluid-structure interaction and flutter analysis of compressor blade based on CFD / CSD

WANG Zheng; WU Hu; SHI Ya-feng; YANG Jin-guang; CAI Jin

Chinese

您当前的位置：

首页 >

文章列表页 >

Fluid-structure interaction and flutter analysis of compressor blade based on CFD / CSD

更新时间：2026-07-07

- Fluid-structure interaction and flutter analysis of compressor blade based on CFD / CSD
- Vol. 26, Issue 5, (2011)
- 作者机构：
  
  1. 西北工业大学动力与能源学院,西安,710072
  2. 西北工业大学机电学院现代设计与集成制造技术教育部重点实验室,西安,710072
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2011
- 稿件说明：
移动端阅览
WANG Zheng, WU Hu, SHI Ya-feng, et al. Fluid-structure interaction and flutter analysis of compressor blade based on CFD / CSD[J]. 2011, 26(5).
DOI：

WANG Zheng, WU Hu, SHI Ya-feng, et al. Fluid-structure interaction and flutter analysis of compressor blade based on CFD / CSD[J]. 2011, 26(5). DOI：

摘要

针对叶片故障的原因颤振问题

基于计算流体动力学/计算结构力学(CFD/CSD)耦合算法

研究了压气机典型叶片的流固耦合(FSI)问题及颤振特性.使用有限体积法求解非定常三维Navier-Stokes方程和有限元法求解三维结构体模型

在两个求解器间由载荷转换、网格变形传递和同步化方法完成数据交换及求解.以高性能风扇NASA(National Aeronautics and Space Administration) Rotor 67为例

对其工况下的气弹响应进行分析

计算结果与实验数据进行对比

以确认方法的正确性和有效性.结果表明可根据循环功和平均压力分布来分析叶片的颤振机理

从而为压气机稳定性的判定提供重要依据.

Abstract

For the most important flutter problem of turbomachinery blades

the fluid-structure interaction (FSI) problems and flutter characteristic of turbomachinery blades were studied in present paper based on the CFD/CSD (computational fluid dynamics/computational structural dynamics) algorithm.The three-dimensional unsteady Navier-Stokes equations and three-dimensional structural model were solved by the finite volume method and the finite element method

respectively.High accuracy in calculation and data exchange were gained by using load transfer

deformation tracking and synchronization between two solvers.The procedure successfully simulated the aeroelastic responses of a high performance fan rotor

NASA (National Aeronautics and Space Administration) Rotor 67

under a range of operational conditions

and the results were compared with the experiment.The results show that the flutter mechanics of the compressor blade could be illustrated based on the distribution of cycle work and mean pressure

which is helpful to the decision of compressor stability.

关键词

Keywords

references

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Surge control system design and validation for an aero⁃engine

Numerical analysis of tip leakage flow effect on compressor stability

Impact of bow shock on tip leakage flow in counter-rotating compressor

Unsteady aerodynamic characteristics of ducted coaxial propeller unmanned aerial vehicle

Accuracy analysis of unsteady numerical simulation methods for axial flow compressor

Related Author

Bo WANG

Xinglong ZHANG

Xinfei ZHANG

Jiexian CHE

Tianhong ZHANG

WANG Hao

TU Baofeng

徐强仁

Related Institution

Sichuan Gas Turbine Establishment，Aero Engine Corporation of China

Project Management Center，Equipment Department of Air Force，People's Liberation Army

College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics

中国科学院工程热物理研究所中国科学院轻型动力重点实验室

中国科学院大学航空宇航学院

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰